CN104236390B - Space suit - Google Patents

Abstract

A kind of by high height or the space suit of taking advantage of the passenger in rocket to wear in space, described space suit includes: in one group of joint of at least some joint of the passenger wearing described space suit, described group of joint may be locked in optimum air power position relative to the rocket for launching, wherein said passenger wears described space suit and is loaded, foot arrives first on the top of described rocket, for opposing gravitational effect of described rocket during launching.

Description

Space suit

The application is filing date on February 10th, 2011, Application No. 201180018304.5, invention entitled " rocket Emission system and support means " the divisional application of patent application.

Cross-Reference to Related Applications

The US provisional patent that the application on February 11st, 2010 submits to according to 35 119 (e) Zhang Yaoqiu of United States Code No. Application No.61/337, the interests of 645, this patent application is integrally incorporated herein with it by quoting.

Technical field

The present invention relates to space suit, and relate to be transported to various types of payload upper atmosphere and farther The system at place, and relate more specifically to the high cycling rate emissivity rocket launcher with high-rise transmitting station.The weight of cable itself Amount is lighter than the balloon of air and offsets.Cable is strained by one or more balloons being lighter than air, and the tether being pivoted Cable grappling.

Background technology

By useful material such as propellant, the gas being used for life support etc. and manufacture article be transported to upper atmosphere or A lot of methods of farther place exist or have been suggested in nearest publication.

These rockets relating generally to be provided power by chemically based, core or the laser instrument on ground or main source of energy.Reduce and will have Material and manufacture article and be transported to the various methods relating to rocket of per unit mass cost of upper atmosphere or farther place Exist or be suggested.

These include the rocket-powered flight device that can re-use, such as by the most retired U.S. space shuttle or Russia Present out-of-operation Buran.At present, only there is the multistage fire of chemistry of belt on solid fuel power rocket booster The small-sized Pegasus of arrow or aircraft or rocket such as U.S. of being transported to High aititude before transmission is being used by known In.

The method proposed of the conveying cost being reduced to upper atmosphere or farther place most commonly relates to by lighting Increase initial kinetic energy before sustainer or multiple electromotor or potential energy transmits energy to rocket.This proposal bag can be realized Include: the height hung under the balloon being lighter than air of disposable free flight, or from utilizing chemical propellant or compressed air Or the big spray gun of compression hydrogen is with high speed forced jet, or it is transported to be connected to aircraft such as Virgin Galactic (Wei Zhenyin River) High aititude of White Knight Two, or it is transported on the cable tether cable after aircraft the High aititude of traction, or Linear response electromotor based on ground is used to accelerate at high speed, or before lighting one or more sustainers of rocket Injection or rocket-powered sledge.

The method of the proposition for reducing conveying cost being not related to rocket is so-called " space elevator ", wherein Big thing block is bolted to the earth by the individual cable of several thousand miles length.Big thing block with geosychronous track in around the earth Track runs, and keeps cable to strain.This cable will then be used in the way of being similar to the railroad rails that train is advanced.

The main difficulty of this later approach is, the tensile strength of the material needed for cable is considerably beyond any existing material Material, especially because the half weight of cable will be sizable.Another difficulty is to provide for enough energy at this electricity The aircraft climbed on cable is substantially to climb out of most of gravitational field of the earth.Weightless superpower cable material is to such " space elevator " is preferable, but this there is not yet.Additionally, the problem of the up to energy supply of the cable of several thousand miles causes Arrive pencil microwave or the consideration of laser power of climbing flight device.Cloud and defocusing of air on pencil power are imitated with obstacle Should greatly reduce the amount of the power actually arriving in climbing flight device.Owing to needs brake to prevent (climbing) aircraft Exceeding the speed ability of the mechanism that described aircraft remains to cable, returning to terrestrial time dissipation of energy at aircraft may Quite waste.

A lot of current methods proposed need new material or the development of massive material, and may be tens of by arrive Commerce services is seen, even if being also few if having in Nian.

The current launching technique of major part be directed to use with the big energy that mainly obtains from Fossil fuel such as coal or oil with Produce low-temperature liquid oxygen oxidant, low temperature liquid hydrogen or other liquid hydrocarbon or solid propellant.This of non-renewable energy resources Individual use is poor efficiency inherently, because there is the mixing of process inefficient rate in each production phase of fuel.For by aircraft Big quality and the most poisonous character of releasing the obsolete material of air also often result in ecological damage, and weather maybe may be caused to disturb Disorderly.

Accordingly, there exist to much smaller than on Current commercial available often conveying Unit cost by useful material example Such as propellant, for living the gas etc. supported and manufacture the needs that article are transported to the method for upper atmosphere or farther place, should Method utilizes currently available material and technology.Additionally, by making to generate electricity from water power, underground heat or sun photovoltage generate Electricity minimizes the quality of the material of the air for aircraft is released the earth to draw lighting the one or more of aircraft Hold up make before aircraft rise the highest by be in ecology useful.

Air monitoring had been carried out more than 50 years.Solar radiation, the concentration of minimum gas, temperature, pressure and other ginseng The measurement (direction of the climate change of the earth can be predicted by these parameters) of number drastically increases us to our world The understanding of weather.It is for ozone hole, the raising continuously and other " greenhouse " gas in air and now of carbon dioxide Extremely important more than 50 kinds of chemical substances in earth atmosphere.

" greenhouse " and ozone depletion gas example when the increase level of other change causing global warming and global climate When occurring such as carbon dioxide, Chlorofluorocarbons, nitrous oxide and sulfur hexafluoride, create carrying out air on the basis of more continuous print The needs of the increase of monitoring.Relate to equipping the manned of a lot of instrument or unmanned aviation for monitoring the current method of atmospheric condition Device, there is the balloon of the free flight of the instrumentation package of suspension, there is sampling and the rocket of instrument payload and based on ground Laser instrument and radar station.

In addition to station based on ground, these can only provide the relatively short period that atmosphere data uses.By being not based on ground The maximum length in time that is monitored of method at present in the case of balloon less than more than several days, and the shortest persistent period Such as rocket may be with a minute measurement.A lot of in these air monitoring methods also utilize the instrumentation package being intended for single use, and show The station based on ground having can not obtain physical samples be chemically defined, antibacterial/viral level or intensity of sunlight and frequency spectrum Analysis and other data in the entire depth of air.

Accordingly, it would be desirable to extend to the structure of big height from the surface of the earth, can install on this structure for air and The incident sun and the continuous of other radiation monitor and the instrument of sampling.

In radio telecommunication and horizontal plane, radar is used by global a lot of countries for security reason more expensively.

The such as U.S. of country is ordered about in nearest worldwide due care about abrupt terrorist attack Other detection device of zones of different by using radar and utilize electromagnetic spectrum increases Supervision Level.This is by Congress 2007 Year 9/11 committee member's bill prove, this bill in order to the U.S. safety and partly radio telecommunication system with interoperable have Close.Radar based on ground is limited by the curvature of earth surface, and in order to realize bigger useful scope, radar and other system are pacified It is contained in the airborne vehicle of high-altitude flight or on balloon that low clearance is fastened.

In a similar fashion, honeycomb radar telephone operator seeks to expand have Receiver And Transmitter by use at present The area that services of High aititude airborne vehicle, this airborne vehicle is proposed in the loop in coverage flight.This pole High aititude situation is INMARSAT and IRIDIUM satellite telephone system, and it utilizes the most static of extremely expensive and unrepairable Satellite for telecommunications.

Thus, it can be seen that, exist lower cost High aititude radar and the needs of radio telecommunication platform.

The invention still further relates to tourism.High monument such as Eiffel Tower, high constructure such as Empire State Building or High aititude The visit of physical feature such as Everest continues to be the common activities of traveller.It practice, the most also have expensive height The non-military interest of the increase of altitude aircraft flight.Recently, by Burt Rutan's Space Ship One win to 100 " the X bonus " of kilometer or higher safe flight has promoted the commercialization that High aititude transports further.Space Ship One and The problem of Space Ship Two is, their rocket engine uses nitrous oxide oxidant and the poly-fourth of terminal hydroxy group of liquefaction Diene solid fuel, this solid fuel produce include flue dust, the rubber that partly burns and the refuse of other toxic material.? In near application, specifying, the alternate fuel of Space Ship Two is studied, such as Colophonium and paraffin.Although these are cheap Fossil fuel, may burning be not completely.Produce in the case of Colophonium, metal-oxide and acid cure compound and pollute Waste product is possible.Recently to the only flue dust that 1,000 transmittings of the Martin Ross of annual airline calculate The temperature that impact suggestion stratosphere at earth earth polar divides and surges.The emissivity announced be per week the most several times.

Therefore to more inexpensively, more frequently by traveller transport higher height and have the market of growth.

In the past few years, parachuting to have changed into as motion includes ram-air aerofoil profile parachute, and auxiliary equipment is such as The use of the little firm wing, small-sized surfboard, rocket and even small sized turbine jet engine engine.Additionally, chutist's take-off Height in increase, although this is limited by two principal elements.These factors are: civilian solid at higher operating at elevations Determine the limited capacity of wing aircraft and helicopter, wherein there is the civil aviation to rich oxygen containing respiratory system and limit half an hour； Or to pressurization suit or the needs in cabin.In a short time, it is contemplated that when the market development of High aititude parachuting, civilian pressure cuffs Parachute jumping enthusiast will be made available by by clothes.

Consider the most now the parachuting of more extreme form.These forms proposed relate to from the top of air model in one's power Impale jumping or even enter back into from space, as gone out when the passenger of unhappy orbiting spacecraft will return terrestrial time safely Existing.

Accordingly, there exist the novelty to the parachuting for new model and the market of the relatively growth of High aititude platform.Actual On, also there is the lasting requirement to the low-cost platform at the height of up to 10,000 feet.

In the nearest time, in order to reconnoitre or other purpose, aircraft rapid deployment is actual to the place having military interests On necessitate.Additionally, the transport of business hypersonic speed there to be the interest of growth.For this purpose it is proposed, have the height of supersonic speed internal combustion engine Supersonic plane is developed to realize these needs recognized in a lot of countries.

But, the engine of such aircraft being designed to effectively operate with higher Mach number is reported as needs and reaches Exceed the speed of three times of the velocity of sound to make them start.In order to make engine from static in the various state of flights of superelevation velocity of sound Operation, needs sizable complexity, has subsidiary weight to hinder.Except use rocket booster reach priming speed with Outward, other design path seems to need two component engine.First component is to fly ultrasonic from subsonic to low mach Dominant turbofan or turbojet in row state, it is transitioned into in the superelevation velocity of sound of High Mach number Combustion engine, and close first component.

It is designed to much do not have the movable part will be therefore in weight at the engine of superelevation velocity of sound range of operation On lighter, simpler and the most expensive.

In 2003, due to the structural failure occurred during launching phase, the manned spacecraft Columbia of the U.S. When entering back into the air of the earth destroyed.Over time, there is also eligible for repair track airborne vehicle accumulation, with And the bad and dangerous remains that the track airborne vehicle damaged removes from track with needs.

Because the Columbia space shuttle of the airborne vehicle such as U.S. is the heaviest, and owing to carrying return flight in an atmosphere Time the low temperature that uses or the danger of other fuel and weight hinder, they lack can be after entering back within considerable time The leading engine of operation, these airborne vehicles must leave track, if they can slide into has enough intensity at specific point With several airports of the runway of length, these runways exist near its rail track.

Therefore, other people can fly creating with the subsonic in earth atmosphere, supersonic speed or lasting superelevation velocity of sound The less airborne vehicle that in row, the ability of flight performs useful work in atmospheric exterior under the power of oneself is inevitable. These may use rocket power to launch, and after any point enters back into, flies to be suitable for such relatively flivver and land Any one in the multiple existing civilian or military airport of ground safety.

These save the passenger of the track airborne vehicle of damage and from the unmanned track boat damaged quickly and safely by being used for The track of pocket is repaired or removes bad and dangerous remains.The another type quickly come into operation is for refuelling or connection To the space airborne vehicle damaged and serve as towboat to extend the little servicing aircraft of useful life longevity of such aircraft.Further Little airborne vehicle or rocket can be used for launching moonlet, or the assembling of the big structure in the track and the modularity portion of refuelling Part, it can be used for the gravitational field escaping from the earth may reflect dangerous asteroid or the exploration solar system.European Space Agency and Russia Ross space agency starts to consider to create shipyard in Low Earth Orbit recently, in order to utilize the goods the most do not built to return The senior moon entering back into aircraft (ARV) or Mars Mission.

Additionally, it is contemplated that the lasting needs to serving satellite and other track airborne vehicle will be had.This service can include conveying Food, fuel, for breathing or the compression of other purposes or liquid gas, medical treatment and science supply, space flight of replacing or upgrade Personnel that the electricity of device system, machinery or miscellaneous equipment, transport are sick or injured or the personnel of replacement.

It is therefore contemplated that there are the needs of the most cheap device to transmitter module parts, modular member is used for Assembling in space, little civilian cause airborne vehicle, moonlet and miscellaneous equipment and refuelling.

The a lot of telescopical sensitivity used in astronomy greatly reduces due to air dust and aerosol, Because light is reflected by above-mentioned microgranule or scatters.Looked at the top on minimum affected telescope mountain range the most a long way off Arrive, on most of air that major part dust or aerosol are found.

Therefore, there are the needs to High aititude platform further, this High aititude platform can install sensitive telescope. Specifically, multiple platforms and telescope can be used for simulating the very big aperture of planet being such as currently used for being positioned in other solar system Telescope.

When in December, 2004 Indonesia Tsunami disaster occurs, it is understood that a lot of affected regions reconnoitre and Initially the conveying subsequently of disaster relief supply is not until the most occurring till a couple of days after event or even a few weeks longer, and result is Thousands of deaths, if many when can get than the disaster relief in early days.Accordingly, it would be desirable to the rocket-firing system of quickly baby track flight is come The disposable rocket using simple GPS to guide carries the least nobody and reconnoitres and drive an airplane and the last GPS of thousands of tons of draws The disaster relief supply of the parachute conveying led.

Summary of the invention

Accordingly, there exist to much smaller than on Current commercial available often conveying Unit cost by useful material example Such as propellant, for living the gas etc. supported and manufacture the needs that article are transported to the method for upper atmosphere or farther place, should Method utilizes currently available material and technology.Additionally, by making to generate electricity from water power, underground heat or sun photovoltage generate Electricity or other regenerative resource minimize the quality of the material for aircraft is released earth atmosphere to light aircraft One or more engines before make aircraft rise the highest by be in ecology useful.

It is an object of the invention to provide for payload being sent to space and the height of satellite loaded in space Emissivity rocket launcher.

It is yet another object of the invention to provide high emissivity rocket launcher, its available water generating or be used for making rocket Rise to other rechargeable energy of firing altitude.

Another object is that utilization uses optionally or rechargeable energy is made more eco-friendly fuel and oxidant.

It is yet another object of the invention to provide and utilize the high-rise of electronic tubulose laugnching lug to rotate transmitting station, transmitting station passes through Cable is connected to ground, is connected to cable for straining and support the balloon being lighter than air of cable and dependency structure.

It is a further object of the present invention to provide to reuse and for utilizing motor via tethers by use The regeneration brake of machine recovers to be returned to by empty rocket launching bracket after the transmission the device of the potential that terrestrial time relates to.

A further object of the present invention causes the whole world when other propellant in increase level " greenhouse " gas or air Air monitoring is provided during the change of weather on the basis of more lasting.

It is a further object of the present invention to provide High aititude radar and radio telecommunication platform to greatly increase spatial volume The region of the earth surface correspondingly covered.

