CN1978279A - Efficient flying boat and missile with tail-wing-skirt self-stabilizing return capsule - Google Patents

Abstract

A return cabin with a tail fin and skirt and its spaceship belong to high efficient integration of spaceships and space shuttles, which can change the sizes of airships, its tail fin and skirt is small, thin, light and cheap and deployed in the idle space of a commutation cover, yet its performance and potential is extremely great and can be improved to a sudden-protection missile returning to aerosphere and the antimissile system will lose power.

Description

Efficient flying boat and guided missile with magnetic tape trailer wing tail skirt self-stabilizing recoverable module

The invention belongs to improvement to the recoverable spacecraft and the guided missile of reentrying of many cabin structures.Belong to integration to technology such as parachuting formula spacecraft and space shuttle, guided missile control fins.Title of the present invention can be referred to as the simple and easy space shuttle of magnetic tape trailer wing recoverable module parachuting formula module combinations again.

Divine boat's No. 6 spacecraft safeties Returning ball, the whole nation was a scene of jubilation, and this is the another huge achievement of China's space industry.

The recoverable module of No. 6 spacecrafts of divine boat is very similar to the Muscovite recoverable module that connects alliance's spacecraft, be head big and put down, tail is little and sharp, be campanula halleri Halleri.

In on October 15th, 2005 Xinhua News Agency's news from Beijing, the article that reporter Sun Yanxin, Xu Zhuanzhi deliver " why recoverable module is as individual great bell ", quote explaining of Airship system structure and the subsystem director design engineer Chen Tongxiang of mechanism, this is not in order to make certain section's illusion effect, but its scientific basis is arranged.

" why not does airship make an integral body? fact proved that it is proper to have only three cabin structures to be only.”

When airship returns,, make airship and astronaut be faced with baptism with violent fricative high temperature of atmosphere and overload.The airship safety is returned will be through four roads " danger spot ".In removal process, no matter which road closes not in the past, all might ruin airship, makes the astronaut sacrifice life.”

Flame closes airship and returns the high temperature that can