It is another object of the present invention to for traveller provide continuous print arm's length pricing business access with visit except rocket, The atmosphere of other device inaccessible beyond the lighter-than-air craft of aircraft or free flight.

It is yet another object of the invention to provide more available more than the current extreme height to various new models or space parachute jumping The platform of High aititude and the height in up to one myriametre that can access in the case of not having the oxygen supplemented or compression suit The low-cost platform at place.

It is a further object of the present invention to provide the most cheap device launching little civilian cause airborne vehicle, it is used for safety Ground save damage track airborne vehicle passenger, from damage unmanned track airborne vehicle track reparation, upgrade or remove bad With dangerous remains.

It is yet another object of the invention to provide the High aititude platform on the cloud layer of the earth, can on this High aititude platform Sensitive telescope is installed, particularly through calculating device, including the telescope that the electromagnetic wave of light wave and radio wave combines, Light wave and radio wave are received to serve as the single telescope of the diameter of the distance of the ragged edge member equal to array, in order to The observation more senior than being currently available that, in addition to space.

Another object is to provide the device for keeping in repair satellite and other track airborne vehicle, such as in order to supply food, use In breathing or the compression of other purposes or liquid gas, fuel, medical treatment and science supply, Space Vehicle System of replacing or upgrade Electricity, machinery or miscellaneous equipment and for transporting sick or injured personnel or replacement personnel.

One purpose is to provide for transporting loading rocket along the cable extending up to transmitting station through air The transportation system of bracket.

Another object is to provide the transmitting station for rocket is transported to be positioned at atmosphere eminence along cable.

Being also an object that a kind of device of offer, it keeps for the bracket loading rocket and is directed to for inciting somebody to action along cable Bracket is transported to be positioned at the transmitting station of atmosphere eminence and for empty bracket is transported to the device on ground from transmitting station.

Being also an object that a kind of system of offer, it deposits rocket and for by rocket or the bracket of loading rocket for safety It is transported to for the bracket of rocket or loading rocket being kept and being directed to for the bracket of rocket or loading rocket is transported to It is positioned at the device of the device of the transmitting station of atmosphere eminence.

Thering is provided the device for carrying the bracket loading rocket is also the purpose of the present invention.

It is another object of the present invention to for carry rocket, the parts of rocket, the bracket of rocket and/or from storage facilities to Keep and assemble facility rocket conveying equipment clamper, for subsequently transport to for will load rocket bracket promote System to transmitting station.

It is a further object of the present invention to provide the aburton machine for rocket being loaded bracket.

It is a further object of the present invention to provide elevator assembly, it is for rising to the bracket loading rocket for filling The bracket carrying rocket loads the device of one group of elevator cable and to rocket launching pad.

It is a further object of the present invention to provide for receiving the capstan head of the bracket loading rocket and for rocket will be loaded It is relevant that bracket is directed to for the bracket arrangement guide frame device on the cable being directed to transmitting station by loading rocket Device.

It is yet another object of the invention to provide for the balloon being lighter than air is connected to cable system stably to keep And separating the equipment of cable, described cable is directed into transmitting station.

It is a further object of the present invention to provide the one group of cable arriving transmitting station for making the bracket of loading rocket rest in On Docking station.

Offer for the bracket loading rocket is transported to the purpose of the electric power of the transmitting station of rising along cable system is Another target of the present invention.

It is a further object of the present invention to provide for along cable system by load rocket bracket rise to Docking station it On enhancing ring.

Another object be to provide for by cable be separated into the transmitting station of rising and be used for the equipment of stable cable.

The purpose of the present invention is also provided with for framework and other device being connected between ground and the transmitting station of rising The attachment means of the cable extended.

Thering is provided the device for being maintained in bracket by rocket is also the purpose of the present invention.

Another object is to provide installation and is used in the telescope being kept upright in an atmosphere on one group of cable.

There is provided and keeping the rocket the most upwards transported also to be this one or more people or equipment or supply Bright purpose.

The fluid pressure of improvement that it is another object of the present invention to be worn by people compensates suit to allow in rocket launching and big Gas restrains oneself high acceleration during entering back into.

Preferred embodiment according to invention discussed below achieves these purposes.From inventive concepts as discussed below Neutralizing from claims, other purpose purpose will be apparent to one skilled in the art.

Accompanying drawing explanation

Fig. 1 describes to be formed the schematic diagram of some features of the preferred embodiment of the rocket-firing system according to the present invention.

Figure 1A and 1B is the detailed view of the feature shown in Fig. 1.

Fig. 2 is to illustrate assembling and basic Load System of the rocket-firing system according to the preferred embodiments of the invention Schematic diagram.

Fig. 3 illustrates according to an aspect of the preferred form of the present invention and is loaded in axial transport equipment by rocket.

Fig. 4 is the schematic diagram illustrating the different views keeping the bracket of rocket, dumping mechanism and axial transport equipment.

Fig. 5 be illustrate the tracking loop of the bracket according to the preferred embodiments of the invention, storage shelf, rocket keep and The schematic diagram of the plan view layout of assembly or fitting table, bracket, fuel storing unit and the electric power system relevant with making rocket preparation transmitting.

Fig. 5 A is the amplification details of a part for the guide rail shown in Fig. 5.

Fig. 6 illustrates and according to the preferred embodiments of the invention, rocket loads refuelling or assemble the exemplary form in cabin.

Fig. 7 illustrates the details of the aburton machine shown in Fig. 6.

Fig. 7 A is the lower limb shown in Fig. 7 and the amplification detail perspective view reversing lock pin.

Fig. 8 is that the liter illustrating the preferred embodiments of the invention with lateral transfer equipment and rocket holding bracket is come down to a lower group The schematic diagram of the operation of part.

Fig. 8 A is the amplification detail view of a form for supporting the device for the turntable rotated.

Fig. 8 B is the another form of amplification detail view for supporting the device for the turntable 72 rotated.

Fig. 9 be the lifting assembly according to the preferred embodiments of the invention, revolving bed, lateral transfer equipment, the one of bracket The schematic diagram of part.

Fig. 9 A is the enlarged perspective of conical dowel pin.

Fig. 9 B is the enlarged perspective that lock pin is reversed in segmentation.

Fig. 9 C is the amplification detail view of the base of bracket.

Figure 10 illustrate according to the preferred embodiments of the invention for make rocket keep bracket be received in cableway, make fire Arrow keeps bracket to align with cableway and starts the device that rocket keeps bracket insert cableway.

Figure 10 A is the amplification detail view of cable separation part.

Figure 11 illustrates another portion of the preferably part of the present invention about the cable system keeping bracket for transport rocket Point.

Figure 12 is the details of the upper part of the preferred form of the present invention with exemplary form, and it illustrates according to the present invention's The balloon assembly keeping bracket for promoting rocket of preferred aspect, this balloon assembly is used for promoting cable assembly and being arranged in it On part.

Figure 13 is the schematic diagram of the preferably upper part of part of the present invention, and it illustrates a part for cable assembly and is connected to Its different parts.

Figure 13 A is the end-view of bracket, and end cap is on open position.

Figure 13 B is used in the perspective view of the end of the bracket in the device shown in Figure 13, and Figure 13 C is to illustrate some of The lateral partial cross sectional view of the bracket of the operating position of parts.

Figure 14 is the schematic cross section of the preferred embodiments of the invention, and it illustrates cable assembly and is connected to it Different piece.

Figure 14 A is the amplification detail view of the part of carrier end fixture.

Figure 15 is the schematic diagram of the preferred embodiments of the invention, and it illustrates the steady component of balloon and cable assembly.

Figure 15 A is the detailed view of a part for the steady component of the balloon shown in Figure 15.

Figure 15 B is the upper distance piece decomposition diagram to the connection of cable, and Figure 15 C is its plane graph.

Figure 15 D is the enlarged perspective of the cable connection structure of the centre to distance member arm.

Figure 15 E is that lower distance piece is to cable and the decomposition diagram of the connection of big harness.

Figure 16 is the detailed of a part for the steady component of the invention of the preferred form intercepted on direction 16-16 in fig .15 Thin schematic plan view.

Figure 17 is of the steady component of the preferred embodiments of the invention intercepted on direction 17-17 in fig .15 Another detailed view divided, it illustrates some force vector.

Figure 18 is the assisted perspective diagram stablizing assembly of tool according to the preferred embodiments of the invention.

Figure 19 is the perspective view of the cable stabilizing equipment of the preferred form according to the present invention.

Figure 20 A and 20B be the preferred form according to the present invention be connected to many groups of the cable assembly balloons being lighter than air In the side view of two.

Figure 21 is the perspective view according to the Stranded cable in the cableway that can be used on emission system of the preferred form of the present invention.

Figure 22 illustrates the structure of the side for article are installed to cable as shown in figure 21.

Figure 23 and 24 is the cross-sectional view of the deformation of the structure shown in Figure 22.

According to the preferred form of the present invention, Figure 25 illustrates that cable is by for travelling upwards or downwards along described cable The cross-sectional view that the wheel of traction drive engages.

Figure 26 is the perspective view of the contractile arm component according to the preferred embodiments of the invention.

Figure 27 be illustrate according to the preferred embodiments of the invention for rocket is kept collapsible arm within the carrier The details of assembly.

Figure 28 is the schematic diagram of the upper part of the preferred embodiment of rocket launching invention, if telescope is arranged on one Or on the top of multiple main lifting balloon.

Figure 28 A is the perspective view of the upper part of Figure 28.

Figure 28 B is the detailed amplification of a part for the device shown in Figure 28 including gear rotary drive system and collar bearing Details cross-sectional side view, and be intercepted on the direction 28C-28C that Figure 28 C is in Figure 28 B, and generally illustrate that cable can the most eventually Only.

Figure 29 illustrates the possible telescope installed being used in the embodiment shown in Figure 28, and this view is with in detail Perspective view.

Figure 30 is showing of the rocket for launching a people wearing space suit according to the preferred embodiments of the invention It is intended to.

Figure 31 is for multiple independent releasable gondolas or the deformation of the rocket of the people wearing space suit.

Figure 32 is shown in the separable people wearing space suit entered back on framework utilizing the aviation of ignition by shock wave to follow closely.

Figure 33 illustrates separable another deformation entering back into framework utilizing the aviation of ignition by shock wave to follow closely.

Figure 34 be for when leaving and enter back into air use according to the preferred embodiments of the invention by occupying The schematic diagram of the space suit that person wears.

Figure 34 A is the details of the space suit helmet shown in Figure 34, and Figure 34 B be the space suit helmet of Figure 34 additionally Details.

Figure 35 illustrates the device of a kind of method of the internal volume changing the space suit shown in Figure 34.

Figure 36 is the detailed view of the people's extremity in a part for the space suit of Figure 34.

Figure 37 and 38 illustrates according to the rocket assembly on the top being arranged on rocket of the preferred embodiments of the invention The space shuttle having the ability of entering back into deforms, the wing having extension, and one has the wing folded to transport in bracket.

What Figure 38 A was used in the preferred embodiments of the invention has the lifting of folding and the lifting main body of control structure The diagram of type space shuttle.

Figure 39 is the satellite of the part according to the preferred embodiments of the invention with discardable pneumatic protection shell Or on rocket the schematic diagram of other payload of carrying.

Figure 40 and 41 is shown as perspective view and the cross-sectional view of the rod of a type of cable that replacement cable wire uses.

Figure 42 shows the view of bracket and turntable.

Detailed description of the invention

With reference to some parts described in greater below, the preferred embodiments of the invention are the most generally described.Typically Parts are generally shown in Fig. 1,1A and 1B.Preferred embodiment is to include the fire of the device for moving armed rocket 18 Arrow emission system 1.Rocket 18 is first in container or rocket transporting equipment such as bracket 20, or will load torr from storage shelf 7 In frame 20.Bracket 20 has the cylindrical longitudinal hole in the continuous pipe in open end 836 (Figure 13,13C), and it arranges and be maintained at suitable When position be used for receiving rocket 18.Bracket 20 is weather-proof, and has the longitudinal axis, and it is the same longitudinal axis of pipe 836.Rocket 18, its parts and may or may not being carried by the suitable conveyance rail on track 3 equipped with the bracket 20 of rocket 18 To storage shelf 7 and to unloading district 5.Crane 48 transports rocket 18 and/or bracket 20, and/or the parts row of rocket 18 respectively Enter or maintain for rocket being sent out the some of emission system 1 crane rail 78 of opposite, narrow.Rocket 18 can have The wing 21 (Fig. 7), and each bracket 20 also has internal support in addition to pipe 836.

Advancing on guide rail 90 on aburton machine 50 direction shown in arrow A in figure ia, guide rail 90 is compared with heavy-duty machine Guide rail 78 is spaced farther from one another out.It is preferentially used for being transported to assemble or refuelling by rocket 18, bracket 20 etc. from storage shelf 7 The aburton machine 50 in cabin 10 includes the lorry 92 for advancing on guide rail 90, and it is horizontal to have a pair on the top of beam 96 On parallel track 97, movably there is wheel guide rail 98 and be connected to take turns the elevator assembly 100 of guide rail 98.It is preferentially used for The crane 48 performing emission system maintenance can also be used for removing rocket 18 and/or bracket 20 etc. from storage shelf 7, and by rocket 18 and/or bracket 20 be transported to assembling/refuelling cabin 10 (generally having multiple assembling cabin 10).Elevator assembly 100 is in arrow B institute Move on track 97 on the direction shown.May or may not be by a kind of mode or another way equipped with the bracket 20 of rocket 18 It is placed in assembling cabin 10.Whole operation is by the suitable control equipment controlling storage tank 120 in local emission control or system Control.

With reference to Figure 1A and 2, lateral transfer equipment 46 transports along the one group of guide rail 17 being arranged in path, underground 14 and 14A Equipped with the bracket 20 of rocket 18, path, underground 14 and 14A is between vertical wall 16.Path 14A (referring also to Fig. 5) leads to also to be had There is the closed-loop path passage 15 of guide rail 17.Lateral transfer equipment 46 moves in the direction indicated by the arrow c.Lateral transfer equipment 46 The bracket 20 with rocket 18 is transported the emitter 119 including lifting assembly 60.With reference to Fig. 8 and 9, lifting assembly 60 includes Upper rotating mechanism 61.Bracket 20 rises above the turntable mechanism 63 on ground.Turntable mechanism 63 includes turret base 122 and capstan head Assembly 123 (Fig. 8,10,11).Turret assembly 123 includes turntable 72, lower guide pipe 124 and two grades of guide frames 125, Hou Zheyou Effect it is connected to one group of electric power and conveying one-level cable 27.

One-level cable 27 is the electric energy supplier of the bracket 20 loading rocket of transport on it.Electric energy can be by one group of conduction electricity Cable provides, and bracket 20 can be by second group of firm handling cable conveying.But, electric lines of force and rocket pipeline integrally combine Becoming one group of electric power and conveying one of one-level cable, described cable plays electric energy carrier and supports rocket (the most within the carrier with will Described bracket be transported to High aititude or from High aititude carry described bracket) effect.One-level cable 27 has to guide at two grades to be tied At structure 125 or turntable mechanism 63 or neighbouring end portion and upper part at High aititude when in use.Described electricity Power and conveying one-level cable 27 are the most quantitatively 3, are used for transmitting three-phase power.With reference to Fig. 1,1B, 11,12,13 and 14, one-level cable 27 is connected to Docking station 166, and one group of two grades of cable 184 extends from this Docking station.Cable 184 guides effectively Enhancing ring assembly 182, the azimuth firing angle being once pre-selected is conditioned, the elevated ring assemblies of bracket 20 182 and Docking station 166 Upper ring section part 172 engage, enhancing ring assembly 182 is just adjusted to the suitable height on Docking station 166.Elevated and with Apex ring portion 172 is disengaged from and after carrier end fixture 196 discharges, and enhancing ring assembly 182 is adjusted to be pre-selected Launching elevation.Enhancing ring assembly 182 is positioned on Docking station 166, and the last stage in the transmitting of rocket 18 is positioned at At sizable height.

Cable 27,184 and other cable any are supported to upper atmosphere by a series of balloons 164 and 160 being lighter than air, The crust of the gas that balloon is lighter than air by holding forms.The described balloon 164 of air that is lighter than is off and on along described one-level electricity The length of cable 27 is connected to described one-level cable 27, to support the one-level cable 27 of described group cumulatively and by described one-level cable The own wt of the 27 any structures transported.Balloon 160 supports the part not supported of cable 27 and is connected to it Any structure and from Docking station 166 until described balloon 160 include all structures and the assembly of Docking station 166 and be subject to Draw cable 27 and 184 so that they can transport useful load.Cable 27 by one group of distance piece or anti-roll bar assembly 158 that This separates.(cable is shown as wirerope in major part describes, but they can be such as rod explained later on).

The rocket 18 of each assembling in bracket 20 transports lower guide pipe 124 from assembling cabin 10, subsequently enters two In level guide frame 125, and from there through driving structure to Docking station 166, driving structure can be one group such as Fig. 9 and 9C institute Be built in bracket 20 the one group of traction drive 26 shown.Bracket 20 along advance for one-level cable 27 and have for Obtaining the dynamic drive device of electric power from one-level cable 27 and have dynamic drive device, the own wt of cable 27 is periodically The balloon 164 being lighter than air is offset, and the balloon 160 being lighter than air keeps tension.Balloon 160 and 164 preferably has As Fig. 1,11, the inclined side shown in 20A and 28；Cylindrical sides as shown in fig. 20b can be maybe spherical or also has Other shape.High aititude balloon is known, and is developed continuously and improves.Suitable balloon 160 and 164 should be preferably very Multiple moons and most preferably keep in an application of the invention working in the several years.The balloon arriving air is known, and since Used since nineteen fifty.Bracket 20 is even further improved by applying coatings along two grades of cables 184 and rotates, and then according to as described below Scheduled volume tilts, and hereafter rocket 18 is launched.

The general introduction of the parts of the preferred form providing the present invention described above.Described below is that the present invention is preferred at it More detail discussion in form.

Rocket 18 and respective payload is assembled, load in bracket 20 and if necessary by refuelling, and It is maintained at explosion-proof before transmitting to assemble in cabin 10.Each cabin 10 is positioned under ground surface, and is configured to there is rocket 18 Propellant accidental explosion in the case of limit loss.With reference to Fig. 2 and 11, each cabin 10 has with by suitable reinforcement coagulation The inversion surface of the shape of frustum 12 of the cone that soil material etc. are made, for by upwards it comes with lateral deflection Limit the impact of any such blast.Each cabin 10 is connected to path, closed-loop path 15 by subsurface path 14 and 14A.Road Footpath 14 terminates with the open chute 86 (Fig. 6) tilted, and acclivitous wall 16A (Figure 12) is towards assembling laterally opening of cabin 10 Mouthful.This makes may any cross stream component of blast (structure, set from cabin 10 upward and away from the support means of emission system 1 Standby) and deflect away from personnel.Then turn with about 90 degree to engage with path 14A in path 14.Each cabin 10 can be by rocket 18 are maintained in bracket 20.Each rocket 18 can include short persistent period booster rocket engine, and it is for such speed The degree continuous pipe in its open end 836 (Figure 13 A) injection rocket 18 in bracket 20, even if main rocket engine is misfired, short lasting Time booster rocket engine and rocket 18 also will not fall and damage rocket-firing system 1.Booster rocket engine will Operate in the heat-resisting and pressure restriction of the container being only kept at it, as described below.Each rocket 18 has for by rocket 18 It is driven into one or more sustainers of its desin speed.

Each bracket 20 has the hinge weather end cap at opposite end openings 24 (Fig. 9 C, 13,13A) and its two ends or can The barrier film 30 regained (Fig. 9 C, 13,13A) is with the rocket 18 the protection bracket 20 when bracket 20 is advanced through air from ground. These lids 30 can wave to open the two ends of bracket 20, or barrier film 30 regains to open similarly the two ends of bracket 20, such as Figure 13 A Shown in.Also the side being parallel to bracket 20 in opposite end openings 24 and hinged bidirectional variable spacing propeller 31, makes Obtain them and can rotate to be perpendicular to the position of end by using actuator 29 (Figure 13 B, 13C).In order to upwardly along equal intervals The primary power cable 27 opened is held and draws the purpose of corresponding bracket 20, each bracket 20 to have phase around the periphery of bracket 20 Etc. multiple (Fig. 9 C in spaced apart three traction drives 26 in ground；Discussed in more detail below).Cable 27 and 184 has suitable Local high tensile strength and conductivity, as described below.Traction drive 26 is by aforementioned three equally spaced main electric power Cable 27 provides power, cable 27 to transmit three-phase power, and traction drive 26 extracts its electric power from three-phase power.Traction drive Device 26 is two-way, uses electric power to make bracket 20 increase or produces electric power when being used as backheat brake.Brake in backheat The kinetic energy of the bracket 20 when bracket 20 is lowered by the traction drive 26 of operation in pattern is converted into and feeds back to cable 27 Electricity, the electricity of this recovery can be used for helping the rising of other bracket loaded in adjacent transmission system 1.Traction drive 386 (Figure 28) He 26 (Fig. 9 C) operate in a similar fashion.The inside of bracket 20 is designed to resist heat and be helped by the short persistent period The blast impact that thruster rocket engine causes.End cap or barrier film 30 (being shown specifically in Fig. 9 C and 13A) are maintained at torr Any disadvantageous weather exempted from by rocket 18 in frame 20, and can comprise the gas such as nitrogen of inertia or relative inertness, with suppression From the burning of any reactive explosive of rocket 18 effusion during position is launched in transport to High aititude.The upper end of bracket 20 can have There is the torsion lock socket 32 (Figure 13 A) being similar to segmentation rotation torsion pin socket 154 (Fig. 9) (being discussed below), to receive class Being similar to segmentation and rotate the torsion lock pin 204 (Figure 12 and 13) of twist lock pin 144 (Fig. 9) (also discussed below), it is in standard Lifting bracket 20 during standby rocket launching process, as described below.

Each bracket 20 have the contractile arm in the inside that rocket is firmly held in bracket 20 34 or 35 (Figure 26, 27) so that the center of gravity 36 and 37 (Figure 13) of bracket 20 and rocket 18 is stably positioned in respectively in the centre of bracket 20 that it is heavy The center of power.Small or pneumatic capstan 372 (Figure 27) may be connected to the periphery of rocket and launching period at fire to help prevent CONTACT WITH FRICTION between the inside of arrow and bracket 20, if the thrust vectoring of rocket is not exactly through the center of gravity of rocket. Contractile arm 35 discussed below and relevant part.

With reference to Fig. 3-6, there is rocket 18 and can load the distinct methods in bracket 20.In one form, rocket 18 is initial Flatly assembled, inserted in bracket 20, and be placed on the most in a direction of arrowd on wheel loader 38 (Fig. 3). Bracket 20 is then placed in hydraulic rotary actuator 39, rotator 39 have be arranged between support 41 hydraulically or with other side The rotatable bed of formula 40, is used for by the device of such as hydraulic actuator 43 (or certain other suitable actuator) at pin 42 Rotate.The piston rod of hydraulic actuator 43 is almost fully retracted in cylinder, because bracket 20 has just crossed piston and cylinder.Join Refitting put 44 four angles of bed 40 each in be designed, in order to make the center of gravity of bed 40 and the rotary shaft of pin 42 and with fire The center of gravity of the assembly of arrow 18 and bracket 20 overlaps, thus reduces hydraulic actuator 43 or other rotary apparatus must apply Actuating power.Rocket 18 can be previously placed at axial transport equipment 46 before rotating to vertical direction by hydraulic rotary actuator 39 In the bracket 20 of the horizontal orientation of (or similar transporter)；Or rocket 18 can be placed on by transmission loader 50 and be previously located Assemble in the upright bracket 20 on the cross drive equipment 46 in cabin 10.With reference to Fig. 6, aburton machine 50 or crane 48 can be used In being transported to assemble on the pre-aligned lateral transfer equipment 46 as described below in cabin 10 by empty bracket 20, hereafter, load Rocket 18 is contained in bracket 20 by machine 50 or crane 48.

Laterally Transporting equipment 46 is shown in Fig. 1-6,8,9 and 10.Laterally Transporting equipment 46 along path 14,14A and is led Passage 15 on rail 17 is advanced.Passage 15 is formed on the ground under turntable mechanism 63 (Figure 1A, 8,10,11, be discussed below) The closed-loop path passed, and the lifting assembly 60 being transported to as shown in Figures 2 and 8 from explosion-proof assembling cabin 10 by bracket 20 is (each Bracket 20 is equipped with rocket 18), and also transport empty bracket 20.Each lateral transfer equipment 46 has platform 54 (Fig. 9), and it has use Recess 56 (Fig. 2,4) in the usual triangle of the end receiving bracket 20 so that bracket 20 in stand up position, bracket 20 Outward flange be arranged in recess 56.Showing horizontal Transporting equipment 46, it has for mobile the most defeated on guide rail 17 Send the wheel 58 (Fig. 9) that the independence of equipment 46 can turn to, and also there is suitable steering mechanism so that lateral transfer equipment 46 energy Enough advance along path 14 and 14A and passage 15.Can include that conical dowel pin 142 (Fig. 9 is discussed below) and segmentation rotate to turn round The suitable locking mechanism of twist lock pin 144 (Fig. 9 is discussed below) is arranged to the recess 56 being locked on platform 54 by bracket 20 In.Lateral transfer equipment 46 also has the similar socket as found on the bottom of bracket 20, to receive alignment pin and section rotary Turning and reverse lock pin 144, as described below, for equipment 46 is releasably secured to upper rotating mechanism 61, it is as retouched in early time State is the part of lifting assembly 60 as will be described later.

Along a part for passage 15, a series of rockets 18 and its deformation and other article such as lateral transfer equipment 46, bracket 20 and deformation such as pressurization traveller's bracket and emission system service bracket leave the storage shelf divided by wall 64 in On 7.If rocket 18 does not uses solid fuel, then rocket 18 can deposit period or on shelf 7 preferably in assembling cabin 10 Use propellant such as Liquid-liquid or liquid-solid fuel various combinations and by refuelling, depend on the class of rocket 18 Type.One high specific impact propellant combination is liquid oxygen (LOX) and liquid hydrogen (LH₂), it can leave storage tank 65 and 66 respectively in In, as shown in Figure 5.

This fuel fabrication can produce in the most environmentally friendly mode by using a kind of system, within the system, and one Individual or multiple hydraulic turbine conveying machinery power, thereby increases and it is possible to other hydraulic turbine drives the electromotor 62 being included in electric power facility 468. The hydraulic turbine receives water to divide to generating from the electromotor 62 of coupling with enough pressure and mass velocity from such as river, suitable source Stand power supply, and directly drive compressor, such as the water electrolysis in gas liquefaction factory such as factory 74 and gas liquid beggar factory In find.Electric power from substation 70 can be used for operating the sub-factory of water electrolysis in factory 74, and can be used in factory 74 The gas liquid beggar factory that drives of the hydraulic turbine provide auxiliary power, for liquefaction thus the oxygen (O that produces₂) and hydrogen (H₂), it is also Leave LOX storage tank 65 and LH respectively in₂In storage tank 66, electric power is for all other parts of emission system 1 with needs so Electric power its support device provide energy.The such as nuclear fission of other energy source can be used as alternative scheme, if hydroelectric generation Or shaft horsepower that the hydraulic turbine obtains be not available.Regenerative resource such as underground heat, hydroelectric generation or solar energy are preferred.

As explained in early time, rocket 18 is transported on the ground when being included in bracket 20.Lateral transfer equipment 46 can be along path 14 and 14A and the passage 15 on the parallel orbit 17 (comparing with the guide rail 90 being discussed below) of opposite, narrow Mobile.Deposit the empty bracket 20 on shelf 7 to be illustrated as in figs. 5 and 6 against empty lateral transfer equipment 46.Also figure 5 illustrates Be pressurization traveller's bracket deformation, service bracket aircraft deformation, the bracket that comprises of standby balloon or space tourism person's boat Empty aircraft 76.Be parallel to path 15 straight relative to part extend guide rail 78 and pair of guide rails 90 (being discussed below) (Fig. 5 and 6) for crane 48 and the motion having wheel to transmit loader 50.Empty bracket 20 be shown in along passage 15 move the most defeated Sending on the top of equipment 46, lateral transfer equipment 46 can remove for rebuilding or reloading from passage 15.

Illustrate in greater detail Load System in figure 6.Deposit the complete rocket 18 of each holding of shelf 7 and/or be illustrated as Rocket part 18A, the element portion of rocket 18 of 18B and 18C, and/or space tourism person's space shuttle 76 (Fig. 5) and/or sky Bracket 20 or standby lateral transfer equipment 46.Last rocket 18 can be combined rocket part 18A-18C, but the present invention does not has It is so limited.Having the rocket 18 of corresponding rocket part 18A-18C, to be fed to it by passage 3 (see Fig. 1) corresponding Place, this rocket 18, rocket part etc. may be from the manufacturing facility that the whole world is remote.Bracket 20 and horizontal Transporting equipment 46 also exist Illustrate on shelf 7.Crane 48 can be advanced with building block rocket part 18A-18C in the cabin in depositing shelf 7 on guide rail 78 And subsequently enter one of bracket 20.Crane 48 can also be used for service path 14 and 14A and passage 15.Crane 48 has electricity Cable 49.Crane 48 uses its cable 49 can promote the rocket 18 of assembling with suitable lifting gear, and it is transported to cabin 10 In (left half of Fig. 6) in the preset bracket 20 being inserted on lateral transfer equipment 46 top.Except recited above Beyond other service equipment, in addition it is also necessary to crane 48, it is used for serving guide rail 17,78 and 90 and track 97 (is hereinafter begged for Opinion).When using the crane 48 for carrying rocket 18 it has to be taken care that may tend to shake during carrying because of cable 49 Pendulum, and can be damaged from the rocket of cable 49 suspension.

As explained below, the danger of the accidental explosion of the rocket 18 being constantly present in cabin 10, if the combustion of highly reactive property The combination of material-oxidant is used.In order to protect various structure, equipment and personnel to affect from the blast of such blast, a pair Parallel inverted L-shaped ways 80 (Fig. 6) extends on the opposite edges in cabin 10.Every pair of ways 80 has at arrow Slidably explode on direction shown in E lid 82, and blast lid 82 is before refuelling at the overlapping flanges 84 of ways 80 Lower slider.Blast lid 82 is once positioned under flange 84 and cannot move, even if blast occurs.Even if blast lid 82 is by group Must be subjected to such material that the blast in cabin 10 do not damages during dress, refuelling or other situation make, explode warp Directed away from critical component by chute 86.

Aburton machine 50 shown in Fig. 1 and 6 is to include wide a pair guide rail 90 (guide rail 78 of comparison crane 48 is wide) The part of rocket Load System 88, has the guide rail 92 of wheel for a pair across on guide rail 90.Including beam 96 and the guiding having wheel guide rail 92 Assembly 94 is crossed over wide guide rail 90 and is extended and across on guide rail 92, guide rail 92 moves on wide guide rail 90.Guidance set 94 has Parallel orbit 97 as shown in Figure 7 on the top of beam 96, elevator assembly 100 is crossed over track 97 and is advanced.At track 90 top On whole aburton thermomechanical components 50 be similar to have double crossbeam cranes that the top of end guide rail extends.Parallel guide beam 96 It is fixed to guide rail 92.Have wheel guide rail 98 to cross over such as Fig. 1,1A, the parallel orbit shown in 6 and 7 to move.Transmit loader 50 and include tool Having the elevator assembly 100 as shown in Figure 7 of guiding support device 101 and elevator 102, elevator 102 uses preferably to be used Suitable electromechanical device can move up and down as shown by arrow F in support means 101 of counterweight balance.Transmit and load Machine 50 is by rocket 18 or empty bracket 20 or its deformation or keeps the bracket 20 of various types of rocket 18 or various parts from depositing Shelf 7 remove to assemble cabin 10, horizontal Transporting equipment 46 from assemble cabin 10 by the rocket 18 having added fuel in bracket 20 or its Its bracket deformation transports emitter 119.

With further reference to Fig. 7, it is shown that with somewhat revise the one of the details of the upper part of the aburton machine 50 of form Individual embodiment.As it has been described above, aburton machine 50 has elevator assembly 100, it has the guiding being placed with elevator 102 Support means 101.Showing support means 101, it has the relative extension allowing device 101 to be connected to take turns guide rail 98 103, for crossing track 97 moving lifting thermomechanical components 100 on the top of beam 96.In order to engage the rocket 18 for promoting, rise Fall thermomechanical components 100 has relevant lower limb 105, and wherein minimum of three lower limb is preferred to stability, and lower limb 105 is connected to be fixed to rise The main body 106 of the lower end of fall machine 102, it is allowed to grasp assembly 104 and be reduced to assemble in cabin 10, as indicated by arrow G.Lower limb 105 In guider 110 radially movable relative to the rocket 18 between lower limb 105 (as shown in the arrow H in Fig. 7 A), To adapt to the rocket of different-diameter.Segmentation rotates twist lock pin 111 or is connected to other device of rocket 18 and is positioned at each lower limb The free end of 105, and the upper part of rocket 18 have the segmentation that is equally spaced apart by rotate twist lock pin socket 109 or other Other socket of attachment means, it is for receiving for making rocket 18 can be strongly attached to the corresponding of elevator assembly 100 Torsion lock pin 111.Pin socket 109 is arranged in the leading edge portion 19 of rocket 18, is typically parallel to the longitudinal axis of rocket 18.Pin is inserted Seat 109 can have and is connected to the leading edge portion 19 of rocket 109 but according to inserting from corresponding needed for the passage providing socket 109 The channel covers 113 that seat 109 is removable, the most in use make to provide smooth surface to subtract to rocket 18 when pin socket 109 simultaneously Few when rocket awing time air force towing.

Upper and lower stabilizing arm assembly 114 can be set to be stably held on elevator assembly 100 during laterally advancing Rocket 18, advances along guide rail 90 and track 97 simultaneously.Each arm 116 institute with each arm component 114 of stabilizing arm assembly 114 The hydraulic pressure being connected to or other actuator 115.Arm 116 is rotatable along the path indicated by arrow I.Lug 117 is arranged on often The free end of individual arm 116, for engaging the appropriately configured recess 118 in rocket 18, recess 118 is used for receiving each Lug 117.

As it was previously stated, Fig. 6 illustrates the horizontal Transporting equipment 46 equipped with the bracket 20 keeping rocket 18, it is court in passage 15 Emitter 119 discussed below to move.Another the horizontal Transporting equipment 46 transporting empty bracket 20 is advanced away from emitter 119, Emitter 119 fires a rocket 18 from bracket 20 at High aititude, and bracket 20 moves in passage 15, return to by by again equipped with The unappropriated assembling cabin 10 of rocket 18 or return to provide if necessary the storage shelf 7 of service.

Referring back to Fig. 5, rocket-firing system 1 also includes emitter 119.Local emission control storage tank 120 instructs rocket The operation of emission system 1, or electric energy stream is directed to adjacent emission system 1 or from adjacent emission system 1, from energy source example As electric power facility 468 or other adjacent rocket-firing system 1 guide electric energy stream, and accommodate computer control and monitor system, Utilize from the various measurements placed throughout emission system 1 and the data of imaging device.This is that personnel are generally positioned control Local rocket-firing system 1 also coordinates the transmitting of other member from this group emission system for minimizing the use of energy Occasion.

Lifting assembly 60 is arranged in underground, such as Fig. 2, shown in 8 and 9.Lifting assembly 60 can have elevating mechanism, such as Hydraulic piston rod 68, it is disposed the upper rotary components 61 (Fig. 9) for being rotated by rotating driver 134, shown in arrow J Direction on the bracket 20 equipped with rocket 18 that is contained on lateral transfer equipment 46.The liter being more fully described below with reference to Fig. 8 Fall system 60 includes rod 68, and it has the non-rotary lower bed 135 being fixed to rod 68, and lower bed 135 is mounted to support rotation Turn assembly 61.Upper rotary components 61 is by the top being arranged on non-rotary lower bed 135 (it is not the part of turntable mechanism 63) On rotatable bed 136 (there is workbench portion 141) composition.

With reference now to Fig. 8 and 9,.Piston rod 68 is the part of the piston 67 extended from hydraulic cylinder 69.Hydraulic cylinder 69, work Plug 67 and rod 68 do not rotate.

Aforementioned hydraulic system is not the sole mode of operation elevating mechanism.Mechatronic Systems can form elevating mechanism.

Turning next to Figure 10, it is shown that turntable mechanism 63, it is the ground part of rocket launcher 119, for from Lifting assembly 60 is received the bracket 20 of loading rocket and is that they orientation are with transported.Load the upwards fortune of the bracket 20 of rocket Move and illustrated by arrow L.As it has been described above, turntable mechanism 63 includes turret base 122 and brick tower assembly 123.Turret base 122 connects To ground.

Turntable 72 may be the heaviest, several tons of weight, and should can be supported such heavy duty structure and support, to stand Live to promote and cross force, and smoothly rotate.The details of turret supports equipment suitable shown in Fig. 8 A.

Fig. 8 A illustrates turret base 122, and it has for by the horizontal surface 270 of wheel 284 engagement, upright tubular portion 272 and the outward extending horizontal annular flange in neighboring 274 towards turret base 122.Turntable 72 has the week at turntable 72 The tubular portion 276 downwardly extended at boundary, has the horizontal loops extended internally of multiple wheel shaft clamper 280,281 and 282 Shape flange 278 extends from this circumference, and wheel shaft clamper 280,281 and 282 is respectively towards wheel engaged with base 270, upright tube Points 272 and horizontal annular flange 274 extend.Each wheel shaft clamper 280,281 and 282 keeps wheel 284,286 and 288 respectively Wheel shaft.Wheel 284,286 and 288 is across wheel engaged with base 270, upright tubular portion 272 and the surface of horizontal annular flange 274 On, to realize in fig. 8 by the steady circular rotating of the turntable 72 shown in arrow K.Alternatively, with reference to Fig. 8 B, turret base 122 Can have horizontal bearing base 290, upright tubular portion 291 and horizontal annular flange 292.Equally, turntable 72 can be alternatively There is the tubular portion 293 downwardly extended and the horizontal annular flange 294 extended internally.One group of bearing ball or the cylinder of intersection 295 horizontal annular flange 294 and bearing base 290 and horizontal annular flange 292 each between, and suitable annular shaft If concave groove 296 will be used for the friction with reduction compared with being not provided with bearing to realize the rotation of turntable 72.

The turntable 72 of size based on bracket 20 can be diametrically about 46 feet.Such as, if being used for accommodating fire The inner tubular portion of the bracket 20 of arrow 18 has the radius of 8 feet, and the minimum thickness of the bracket 20 of holding rocket is 2 feet, position Being 3 feet in the gap of Zhong Yang bracket 20, the diameter of turntable 72 will be about 46 feet.This figure 42 illustrates:

If R=8'

Δ=2'

δ=3'

A=R+ Δ=8'+2'=10'

In Δ AOB

OB=2a=20'

AB=a (√ 3)=10 √ 3=17.32'

Bracket side ≈ 2AB=34.64'

OC=OB+BC=20'+3'=23'

The diameter of ∴ turntable is at least ≈ 2 (OC)=46'

For the suitable diameter within the turntable of the bracket 20 of the rocket 18 for accommodating 16 feet, bracket inside diameter adds Suitable (Δ=2 foot) gap of the structure of bracket 20 and make mechanism allow tolerance (δ=3 English of 3 feet that turntable 72 rotates Chi), the diameter of turntable 72 is about 46 feet, and the planar side 22 of bracket 20 is about 34.6 feet.

Brick tower assembly 123 is positioned at ground level, on bed 136 (Fig. 8), and is supported by turret base 122 and retrains.Brick The vertical rotating shaft of tower assembly 123 overlaps with the axle of lifting assembly 60.Lower guide pipe 124 is had for being worn by lifting assembly 60 Crossing aperture 73 and receive the aperture 71 of the bracket 20 loading rocket from horizontal Transporting equipment 46, as shown in Figure 10, aperture 73 is through turning Platform 72 and turret base 122 extend.Turntable bed 136 (Fig. 8,9) has a conical dowel pin 142 and segmentation reverses lock pin 144 with will Lateral transfer equipment 46 with bracket 20 is releasably locked to bed 136.Bracket 20 uses alignment pin 142 and segmentation twist lock Pin 144 is locked in the way of being similar to lateral transfer equipment 46 releasedly.The bracket 20 so locked releasedly can Driven, as explained further below.

Referring still to Fig. 8 and 10, brick tower assembly 123 also includes the phase on the direction shown in arrow K mentioned in early time Turntable 72 rotatable for turret base 122, having the fork 126 of pair of parallel spaced apart arm 127, arm 127 is at turntable On 72 pivotable.Guide pipe 124 (being also the part of brick tower assembly 123) under arranging between described arm 127.A pair level Coaxial trunnion 128 extends through each arm 127 and enters down in the opposite wall of guide pipe 124, and is arranged through a pair support Component 129.Inner carriage guider 133 extends along the inner cylindrical wall of lower guide pipe 124, and is spaced apart from each other 120 °, for making the one group of angle recess 130 (Fig. 9) extended in a longitudinal direction along the corner edge of bracket 20 enter.Angle is recessed Enter portion and comprise traction drive 26.Lower guide pipe 124 and two grades of guide frames 125 exist by means of suitable rotary drive system Pivoted around the same level axle limited by pin 128 on path by rotating shown in the arrow M in Fig. 8.Each arm 127 wraps Include counter weight device 131 described below.The central point of lower guide pipe 124 be arranged vertically within brick tower assembly 123 turntable 72 it On so that each rotating shaft direct cross ground in turntable and lower guide pipe 124 intersects.The vertical rotating shaft of turntable 72 is come down to a lower group with liter Part 60 and any lateral transfer equipment 46 overlap with the axle being positioned at bracket 20 thereon.

Two grades of guide frames 125 have integral tube 143, and it is maintained at from the public fulcrum with lower guide pipe 124 own At fixed range.Therefore, two grades of guide frames 125 are balanced around its horizontal pivot, and have the inside torr in integral tube Frame guider 138.Can align with the upper end of lower guide pipe 124 in the lower end of the inner tube 143 of two grades of guide frames 125, institute It is coaxial with pipe, and inner carriage guider 133 and 138 also aligns.Lower guide pipe 124 can revolve around coaxial trunnion 128 Turn, and rotate, until the block 132 (Figure 10) that its outer surface engagement extends from integral tube 330 so that bracket guider 133 and 138 alignment.Bracket guider 133 is provided power (following institute with 138 in the way of identical with power cable 27 State) so that the traction drive 26 in bracket 20 may utilize electric power.The upper end of the pipe of two grades of guide frames 125 has one The inner transition junction point of level cable 27, to allow bracket 20 to move to one-level cable 27 from inner carriage guider 138.

As in figure 2 it is shown, walk crosswise conveying equipment 46, each bracket 20 equipped with holding rocket 18, along passage 15 from assembling Cabin 10 is moved.Bracket 20 with rocket 18 is removed from passage 15, is transported to rocket launcher 119, and is launched at rocket Afterwards, empty bracket 20 returns to empty laterally Transporting equipment 46 continuing on before passage 15 advances, return to assemble cabin 10 or Storage shelf 7.

Forwarding Fig. 8-10 to, lifting assembly 60 rises (on illustrating by making piston 67 and rod 68 on the direction shown in arrow N Rise and descent direction) make bracket 20 rise or fall along with the lateral transfer equipment 46 being fixed to turntable bed 136, with by bracket In 20 spaces moving to lower guide pipe 124 and turntable 72.Turntable bed 136 has described below for being releasably connected to Lateral transfer equipment 46 is so that the suitable inner carriage guider of traction drive 26 and lower guide pipe 124 of bracket 20 133 structures alignd exactly.

Illustrate in greater detail lifting assembly 60, horizontal Transporting equipment 46 and bracket 20 in figs. 8 and 9.Hydraulic piston 67 exists Its upper end has the upper rotary components 61 being made up of non-rotary lower bed 135, turntable top bed 136 and workbench portion 141. Lateral transfer equipment 46 can advance to position on lifting assembly 60, the center.As mentioned in early time, guide rail 17 is possible must Must be wider than conventional railway guide rail.The most tapered alignment pin 142 (illustrating four) (being illustrated in detail in figure 9 a) is from work Platform part 141 extends, and segmentation reverses lock pin 144 (illustrating four) (being illustrated in detail in figures 9 b and 9) the most so.Explained later with These interconnection of lateral transfer equipment 46.Certainly, corresponding pin 142 and 144 and the position of corresponding socket can be the most defeated Send in equipment 46 and part 141 and invert.

The upper rotary components 61 of lifting assembly 60 is arranged on rod 68, and can rising as shown by arrows, to allow Fig. 9 Shown inferior pyramidal alignment pin 142 and segmentation rotate twist lock pin 144 and are engaged to the corresponding alignment pin of lateral transfer equipment 46 In socket 152 and torsion pin socket 154.

The upper surface of lateral transfer equipment 46 has upwardly extending conical dowel pin and section rotary is shipped and resell on another market, its substantially with It is identical that the inferior pyramidal alignment pin 142 extended from the top of workbench portion 141 rotates twist lock pin 144 with segmentation.Corresponding fixed Position pin socket 155 and twist lock socket 153 are arranged in the lower surface of bracket 20 to be received in the taper on the top of equipment 46 Alignment pin and section rotary are shipped and resell on another market, thus releasedly bracket 20 are connected to lateral transfer equipment 46.

Lateral transfer equipment 46 has four wheels 58, and it is positioned and is formed profile with across electric track or guide rail 17 On, including the guide rail 17 adjacent with workbench portion 141, and can align independently as should be mentioned that in early time.The most defeated Send equipment 46 can from electric track 17 in the way of similar with electric train or electric car (it may be necessarily connected to power supply) or from Certain other vehicle power such as fuel cell or internal combustion engine are powered.

Lower guide pipe 124 has the inner carriage guider 133 (Fig. 8,10) of bracket 20, and it extends to along side 22 Vertical cross section extend each angle recess 130 in, be also shown in expanded form (Figure 10), to engage each bracket The traction drive 26 of 20 moves each bracket 20 along bracket guider 133, and is maintained in the direction of bracket 20 In guide pipe 124.Bracket traction drive 26 is arranged to catch primary power cable 27.Bracket traction drive 26 is to have Partially around longitudinal mechanism of the cross section of one-level cable 27, bracket 20 is across on one-level cable 27, and they are from one-level electricity Cable 27 obtains electric power.Traction drive 26 can include Engine-Generator and have several tooth to relative cylindrical wheel 26A Roller box, each 26A of wheel has the annular groove 137 for receiving cable 27, as shown in figure 25.Wheel 26A is such as arrow O₁And O₂Institute Rotate on the rightabout shown.Traction drive 26 positions along the length of bracket 20.Can recessed at traction drive 26 Groove arranges suitable groove or rough surface or suitable surface is modified, actually press from both sides this of corresponding cable 27 with enhancing Friction to traction drive wheel 26A a bit.Electric motor will rotate corresponding this and several traction drive be taken turns 26A.Electromotor can connect Receive gear-box, and output shaft is rotatable is more than a pair traction drive wheel 26A.Can also be effectively connected to individually to lead Draw the independent electromotor of driving wheel 26A.This is heavily dependent on the load being transported and the size of bracket 20.

Traction drive 26 promotes bracket 20 along cable 27 or guider 133 and 138 (Figure 10).When each bracket 20 in backward direction by gravitational force urges time, traction drive 26 returns to cable.The generation of this electric power causes gravity Retroaction, and make the motion delay of sky bracket 20 when empty bracket 20 moves in a downward direction, such as the transmitting at rocket 18 Certain time afterwards occurs.Each traction drive 26 can have minimum a pair relative wheel 26A, as shown in figure 25. Traction drive electromotor should be constant-torque electromotor or have variable frequency type, beats with compensating cable tension or wheel Sliding, equally promote and maintain the barycenter of bracket and cable 27 or lower guide pipe to make when driving up bracket 20 often to organize to take turns The inner carriage guider 138 of the inner carriage guider 133 of 124 or the integral tube 330 of two grades of guide frames 125 is same Axle.

As mentioned in early time, have according to the rocket launcher 119 of the present invention and torr is raised and lowered for vertically Frame 20 is to engage or out-of-gear lifting assembly 60 with the lower guide pipe 124 on the turntable 72 being arranged on turntable mechanism 63.Horizontal May move relative to workbench portion 141 to conveying equipment 46, in order to segmentation rotates twist lock pin 144 and can be received within the most defeated Send in the torsion pin socket 154 in the bottom of equipment 46.The bed one section that workbench 141 is lifted out guide rail 17 by lifting assembly 60 is short Distance with engage lateral transfer equipment 46 bottom.The workbench 141 wheel 58 at it and whole quilts of workbench portion 141 Then be locked into when being lifted on guide rail 17 on the bottom of lateral transfer equipment 46, therefore workbench portion 141 by means of Rotating driver 134 rotates along with horizontal Transporting equipment 46 and bracket 20 mounted thereto, so that bracket traction drive 26 align with the inner carriage guider 133 in lower guide pipe 124, and inner carriage guider 133 rotates freely through or such as Fruit is necessary, rotates to maintain the wind with change to align along with brick tower assembly 123 with the help of electric power.This guarantee under In guide pipe 124, bracket 20 aligns with necessary the stablizing of the rocket 18 remained at.

With reference to Fig. 1,10 and 11, rocket-firing system 1 includes one group of one-level cable 27, and it is each other by distance piece or regulator Assembly 158 separates.Spacer element 158 is shown specifically in Figure 10 A and includes being formed three side workpiece 159 of triangle and hang down Directly the plane in described triangle is used for engaging arm or the flange 161 of corresponding cable 27.Flange 161 or side workpiece 159 or two Person is made from a material that be electrically non-conductive.Cable 27 can transmit electric power, as described below, lightweight, and has high-tensile.Figure 10 A Shown in the preferred structure of spacer element 158 and deployment way.From the extension of each cable 27 is adaptability adapter 501 (each adaptability adapter is similar to adaptability adapter 247 discussed below).Between adaptability adapter 501 is to separate Every arranging along each one-level cable 27, adapter 501 aligns along corresponding cable 27.Each adaptability adapter 501 has Having the flange 503 of the parallel alignment separated a pair, it (but is generally radially not exactly radially, because they are clamped The staple for electric wire extended from corresponding cable 27) adjacent to corresponding cable 27.Flange 503 is each has pair of holes post 505,506, Each hole post 505,506 alignment on every pair of flange 503.Closest to the hole post 506 of corresponding cable 27 relative to adaptation Property adapter 247 is connected to cable 27, as explained later on.One group of lug (not shown) through corresponding alignment hole 505 with And also have the hole of alignment on corresponding orthogonal flange 161 to extend, it is connected to each angle by corresponding spacer element 158 Corresponding one-level cable 27.Each arm 159 of corresponding spacer element 158 has extension between adjacent one-level cable 27 Preferably with the firm and amplifier section 520 of tubular structure of opposing distortion, it has shoulder or conical surface 522 with side Help prevention cable 27 motion relative to each other, and produce the lateral clearance between spacer element 158 and each cable 27. Arm 159 have for be connected to each other with the small end part 524 of corresponding orthogonal arm 161.Spacer element 158 can have respectively Plant configuration；Spacer element 158 is shown to have square cross section, but circular cross section is also advantageous.Spacer element 158 Can each be overall, bend to that it is triangular shaped and slide in three one-level cables 27, or arm 159 can be arranged on cable It was welded together before or after on 27.Arm 159 is preferably welded to spacer element 158, although it is possible that bolt connects 's.

At the uppermost part of rocket-firing system 1 be one group of tension balloon being lighter than air 160 (Fig. 1,1B, 12-14), and exist along cable 27 location for offsetting the own wt of cable 27 and somewhat contributing to other of its tension It is lighter than the tension balloon 164 (Fig. 1,1B, 11,15,17,18,21) of air.Balloon is strained in order to support one-level cable 27 and other 164, the moiety by weight of all parts on Docking station 166 (FIG. 13 below discussion) (includes with the rocket 18 preparing flight The Operating Weight of bracket 20) purpose, balloon 160 be connected to strain balloon connect framework or the big harness in top 162 (Figure 12- Shown in 14).Balloon 160 and 164 must adapt to carry owing to any of motion of bracket 20 and content and other parts Rise fluctuation and reagency.Due to daily heat and atmospheric pressure change, there is change when promoting from tension balloon 160 and 164.Need The lifting wanting additional quantity makes one-level cable 27 be tightened to a sizable part for its safe working load, because cable 27 Must keep the most practically close to vertical.As mentioned, can be less than the balloon 160 being lighter than air one or more groups Extra be lighter than air balloon 164 or 164A (Fig. 1,11,15,16,17,20A, 20B) must along cable 27 spread with Margin of safety alleviate the own wt of cable 27 and the supporting construction of one-level cable 27 and the weight of spacer element 158 and Daily heat promotes change, and to prevent the cable failure under own wt, net effect is that to have the cable 27 of relevant balloon near Like for there is no weight or there is the cable of loading weight.One-level cable 27 engaged by winch discussed below or hoist(-se) 168 or There is provided electric power to winch or hoist(-se) 168, and form the cableway path 170 shown in Figure 11 and 13.Cableway path 170 is by one-level Cable 27 is formed and surrounds, and bracket 20 engages one-level cable 27 and obtains electric power from one-level cable 27, so it can be along cable 27 advance.Tension balloon connect framework 162 by the upper ring 145 reversely rotated around swivel bearing 149 and lower ring 146 (Figure 13- 14) composition.Upper ring 145 and lower ring 146 are driven by gear rotary drive system 177, and are described below.

Docking station 166 is shown in Figure 13 and 14.Docking station has the apex ring portion that can divide 174 rotations relative to lower ring portion 172, part 172 and 174 engages with collar bearing 176, is driven (for rotating driving accordingly by gear rotary drive system 147 System 379, is also shown in Figure 28), wheel rotary drive system 147 includes reagency propeller 178 and is helped by reagency propeller 178 Help.Gear rotary drive system 177 and 147 is also used for providing ring 145 to connect the lower ring of framework 162 relative to tension balloon The phase despining of 146, and the apex ring portion 172 of Docking station above-mentioned 166 and lower ring portion divide the phase despining of 174.Draw The rotary drive system 177 and 147 that tight balloon connects framework 162 and Docking station 166 is the most coordinated, in order at apex ring portion All parts (including apex ring portion 172 and lower ring 146) between 172 and lower ring 146 rotate, phase together with a unit The cable closed is prevented from and is around wound around each other.In the lower end of bracket 20 is maintained at the apex ring portion 172 of Docking station 166 and torr When frame 20 rotates on optimum orientation for being launched, power propeller 178 and 148 resists wind-induced rotation or the rotation from bracket 20 Change the line of production raw rotation.Docking station 166 has two groups three inner carriage guider 180A, 180B (Figure 13,14), its be used for into The radial direction recess 130 entering each bracket 20 correctly aligns with the corresponding bracket 20 of holding and stablizes, and draws to bracket simultaneously Driving means 26 provides electric power.

Referring still to Figure 13 and 14, it is shown that enhancing ring assembly 182.Enhancing ring assembly 182 includes having triangle or can The short tubular ring 183 of cross section that can be circular, and guided and be electrically connected to two grades of cables 184, two grades of cables by two grades of cables 184 184 upwards extend to connect to strain balloon from the apex ring portion 172 of Docking station 166 connects the lower ring 146 of framework 162.Three grades Cable 186 (Figure 13,14) upwards extends to the framework of lower hoist(-se) 198 from enhancing ring assembly 182.Enhancing ring assembly 182 is by even The two grades of cables 184 receiving Docking station 166 guide and obtain electric power from two grades of cables 184.Enhancing ring assembly 182 is by being connected to down Three grades of cables 186 of hoist(-se) load-carrying frame 200 support, and lower hoist(-se) load-carrying frame 200 is the framework of lower hoist(-se) 198.With reference to figure 14A, carrier end fixture 196 is provided with one group of four aperture 195 and pair of apertures 197, and two grades of cables 184 are through aperture 195 certainly Passed through by ground, three grades of cables 186 through aperture 197 freely through.The electric power of carrier end fixture 196 can be by two grades of cables 184 There is provided.

Tubulose enhancing ring 183 has one group of direction features extended internally or inner carriage guider 188, and it is nibbled It is combined in bracket 20 in corresponding three recess 130 of longitudinal extension, for maintaining the bracket 20 of tubulose enhancing ring 183 Orientation also provides electric power to bracket 20.Enhancing ring assembly 182 includes tubulose enhancing ring 183, itself includes a pair relative trunnion 190 and the bracket rotary components 189 of rotary drive system 194, enhancing ring guider 192 and bivector traction driving means 193. Rotary drive system 194 Rotational Coronary enhancing ring 183, tubulose enhancing ring 183 turns around the trunnion axis rotor limited by pin 190 Dynamic.The center of gravity making tubulose enhancing ring 183 falls in its geometric center, and this geometric center overlaps with the axle of pin 190.Tubulose carries Rise ring 183 and there is clamping or locking mechanism to allow it to be releasably connected to bracket 20 so that the center of gravity 36 of bracket 20 It is maintained on the axle of pin 190.The rotary shaft making bidirectional variable spacing propeller 31 is parallel to the trunnion axis limited by pin 190.Three Level cable 186 is connected respectively to corresponding enhancing ring guider 192.Three grades of cables 186 are arranged on the electricity of two groups of regular lengths In cable, and separately 180 ° be connected to lower hoist(-se) load-carrying frame 200, guide dress load-carrying frame 200 being connected to following enhancing ring Put 192 and help the motion of guide bracket end fixture 196 (being discussed below), and transmitting electric power if necessary.

Enhancing ring assembly 182 includes that rotary drive system 194 is to change the tubulose enhancing ring indicated by arrow P (Figure 13) 183 and the bracket 20 that thus keeps relative to the elevation angle of cable 184 and 186.Carrier end fixture 196 is the most in figures 12,13 and 14 Illustrate.Carrier end fixture 196 can be by being connected to be arranged on the lower hoist(-se) of the lower hoist(-se) 198 on lower hoist(-se) load-carrying frame 200 Cable 201 supports.Lower hoist(-se) cable 201 side indicated by arrow Q in fig. 14 moves up.Carrier end fixture 196 is in fortune Disorder of internal organs is guided by the two grades of cables 184 transmitting electric power, and is supported by three grades of cables 186.Carrier end fixture 196 can be by locking Pin 204 is releasably locked to the top of bracket 20, and stop pin 204 is assisted with the pin locking receptacles 32 in the upper part of bracket 20 Make.When carrier end fixture 196 is rigidly connected to bracket 20, carrier end fixture 196 can promote from Docking station 166 or help Lifting bracket 20 is also upward through enhancing ring assembly 182, until when enhancing ring assembly 182 is declined to become the upper ring with Docking station 166 When part 172 contacts, the horizontal pivot of the enhancing ring assembly 182 that the center of gravity 36 of bracket 20 is limited with pin 190 overlaps.Draw Lead the motion of end fixture 196 cable 186 length must long enough to separate with bracket 20 and elevated one when end breaket 196 Section short distance and depart from conjugative component 166 when engaging allow bracket 20 around trunnion axis rotate.

Lower hoist(-se) 198 lower end to lower hoist(-se) load-carrying frame 200 fixed as described above, and moving also as described above For promoting or help the traction drive 26 of bracket 20 when bracket 20 is to engage with tubulose enhancing ring 183 or to be disengaged from. Lower hoist(-se) load-carrying frame 200 as shown in the arrow R on hoist(-se) cable 202 from being connected to Figure 12, the tension gas shown in 13 and 14 Ball connects framework 162 and is raised and lowered.Electric power provides hoist(-se) 168 by two grades of cables 184.Three-phase current or direct current can For powering to hoist(-se) 168.In as directed three-phase current system, from left to right it is further identified as cable 184A (Figure 14) these four two grades of cables 184 of group are the first phases in three-phase, and cable 184B is the second phase in three-phase, cable 184C It is the third phase in three-phase, and 184D can be used as electrical neutral axis or the duplicate as the first phase in three-phase.Also as time earlier Waiting description, the balloon 160 being lighter than air supports the upper member of rocket-firing system 1, and provides holding one-level cable 27 He The pulling force of required a large portion strained by two grades of cables 184, in order to make them strain, even if there being service load.As Figure 12, Shown in 13 and 14, tension balloon connect framework 162 be arranged in be lighter than air or tension balloon 160 under.

With reference to Fig. 1,1B, 11,15,16,17,20A and 20B, these illustrate own wt for alleviating cable 27 Much organize the less balloon 164 or 164A being lighter than air, and related support structure and spacer element are illustrated.Balloon 164 is taper, and balloon 164A is cylindrical, although other shape and configuration are possible, and fall at the model of the present invention In enclosing.Have tension balloon clamper 208 multiple big harness 206 in each by distance piece or anti-roll bar assembly under three limits 210 are connected to one-level cable 27.Each lower spacer element 210 being constructed with distance piece 158 as described earlier and The identical mode disposed is constructed and is connected to one-level cable 27.Balloon 164 or 164A be connected respectively to balloon clamper or Junction point 208 (Figure 18).Lower spacer element 210 has three arms forming the equilateral triangle such as seen in plan view 211, arm 211 is parallel to the respective arms 222 of big harness 206.Lower spacer element 210 has the corresponding cross section at arm 211 The attachment structure 214 at place, wire 215 extends from it.Each wire 215 from spacer element 210 extends, and is used for being connected to The corresponding balloon clamper 208 of big harness 206.It is also equipped with multiple upper distance piece or anti-roll bar assembly 216, itself and distance piece group Part 210 equally separates one-level cable 27 and further cable rope 218 and 219 is maintained at suitable place.Upper spacer element It is constructed and disposes as spacer element 158 and lower spacer element 210.Each upper regulator 216 has at plane graph In form three arms 217 of equilateral triangle together, arm 217 is parallel to corresponding arm 222.Cable connector 220 is accordingly The cross part office of arm 217.Several cable connectors 220 stable rope 218 being connected at one end at the opposite end of arm 217, And clamper 221 is fastened the midpoint at the arm 222 being parallel to corresponding arm 217.Another group cable conductor 219 is connected to rope even Connect between device 220 gentle ball chuck holder 208.This is arranged and helps to be stably maintained on suitable position harness 206.Harness 206 along one-level cable 27 length cycles be installed together with balloon 164 and 164A respectively, with compensating cable 27 with appoint The own wt of the structure what is connected, and cause the tension in cable upright to assist in keeping them.

As follows for connecting the specific components of the various parts of upper distance piece 216.Upper spacer element 216 and be connected to it Parts shown in Figure 15 A, 15B and 15C.As it has been described above, upper distance piece 216 is by three arms forming equilateral triangle 217 compositions.With reference to Figure 15 B and 15C, cable connector 220 includes having center arm 904 and with center arm 904 separately more than 90 ° The base plate 902 of two arms 906 and 908 at angle.Cable connector 220 also has the support section the most relative with arm 904 910.Base plate 902 is the most smooth, and be perpendicular to its extend be cable flange connector 912, it is along support section 910 Middle part extend.A pair arm support lugn 914 and 916 also vertically extend from base plate 902 and with cable flange connector 912 isogonism Ground is spaced apart.Arm 904,906 and 908 is respectively provided with the lug receiving opening vertically extended through corresponding arm 904,906 and 908 920,918 and 922.It is spaced apart convex that cable flange connector 912 has the series of equivalent ground that the height along flange 912 extends Ear receiving opening 924.

Each cable has at least one and more likely a lot of attachment structures 925, each attachment structure 925 by several to parallel , relative spaced apart flange receive flange connector 926,927 composition, flange 926,927 is parallel to the corresponding axle of cable 27. Flange 926 has a post of the parallel alignment of lug receiving opening 928 and 930, lug receiving opening 928 and 930 with at another flange 927 On respective aperture 928,930 alignment.For the position that each cable connector 220 is connected on corresponding cable 27, cable Flange connector 912 is inserted between the flange receiving flange connector 927,927 with the hole 924 alignd with each corresponding hole 928. A pair lug 932 inserts between the hole 928 and 924 of corresponding alignment, and is connected to nut or other fastener receivers 933. In order to corresponding cable connector 220 is connected to corresponding cable 27 further, similar lug 256 as shown in figure 22 is used for Clamp the ring 244 of cable 27.Flange receives flange connector 926,927 to be sufficiently close to each other have traction drive 26 Bracket 20 through with the complete operation of corresponding cable 27 engage flange 926 and 927 time make traction drive 26 to nibble Close corresponding cable 27.

As mentioned in early time, several a pair arm that cable connector 220 is connected to by stable rope 218 big harness 206 The corresponding midpoint of 222.Each stably rope 218 at one end has connection fork 934, and it is flat that it has a pair of hole 938 with alignment Row flange 936, lug 940 extends through hole 938, and lug 940 is used for being connect by nut or other securing member subsequently also through hole 908 Receiver 942 is received, so that stable rope 218 is connected to cable connector 220.Similarly, cable rope 219 has coupling fork 944, its There is the pair of parallel flange 946 in the hole 948 with a pair alignment.Arm 904 is inserted between flange 946, and lug 950 is inserted in hole In 948 and 920 and enter in nut or other fastener receivers 952.

Figure 15 E illustrates that lower spacer element 210 (Figure 15) is connected to cable 27 and big harness 206 by attachment structure 214 Details.This is fixed to cable 27 to attachment structure 925 by engagement ring 244.Attachment structure 925 is made up of vertical flanges 960, Vertical flanges 960 has the flange connector 962 extended from it and includes string lug hole 963.One group of arm support lugn 966 is from it The vertical flanges 960 that is soldered to by suitable welding process extend, and respectively by suitable welding or other process even Receive the respective arms 217 of lower spacer element.Arm support lugn 966 at an angle to each other, and engages corresponding arm 217 with them Local angled to provide firm support member in structure.Flange connector 962 is placed on to have and aligns with hole 928 (see Figure 15 B) Hole and lug 932 attachment structure 925 parallel flanges between, and through flange connector 962 corresponding alignment hole with And hole 928 and inserting attachment structure to be fixed to cable 27 through nut or other fastener receivers 933 (see Figure 15 A).

Vertical flanges 960 has finger portion 968, and hole extends through this finger portion 968.For by lower spacer element The end of the 210 each wires 215 being connected to big harness 206 has the coupling fork 972 being made up of parallel flanges 974,976, right Neat lug receiving opening 978 extends through flange 974,976.Fork 972 moves so that finger portion 968 is inserted in flange 974 He Between 976, align in hole 970 and 978.Lug 980 inserts and enters nut or other fastener receivers through hole 970 and 978 In 982.

Mentioning in early time, stably rope 218 is connected to the midpoint of arm 222.Show in Figure 15 D for completing this device Go out.Rope flange connector 984 is connected to the midpoint of each arm 222 and extends from the midpoint of each arm 222.Flange 984 has two Galianconism 986, each galianconism 986 has lug receiving opening 988.Each rope 218 has connection fork 944, and it has as above Flange 946.Fork 944 from each rope 218 slides on the suitable arm 986 of flange 984, and lug is inserted through hole 948 and 988 Enter and use securing member such as nut to fasten in position.

For connecting each structure in harness, distance piece and regulator preferably by parts and the sub-portion of same type Part forms.Such structure is firm, stable, easily manufacture and enforcement.

On substantially identical with spacer element 210 multiple three limits, distance piece or anti-roll bar assembly 260 are positioned at big harness On 206 (as shown in figure 18).The detailed configuration of spacer element 260 and it how to be connected to one-level cable 27 substantially and Spacer element 158 is identical with lower spacer element 210.Several to even at three pairs of arms 264 of spacer element 260 as shown in figure 18 The cross part office of the arm connect is connected to cable 27 by attachment structure 262, and these arms 264 form equilateral triangle.One group light The cable 266 (comparing with relatively heavy cable 27) of weight extends to balloon clamper 208 from attachment structure 262, and it is constructed Become and they are remained to big harness 206.The cable 266 of weight amount is during the assembling of emission system or in the maintenance of balloon 164 Period supports big harness 206.

One group three electric reverse effect propellers 800 are connected to turntable in the cross part office of corresponding arm 222 respectively and prop up Support point 802, as shown in Figures 18 and 19.Each propeller 800 includes that fan 804, each fan are arranged in blower-casting 806. Each housing 806 is rotationally mounted between a pair arm 808.Each arm 808 has the coaxial trunnion extending in housing 806 809, make each housing 806 can be around axle S-S clockwise and rotating counterclockwise on the direction of arrow T.Arm 808 is therefrom Center arm 810 bifurcated, center arm 810 is connected to turret supports abutment 802 as above.Propeller 800 is solid with gimbal Fixed electric plating propulsion.Propeller 800 is pivotable and rotatable, and operation keeps on demand relative to vertically The emission system 1 of line orientation.Propeller 800 compensates wind-force and the part of any balloon 164 or always exits, until they can be by more Change or be otherwise maintained.Big harness 206 is controlled by position sensor 812 relative to the position of the base of emission system 1, Position sensor 812 could be for providing the complete of position reference data to the computer in the direction and power that control propeller 800 Ball alignment system (GPS).

Be presented herein below about Figure 15,16,17,18, the explanation of situation of 20A and 20B explanation, wherein (it will be suitable for balloon 164 In balloon 164A) it is connected to one-level cable 27.Spacer element 260 is together with being positioned on upper regulator 216 shown in Figure 18 The cable 266 of weight amount is omitted to understand in fig .15.Look first at Figure 15, it is shown that a part for one-level cable 27, Lower regulator 210 and upper regulator 216 are arranged to make harness 206 stable.(only one of which is at Figure 15 for three balloons 164 In be shown in solid lines) be arranged to offset cable 27, various regulator and be applied to cable 27 any extra load from heavy sensation of the body Amount.Balloon 164 may need the tubulose separator being made up of the material identical with balloon according to its diameter, and uses identical light Gas in air is inflated.In order to prevent cable 27 from contacting balloon 164 (or balloon 164A), fixing belt or sideband 227 (figure 15A) it is arranged to that balloon 164 is connected to cable separating part and such as goes up spacer element 260 (Figure 18), to prevent such connecing Touch.Each fixing belt 227 is the part of regulator 228, and regulator 228 is phase in the way of being connected to cable 27 with other regulator Same mode is connected to each cable 27.Regulator 228 also has for being held in position in by corresponding fixing belt 227 Connecting elements 229.The mode that foregoing teachings completes can be seen in detail in figure 16, and Figure 16 is direction in fig .15 The top view of the upper intercepting of 16-16.It can be seen that, each regulator 228 is connected in three cross sections of regulator 228 Level cable 27.Regulator 228 is made up of three corresponding arms 234, and these three arm 234 common across is to form equilateral triangle. From each connecting elements 229, a pair fixing belt 227 shape is at an angle so that accordingly to contacting corresponding balloon 164, firm Band 227 is almost tangent with balloon 164.Carried for 227 each connections by tangent band 224 be connected to balloon 164.Band connects 224 to be prevented Cable 27 contacts balloon 164 (or balloon 164A).Band connect 224 (Figure 15) can be the most suitable binding agent, Plastic Welding Or use the stitching of sufficiently tight line, for fixing belt 227 being connected to corresponding balloon 164 (or balloon 164A).

Figure 17 is shown at balloon clamper 208 three balloons 164 being connected to big harness 206.Show regulator Assembly 216, it has the stable cable rope 218 of the rope clamp holder 221 being connected on arm 222.Figure 17 illustrates along tension Force vector FF that cable 219 extends, it is shown that extend to the pulling force of balloon clamper 208 from cable connector 220.

The side view of connection system shown in Figure 20 A and 20B.Each balloon 164 (Figure 20 A) and 164A (Figure 20 B) tool There is light, the firm tension base connector 232 of the balloon clamper 208 being connected to big harness 206.One or more connections Device 232 can be tubulose with by replace the gas being lighter than air be sent in each balloon 164 compensate leakage.Balloon 164 and 164A is the balloon being lighter than air, so pulling force FF is illustrated by the arrow along adapter 232.Adapter 232 is with each The crust of balloon 164 and 164A is tangent.Showing one group of three or more adapter or regulator 228 (Figure 16), it is used for Corresponding balloon at several points is linked together.

As explained in early time, tension balloon connects framework 162 and has upper rotative portion 145 and lower rotating part 146 (Figure 13,14), it connects on the vertical axis by collar bearing 149, for reducing the friction from rotary motion, such as Figure 12 institute Show.Reaction propulsion device 148 is tangentially connected to the periphery of upper rotative portion 145.Similarly, reaction propulsion device 178 Example is connected to the periphery of the lower part 174 of Docking station 166.The propulsion unit being arranged on upper rotative portion 145 and be arranged on portion Those unit on 174 are divided to be used for maintaining them not rotate.Propulsion unit combination gear in upper part 145 rotates drivetrain System 177 helps the rotation relative to upper rotative portion 145 of the lower rotating part 146.Similarly, the propelling in upper part 174 Unit combination gear rotary drive system 147 (Figure 13,14) helps the rotation of upper rotative portion 172.It is gathered into the two of two groups Level cable 184 (separately 180 °) relative to one another is connected on lower rotating part 146.Upper hoist(-se) 168 is connected to lower rotating part Divide 146.Balloon is connected framework 162 and is connected to Docking station 166 (Figure 13,14) by cable 184, and transmits electric power on demand.Cable 184 also guide lower hoist(-se) load-carrying frame 200, carrier end fixture 196 and the motion of enhancing ring assembly 182.Cable 184 long enough with Owing to lower hoist(-se) load-carrying frame 200 and allowing safely to accelerate downwards at the local acceleration of the gravity of its article hung Degree period long enough so that when rocket 18 is in the rising gap freely falling condition and bracket 20 with its limiter disconnection.Right In subtracting of the remainder of lower hoist(-se) load-carrying frame 200 and all items (including that load and empty bracket 20) of hanging from it Speed, it is also desirable to one section of extra cable 184 is to allow extra a period of time.One section of extra cable will allow to load completely The deceleration of bracket 20 is to stop in the case of misfiring at short persistent period booster.

As explained above and further described below, need the dress for the article of system 1 being fixed to various cable Put.Figure 21 illustrates the cable 240 being made up of several strands of electric wires 242.Per share the 242 of cable 240 can have the main body from cable 27 The ring male portion of outer surface extension or ring 244, be used for securing objects to cable 27, keep most of outer surface of cable simultaneously Without hindrance.Each ring 244 extends from the main body of each cable 27, and returns in the main body of cable 27.Such as, adaptability is even Connect device 247 figure 22 illustrates, as discussed in detail below.Adaptability adapter 247 has prominent flange 248, its tool Having a series of bolts hole 249 and another series of bolt holes 250 extended through pair of parallel wall 252, wall 252 is abreast from public affairs Base 253 extends altogether.Adaptability adapter 247 can be pushed to cable 27, and ring 244 is right with hole 250 with theirs in parallel walls 252 Slide between neat corresponding annular distance 254.Bolt 256 may pass through annular distance 254 and bolt hole 250 extends with by adaptability adapter 247 are fixed to cable 27, and nut can be placed on corresponding bolt 256 to realize firm connection.Top view shown in Figure 23 Figure.Alternatively, the parallel walls 255 separated by the distance piece 259 as optional adaptability adapter 257 can be used, such as Figure 24 Top view shown in.Cable 27 can be caught by a pair traction drive 26A of bracket 20 as shown in figure 25, and this is to leading Draw driving means 26A at contrary direction O₁And O₂Upper rotation.

In order to use rocket-firing system 1 described till now, rocket 18 is contained in respectively at device as shown in Figure 5 In bracket 20 in one of, and lateral transfer equipment 46 is used to be carried along passage 15.Lateral transfer equipment 46 uses accordingly Conical dowel pin 142 and segmentation rotates twist lock pin 144 and corresponding co-positioned pin socket 152 thereof and segmentation rotates and reverses Latch receptacles 154 is fixed to lifting assembly 60, as explained about Fig. 9.Two grades of cables 184 and one-level cable 27 pass through respectively Tension balloon 160 and balloon 164 are kept tension, and balloon 164 promotes the tension in one-level cable 27.Following cable tension warp Connected framework 162 by tension balloon to be transmitted, and electrical cables separate and further tension are via big harness 206, distance piece 158 and Distance piece 228 (Figure 11,15 and 18) realizes.

Each bracket 20 is rotated into and aligns with inner carriage guider 133 and load in lower guide pipe 124 (Fig. 8).Under The upper part of guide pipe 124 is then inclined to engage with the lower part of two grades of guide frames 125 (Figure 10), until lower guide pipe 124 engagement link stoppers 132 are to align with bracket guider 133 and 138, as discussed in early time.Traction drive 26 connects For driving bracket 20 to enter in its upper part 172 and partially into carrying through Docking station 166 up along cable 27 Rising in ring assemblies 182, enhancing ring assembly 182 makes for reducing by hoist(-se) 168 so that enhancing ring assembly 182 with dock The upper part 172 of (Figure 13,14) engages to stand 166.End fixture 196 is lowered and is correctly connected to the upper end of bracket 20.By from Cable 27 transmit the electric current in two grades of cables 184 provide power lower hoist(-se) 198 lifting bracket 20 with further with carry Rise ring assemblies 182 to engage so that the center of gravity of the combination of enhancing ring assembly 182, bracket 20 and rocket 18 and enhancing ring assembly The pivot of 182 overlaps.Therefore lower hoist(-se) 198 helps traction drive 26, and it is being lifted up torr relative to Docking station 166 Inner carriage guider 180A and 180B is engaged during frame 20.Then carrier end fixture 196 makes stop pin 204 depart from bracket 20 Lock socket 32, and promoted the most without barrier by the use of lower hoist(-se) 198.Enhancing ring assembly 182 is by two Level cable 184 guides and is supported by three grades of cables 186.The further lifting bracket 20 of hoist(-se) 168, until the lower end of bracket 20 is not Again in the lower part 174 of Docking station 166, and only in upper part 172.Gear in lower Docking station 166 rotates drivetrain System 147 is present in a coordinated fashion collar bearing 176 He with the gear rotary drive system 177 with tension balloon framework 162 Rotate to all parts between 149 to be suitable for fire a rocket 18 direction on.Propeller 148 and 178 operates to prevent simultaneously The lower part 174 of Docking station 166 and tension balloon connect the upper part 145 of framework 162 and rotate (Figure 14).

(rocket 18 of bracket 20 holding must to be disengaged from Docking station 166 completely for hoist(-se) 168 then lifting bracket 20 Must be elevated more and more higher according to the weight of a combination thereof) and enter short tubular ring 183 with to the secure transmission of rocket 18 In Zhong Bu required the highest.Rotary drive system 194 and the bidirectional variable spacing propeller 31 extending 90 ° coordinate to come relative to The short tubular ring 183 with bracket 20 is rotated into suitable angle by the horizontal line being suitable for launching.Bidirectional variable spacing propeller 31 are adapted to assist in rotary drive system 194 and prevent bracket 20 from swinging around the trunnion axis through pin 190.When bracket 20 is in use Time at the expectation elevation angle launched, stable bidirectional variable spacing propeller 31 further rotates to avoid and heat around its hinge Rocket gas contacts.

Deformation is possible, to help rotary drive system 194.This bracket 20 being included in enhancing ring assembly 182 Location and stabilisation, and particularly prevent bracket 20 around the swing of trunnion 190.With reference to Figure 13 B-13C, can be the two of bracket 20 Bidirectional variable spacing propeller 31 and a pair subsidiary wheel shaft generator 822 are set at end.Each propeller 31 and wheel shaft start Machine 822 can be placed in one end of the bracket 20 under end cap 830.Each propeller 31 has to be installed at the two ends of bracket 20 One group of rotatable blade 826 in pivotable propeller base 828.Each base 828 is arranged on hinge component On 829, and by hydraulic actuator 832 in resting position (illustrating with dotted line in Figure 13 C) and parallel with the longitudinal axis of bracket 20 Moving position (being shown in solid in Figure 13 C) between removable, hydraulic actuator 832 rotates around actuator pivot 834. When propeller 31 is on its moving position, air-flow produces as shown in arrow U.This prevents the swing of bracket 20.Wheel shaft generator 822 is two-way, because air-flow can flow in the two directions.Equally, the spacing of blade 826 is variable, with along with surrounding The change of air and change, in this surrounding air, blade 826 is rotated.But, when the engine ignition of rocket 18, advance Device 31 can moving with obtuse angle as shown in the dotted line at the left-hand part of Figure 13 C, with avoid booster exhaust during Short circuit.The upper end of propeller 31 also is moved into its position, obtuse angle so that rocket 18 can load in bracket 20.It should be noted that bracket 20 Inside have opposing continuous print pressure and heat pipe 836, its end-to-end extension is to comprise rocket 18 wherein.One group three or More centering support members 840 maintain the centering of each bidirectional variable spacing propeller 31.

The upper end of hoist(-se) cable 202 (Figure 14) is fed out from upper hoist(-se) 168, and the two-way of enhancing ring assembly 182 is led Draw driving means 193 to start to travel downwards, operatively engage with two grades of cables 184 simultaneously.Hoist(-se) cable 202 unclamps and moves What enhancing ring assembly 182, bracket 20, rocket 18 and cable 202 were supported downward is helped to overcome friction and empty by driver 193 Other parts all of atmidometer so that they are in in the free-falling of the acceleration of 1g, and rocket 18 is relative to bracket 20 become zero gravity.There is the slight friction maintained in upper hoist(-se) 168 to maintain the control freely falling period, and avoid Cable 202 any lax and any unsteered untie.Before freely falling, the collapsible end cap of bracket 20 30 (Fig. 9, 9C, 13,13A) open (or the end cap 830 shown in Figure 13 C open).Within the bracket 20 that rocket 18 is maintained in bracket 20 Collapsible arm 34 or 35 (Figure 26) is retracted (as described below), and the short persistent period booster rocket engine of rocket 18 is ignited So that rocket 18 is driven out bracket 20.Short persistent period booster rocket engine is only in the heat resistanceheat resistant and pressure limit of bracket 20 Operation, to prevent the damage to emission system 1.

Enough remote on rocket 18 ground of advancing on its trajectory path, its sustainer can be lighted a fire on demand safely, with Avoid the damage to emission system 1.When the bivector traction driving means 193 of enhancing ring assembly 182 (Figure 13) is in braking mode Operation is to prevent bracket 20, lower hoist(-se) load-carrying frame 200, carrier end fixture 196 and enhancing ring assembly 182 (Figure 12,13,14) Further during free-falling, cable 202 tapers off from the feeding of upper hoist(-se) 168 (Figure 12).Bidirectional variable spacing propeller 31 (Figure 13 C) can be then used in before they are retracted to the end of bracket 20 and help bracket 20 to rotate on upright position, and Can be used for releasing from the inside of described bracket any waste gas before closing weather lid 30.

The short tubular ring 183 rotating to the enhancing ring assembly 182 with sky bracket 20 on upright position (prepares around hanging down D-axis rotates, because inertial rotation square is minimum when bracket 20 is on upright position) then pass through with shown in Figure 13 and 14 right Go to the station to meet somebody 166 upper part 172 engagement upper hoist(-se) 168 and reduce.Before bracket 20 reduces into and engages with upper part 172 such as The most extra support or guiding are required, and bracket 20 and carrier end fixture 196 can then be brought together after locking bracket 20 To carrier end fixture 196.The lower end of bracket 20 then reduces engages with the upper part 172 with Docking station 166.Tension balloon connects The lower part 146 (Figure 14) of framework 162 and the upper part 172 of Docking station 166 then rotate so that enhancing ring assembly 182 (figure 13,14) inner carriage guider 188 and the inner carriage guider 180 of upper part 172 start and Docking station 166 (figure 13) cable 27 aligns.Carrier end fixture 196 is then reduced to enhancing ring assembly 182 (Figure 12,13,14) by hoist(-se) 168 Top, and discharge bracket 20.Enhancing ring assembly 182 also departs from bracket 20.

Bracket 20 uses backheat braking to travel along the cableway path 170 (Figure 11) formed by one-level cable 27, holding in the palm The downward velocity of frame 20 remains to manageable level.The electric power quilt of one-level cable 27 is returned in this and other transmitting station It is sent to another emission system to supplement or to replace another bracket 20 to lift required electric power up along its cableway path 170. One group of active emission system of minimum of four is conceived to have serve as such as travels for light responsibility or the preparation of High aititude parachute jumping Good standby, the 5th active emission system utilizing special light weight cradle, until active transmitter needs to safeguard or Higher clean rocket launcher speed is required.Combination emissivity the most once is considered as feasible.

After empty bracket 20 enters back into two grades of guide frames 125 (Figure 1A, 2,8,10 and 11), it reduces further, directly Depart to bracket 20 from two grades of guide frames 125 and in the center of gravity of bracket 20 and the combination of lower guide pipe 124 and lower guiding The point that the rotary shaft of pipe 124 overlaps is in lower guide pipe 124 and becomes to be in center.Lower guide pipe 124 then returns to vertically Position, and bracket 20 drops on the horizontal Transporting equipment 46 of the suitably alignment on lifting assembly 60 top.Lateral transfer sets Empty bracket 20 is returned to the explosion-proof for reloading by standby 46 to be assembled cabin 10 or is used for changing and the storage shelf 7 of trimming. The rocket 18 of another pre-assembly, bracket 20 and horizontal Transporting equipment 46 can load in system 1, and next rocket 18 is described above It is launched.

One possible structure of collapsible arm is for being maintained in bracket 20 in the direction of arrowv by rocket 18 Collapsible arm 34, as shown in figure 26.Rocket 18 have at least six for receiving collapsible arm 34 equally spaced can Regulation slit 300, has an arm 34 to each slit 300.

Referring next to Figure 27, it is possible to provide optional different collapsible arms 35.Each collapsible arm 35 has for entering narrow The overhead 302 of one of groove 300 and bottom member 304, relative coaxial trunnion 306 extends from bottom member 304.Bar 308 Interconnect with overhead 302 and bottom member 304, and net or the support 310 strengthened prolong between bottom member 304 and bar 308 Stretch.Bracket 20 has the inside antiknock bombing 312 with chamber 314.Pipe 312 has a pair protection door being arranged on hinge 318 316, it may be positioned to close the part (as indicated by arrow W) in chamber 314 and be pivoted out opening the portion in chamber 314 Point, as shown in figure 27.Pipe 312 also has the end door 320 covering chamber.Door 320 can have for protecting door 316,320 and chamber 314 Flow diverter 322, strengthen ridge strain component 324 and keep the pin clamper 326 of coaxial trunnion 328, it is used for making pivot In the general lateral of the sidewall 332 that socket 331 enters the part defining chamber 314.Door 320 is between the open and closed positions at pin Pivot on 328.Wall 332 also has the pivot socket 334 of the pin 306 for receiving collapsible arm 35.

The hydraulic pressure of socket 338 that chamber lid door 320 also has for being moveable into and out being positioned in the arm 340 of door 320 is collapsible Pin 336 and the hole in bottom member 304 339.Door 320 also has the parallel arms 342 in the hole 344 with alignment.Collapsible The bar 308 of arm 35 has upstanding portion 346, and it has the slit 348 of longitudinal extension in bar 308.Part 346 lower limb 342 it Between extend, and sliding pin 350 extends through slit 348 and enters in each hole 344 so that collapsible arm 308 is coupled to chamber Gai Men 320.Hydraulic arm 352 has lower limb 254, and it has for being in the current alignment of pair of leg 362 at the bottom plate 364 in chamber 314 Hole 360, lower limb 362 has the hole 366 of alignment, and lower limb 354 is held in position in by pin 356, and pin 356 is through hole 360 Extend with 366.The most pair of parallel lower limb 368 extends from axle 369, and axle 369 generally extends forward from arm 352, and a pair alignment Pin 371 is received in hole 370.Door 316 is opened and closed by the hydraulic pressure coordinated with door 320 or electromechanical device.

The door 316 and 320 that aforementioned arrangement pinning is displayed on open position in figure 27, and each collapsible arm 35 Overhead 302 is retained in the respective slots 300 in socket 18.Freely fall and relative to torr along with bracket 20 when rocket 18 When frame 20 becomes zero gravity, arm 35 and the remainder fast retractile of assembly that operates together with arm 35 are to its corresponding chamber In 314, and door 316 and 320 was closed just before the igniting of the booster rocket engine of rocket 18.The most true at thrust line Cut coaxial with the inner tube of bracket 20 or in the case of being not passed through the mass centre of rocket, each rocket 18 can have group Wheel 372 is to keep rocket 18 at the center of pipe 312 during launching.

In addition to firing a rocket, if telescope is thus lifted to the top of unit, it be also possible to use another change of the present invention Shape.With reference to Figure 28 and 28A, it is shown that telescope keeps system 373.Figure 28 A illustrates balloon 160 in simplified form.Beg for below The parts that opinion is relevant with telescope.System 1 has transmission electric power and is connected to three one-level cables 27 of Docking station 374.Docking Standing and 374 have upper part 376, it uses rotatable drive system 379 on the direction relative to the arrow X of lower part 378 Rotatable.With reference to Figure 28 B and 28C, rotatable drive system 147 is by having the ring of the component 852 that cross section is inversed l-shaped Bearing 850 makes upper part 376 and lower part 378 relative to each other rotate, and array ball bearing 854 and 856 is respectively in upper part 376 With in the guide rail 857,858 and 859,860 in l-shaped member 852 and lower part 378 and l-shaped member 852.

The upper end of cable 27 is firmly held as shown.One cable 27A is through opening 862 He in lower part 378 Extend with an angle for firmly holding the suitable clamping device 864 of cable 27A.Second in cable 27 is illustrated as cable 27B, and it is securely held to flange 866 by suitable device, as further shown in Figure 28 C.In cable 27 3rd is firmly held similarly.Electromotor 868 swing pinion 870.Gear 870 is continuously attached to upper part 376 Tooth 872, to realize the aforementioned rotation as shown in arrow Y.Protective housing can surround electromotor 868 and gear 870.

Three or more retroaction propellers 380 can be used, and they offset rotating against of part 390 and 378, when When the standby emission system described in Figure 28 is used for firing a rocket, part 390 and 378 keeps static.It is similar to other Docking station, Collar bearing 377 and rotary drive system 147 are included between the upper part 376 of Docking station 374 and lower part 378.Two grades of electricity Cable 184 also transmits the electric power for operating electrical components.It can be paired cable flow directing device or four cable three-phase installations.

Enhancing ring 382 in direction shown by arrow Z on cable 184 to or travel downwards.Enhancing ring 382 includes two-way Traction drive 386 and for keep bracket 20 can on the direction indicated by arrow AA pivotally supported structure 387, And rotating driver 381 is to change enhancing ring 382 and the angle of bracket 20.Upper Docking station 388 have generally remain static Upper part 390 and use rotating driver 381 around the rotatable lower part of vertical axis 392 on the direction shown in arrow BB. Collar bearing 394 reduces the friction from such rotation.Upper part 390 offset by one group of minimum of three reaction propulsion device 397 Trend with around vertical axis rotate.

Special brackets 398 can be transported to top saddle 399, each bracket 398 by firm elevator shaft or elevator pipe 396 There is built-in telescope CC.Special one or more light weight cradle 20A can also be used for after shifting from enhancing ring 382 Up along elevator pipe 396, bracket 20 is transported to saddle 399.One group of electricity transmission cable or track may be installed elevator pipe On the inside of 396, the engageable elevator pipe 396 of bracket 398 or 20A, and also can receive electric power (as engaged the traction of cable 27 The wheel of driving means 26 completes) so that bracket 20A can be carried up and down in elevator pipe 396 inside.Balloon 160 are connected to or around elevator pipe 396 as described earlier, to provide enough pulling force to realize carrying to cable 184 Liter ring 382 is along with the conveying of the special brackets 398 maintaining telescope CC, and supports cable itself and be connected to the dress of cable Put.

Telescope top saddle 399 includes turret-like platform 402, it is arranged and rotates relative to static upper part 390 Rotatable turntable 404.Telescope receiving opening 405 extends through the platform 402 as shown in Figure 28 A and 29 and turntable 404.Peace Dress wall 406 extends from turntable 404.Telescope keeps structure or ring 408 to clamp the special brackets 398 equipped with telescope CC, bracket In the minds of the center of gravity of 398 is arranged in ring 408, ring 408 works in the way of identical with enhancing ring assembly 182, but does not has There is traction drive.As being shown specifically in Figure 29, it is coaxial that ring 408 has in the socket 412 extending to assembly wall 406 Trunnion 410.Provide the assembly wall 406 of telescope incline structure 411, ring 408 and trunnion 410.Therefore, bracket 398 and installation Telescope CC within it can the most in height tilt, and by the rotation on the azimuth shown in the arrow DD of turntable 404 Guide bracket 398 and the telescope CC included on arbitrary desired direction.Turntable 404 and platform 402 can be made relative to lifting Machine pipe 396 can be independently rotated on the corresponding rightabout shown in arrow HH and II (Figure 28 A, 29).This is rotated through class The rotating driver 383 being similar to driver 381 realizes.Platform 402 can have radially adjustable weight so that its rotation is used to Property square equal to the assembly of turntable 404 and the rotation inertia moment of its part above so that when they rotate in the opposite direction Time, do not have clean moment of torsion to be applied to elevator pipe 396, because turntable 404 and its part above rotate.

Rocket-firing system 1 can be used for various purpose.Such as, it can be used for launching and has turning to and send out as shown in figure 30 Single or the basic rocket 601 of motivation 603, convertible engines 603 being movable to as indicated by arrow EE turns to rocket 601.Showing that dress is full of the people or the passenger GG that launch or enter back into suit 605 of fluid, it is straight that joint 607 is locked in optimum pneumatic It is used for launching on vertical position, and first foot is locked on the top of rocket 601, for opposing shooting of rocket 18 during launching Gravitational effect.After rocket 601 stops operation and the joint of suit is unlocked, suit 605 separates from rocket 601 on demand, Passenger GG is allowed to move freely.If suit will be used for entering back into, a part for the fluid surrounding passenger GG can pass through porous pad It is sucked, to be cooled down the outside entering back into suit 605 by evaporation when entering back into, first cools down foot.(identical suction behaviour Make and cooling effect also will the application when launching.) having of being arranged on top wears the rocket 601 of the passenger GG taking 605 should The visual field that passenger GG offer is good is given during launching phase.Air force damping device around suit 605 is not likely to be to be needed Want, unless when being so configured, and this group joint 607 is locked in position, air force towing is the highest In necessary to optimal transmitting.

Figure 31 illustrates and clips to the traveller in the suit 605 of core rocket 604 or firm gondola releasedly for conveying The possible method of the material in 608.Main rocket 601 stops its in check transmitting one period after it is launched.Core Rocket 604 is releasable from main rocket 601 when the in check transmitting of main rocket 601 stops.Windshield 609 can be used at fire Arrow 601 its to protection suit 605 when penetrating air on the road of space or the traveller in gondola 608 from high-speed air, its Middle suit 605 or gondola 608 can discharge on the direction indicated by arrow JJ.Core rocket 604 can have one group rotatable The wing 602, it is rotated to turn to rocket 601 by heading control loop on the KK of direction.

Figure 32 illustrates that having sled shape enters back into the standby gondola 610 of framework 616.Passenger GG dress is launched or enters back into set Take 605.Sled shape enters back into framework 616 and includes turning to the wing 619 and aviation nail 611.Aviation nail 611 has extendable antenna shape Configuration, antenna-like configuration have as forward direction shock wave indicator disk 613 with produce for the air force reducing suit 605 The shock wave 615 of heating.

In fig. 33, it is shown that enter back into suit 605 equipped with people GG, it is arranged on and has the directional steering wing 618 and boat In the framework 617 more like rocket shape of empty nail 611.Framework 617 has the disk 613 as discussed about Figure 32.Guiding equipment Can be located in afterbody inner frame 617 with storage compartments.

With space suit 605 suitable in Figure 34 and 35 is shown in people GG, space suit 605 is also used for adapting to weight Stress effect.Space suit 605 enables passenger GG to survive, and maintains consciousness, and can be in upright appearance in high acceleration environment Holding activity time in gesture.For the operation of extension, this is about identical with health close by passenger being immersed in firm suit Realizing in the fluid of degree, this firm suit has outside electromechanics or hydraulic pressure, raises the joint that the constant volume of auxiliary put by clothing.Too Empty set take 605 helmets 650 with the head around people GG (Figure 34,34A, 34B, 36) and firm shell 648.Internal suit 651 are positioned against at person of modern times GG, and the inside face shield 653 with vizard 655 is sealed to internal suit 651.Nontoxic fluid 656 (Figure 34,34A-34C, 36) such as water fills the space between firm shell 648 and internal suit 651.If fluid 656 is added Heat is to comfortable temperature, then internal suit 651 can be omitted.Dual-seal 654 is had between internal suit 651 and face shield 653. Internal suit 651 can be closely around the crust of people GG, and face shield 653 can be vented to air via air supply pipe 661 Supply or ventilate from air supply.If there is to the leakage around the space between the dual seals of the face of people GG, leakage Pipeline 652 is arranged on the face shield 653 of space suit 605 for discharging water.Water or other suitable nontoxic fluid 656 are filled such as figure 34, the inside suit 651 shown in 34A and 34B and the space between shell 648 and face shield 653 and vizard 655.At space set Take the people GG in 605 and can rotate his head when being suspended in water 656 in the helmet 650.Space suit 605 has firm Lightweight structure；But, the volume gas streams sensor in face shield 653 or vizard 655 can be set to guide hydraulic pressure or electromechanics Piston (explained later) is driven to be moveable into and out with coupling owing to the change in volume breathed.Additionally, in order to mate breathing rate, also That is, divided by the change in volume of time change, the various location (particularly near chest) in space suit 605 Pressure transducer keeps fluid pressure constant by being directed into and be guided out piston.Allow people GG example in high acceleration environment As launched or entering back into the external high pressure hydraulic power side moved freely through everywhere in suit 605 in the environment of period existence The use helped avoids for making the water of the joint motion of suit or other hydraulic fluid escape into the probability in suit inside, This effusion will be crushed passenger GG.

About piston, referring also to Figure 35.Here, space suit 605 has that to fill the water of the suit around people GG (or big It is approximately the nontoxic fluid of the density of human body) 656, and piston 657 is moveable into and out cylinder 660, it is by high pressure hydraulic fluid or logical Cross electric machine piston 657 directly activate provide power to change the volume in suit 605, required for eupnea 's.

Firm shell 648 typically has the structure of the suit 605 described in Figure 34 and figure 36 illustrates.Suit 605 Firm shell 648 include a pair firm sleeve, each sleeve comprises internal sleeve 664 (only illustrating), the most each in Portion's sleeve 664 is made up of open plastic web or soft open celled foam or net and a pair firm lower limb, and each firm lower limb has The inside leg of the structure identical with internal sleeve 664.Internal sleeve and inside leg will be hereinafter referred to as " internal sleeve ".Kong Ying Sufficiently large, in order to inconspicuous obstruction water is through the flowing of sleeve 664.Sleeve 664 is by being connected at one end to the weak bullet of suit 605 Property tendon 668 is maintained at center in suit 605, and elastic steel bar bundle 668 is crossed over sleeve 664 and extended and be connected to and be tangential on The sleeve 664 that they are connected at the other end.Pulling force in elastic steel bar bundle 668 is detected and for providing feedback to draw Guide pin bushing takes the motion of the power joint reflection passenger GG of 605, the center he being maintained in suit.Passenger GG only slides into suit In 605, and his or her whole health is slided in general sleeve 664.Suit 605 is by rocket 601 or in rocket 18 Reality that people GG wears and effective space suit, particularly flight transmitting, above push away and enter back into the stage during.Other shell 648 can have ablative exterior material, and it has insulation or heat resistanceheat resistant is heat insulation.

Other deformation of rocket is shown in Figure 37,38,38A and 39.Rocket 700 has space shuttle 702, and it has even Receive the main body shown in Figure 37,38 and 38A and folding on the direction shown in arrow LL and MM dispose and fold Promote and direction control structure 704.Promote subject type enter back into aircraft 706 be shown in Figure 38 its fold transmitting join In putting, promote with direction control structure 704 in the folded condition.Have on the other direction indicated by arrow NN folding Promote and direction control structure 704 lifting subject type control enter back into aircraft 706 be shown in Figure 38 A folding and not In the configuration folded.The military deformation of rocket 700 mainly rocket 18.

With reference to Figure 39, it is shown that more generally rocket 720.Rocket 720 includes satellite or other payload 722, its Protected during transmitting and flown by a pair disposable air force shell 724.After rocket 720 leaves air, outward Shell 724 is automatically separated on the direction indicated by arrow PP, and preferably falls back to the earth and satellite, or other payload 722 enter space.The business deformation of rocket 720 mainly rocket 18.

Preferred embodiment described above can use and be currently available that material and product realize.General equipped with rocket Bracket can be estimated attaches most importance to 80 tons, although bigger weight is possible.Each cable must be firmly and to conduct electricity.It should enter One step is wear-resisting, to withstand traction wheel up and down along the traveling of cable.Therefore, cable 27 and 184 can have outside steel, There is aluminum mid portion and steel core.Cable can be to have copper and steel stock and the multiply of copper-plated steel stock or other is suitable Structure.For 70 tons of liftings, cable should diametrically be of about 2/3 inch.Each in three cables has 1.25 inches Diameter, and two grades of cables should each diameter with an inch.

As mentioned in early time, the weight of cable is advantageously periodically offset.Steel cable has 1.125 inches Diameter, every foot nearly weighs greatly 2.03 pounds.At least five safety factors should be used.The cable of one inch diameter keeps at its breakaway poing 120 tons.

Preferred gas for balloon should be hydrogen, and it is more much bigger than helium buoyancy, and can be produced by water, and the limited supply of helium Main from natural gas well digging.But, safety is a key factor.Balloon advances the highest in an atmosphere, and lightning is attacked Danger is increased by.Therefore, rotatable lifting assembly and parts above all should insulate with the earth, are charged to big with High aititude Gas phase electromotive force together is to avoid causing lightning, and power supply connects sensedly.The insulated part of rocket-firing system can be advantageously It is made up of pottery or glass.

The crust of balloon should be light, firm and uvioresistant (UV) light.From nearest dirigible light balloon and other In the design of balloon and operation, enough being operated in such crust is had to complete.

It is phase DANGMING that the rocket-firing system of the present invention is better than the advantage of those rocket-firing systems the most in use Show.The first stage of the Saturn V rocket that NASA is launched is 203,000 US gallons at the period internal consumption of 2.5 minutes RP-1 (kerosene raffinate) and 331,000US gallon liquid oxygen (LOX).The present invention can by before transmission use have equal effectively The least rocket is risen to desired height up along the cable that balloon supports by the motor-driven bracket of load to be come greatly Reduce the quantity making identical payload height highland be raised to aerial propellant.Current techniques state uses huge number of base Energy in expendable Fossil fuel.Such as, for Space Ship Two, Virgin Galactic (Virgin Galactic) White Knight missile carrier uses several tons of JET-A-1 kerosene stocks to arrive its firing altitude, and Space Ship Two makes With the rubber of a kind of form with liquid oxidizer, and produce black coal smoke waste gas.Solid-propellant booster rocket often leave behind fluorine and Partially combusted Hydrocarbon in chlorine compound and other the dangerous residue in its waste gas.All these waste gas and Residue atmosphere pollution.On the other hand, the energy used when lifting bracket in a preferred form of the invention is from renewable energy Source obtains, and the biggest part energy is switched to its regeneration mould at traction drive when bracket is returned downward along cableway It is resumed during formula.

Additionally, the present invention will sufficiently reduce the cost of space flight to allow the track removing around our planet In remains and even allow for the structure in track shipyard.Dangerous example true to nature at space middle orbit remains is in 2008 The Russia Cosmos 2251 of the non-operating that what February 11, Iridium was had have mobile phone satellite based on the U.S. communicates The collision of satellite.Each satellite is advanced with the orbital velocity of per hour 17,500 miles.Remains from this collision are estimated as Amount to 500.NASA declares, these remains carrying out self collision increase the danger of the damage to ISS.Pacify for space The international association of full progress proposes the mandatory of the satellite of non-operating and removes.

Present invention accordingly comprises the one group of cable supported by the balloon being lighter than air, these balloons can be with highly effective and high The mode of effect is for numerous purposes.When being used for firing a rocket, the amount of the fuel required when launching strongly reduces, because rocket Upper atmosphere it was transported to before it is engine-operated.Rocket can be used for various purpose, and due to the energy expenditure reduced and because of And the cost caused reduces, the amusement being so used as to use rocket, parachute, little jet engine or other device may It is economically feasible.Equally, the facility being used for keeping in repair satellite becomes more feasible and economical.High aititude platform is such as looked in the distance Scientist may be highly profitable by the use of mirror.

In preferred embodiment discussed above, provide three cables for three-phase power.Each cable may be definite / 3rd of ground transmission electric power.In the case of this can not complete or exist it can be in the rocket launching system according to the present invention During the use of system in the case of the probability that completes, the structure with the neutral conductor or otherwise ground wire should be provided with at these three electricity The each central of cable obtains necessary power balance.

In addition to those purposes described above, the present invention also has a lot of purposes.Exist from being driven in space A lot of rockets the track around the earth run a large amount of remains.NASA estimated in 2009, had about 14,000 thing Body is by U.S.'s space supervision network trace.A lot of threats in these objects may pass through other of the respective track of these objects Equipment, because collision may cause sizable damage.The present invention can be used for being placed in track remains catcher, for Economic and safety mode is recovered such remains and makes it orbit or recycle such article, as can be at track In useful structure in reuse.

Cable discussed herein is described as having the rope of general type, and it is made up of the torsion stock of metal and is illustrated as turning round Change into spiral type.These are the electric wire ropes of conduction, and are similar on cable car, cable railroad and aircraft elevator use that A bit.Also discuss the different distortion in cable.But, term " cable " is not defined as being limited to electric wire rope.Cable also may be used To be different types of rod, it occurs with single length, by various types of solder joints, or is being coupled to produce In a series of less link of desired length.The key character of whatsoever cable used according to the invention is, it is jail Solid, conduction, and can accept to exist at the height raised for as described herein conveying rocket conveying equipment and The stress of other device and pulling force.These excellent or other type of cables can be modified at different aspects, such as to revise rod Or the surface of other cable or surface configuration so that when the traction drive dress of rod or other cable with corresponding rocket conveying equipment When putting cooperation, system will more effectively and more efficiently operate.Such rod can have cylindrical cross section or other cross section, takes Certainly in the character of the traction drive used the most therewith.With reference to Figure 40 and 41, it is shown that the rod 990 of flange connector 992, convex Edge 992 is connected at junction surface 994.Flange has connecting hole 996.As the distance piece in other structure being connected to the side of rod Required, bolt connects or other connector can be by bonding, solid-state or welding (such as, friction welding, the blast of other form Welding, brazing etc.) or the joint that is deemed appropriate to be connected.Rod can otherwise be revised, and depends on various factors, such as The chain character of corresponding rod, the electric conductivity of rod, the safety etc. of rod.

The present invention is described in detail with particular reference to its preferred embodiment.But, from aforesaid data with from appended right In requirement, those skilled in the art are it is contemplated that changing and modifications within the spirit and scope of the present invention.

Claims (2)

1. by high height or take advantage of the space suit that the passenger in rocket wears, described space suit bag in space Include:

In one group of joint of at least some joint of the passenger wearing described space suit, described group of joint is relative to being used for launching Rocket may be locked on optimum air power position, wherein said passenger wears described space suit and is loaded, and foot arrives first institute State on the top of rocket, for opposing gravitational effect of described rocket during launching.

Space suit the most according to claim 1, also includes unlocking for the stopping in response to the operation of described rocket The structure in described group of joint.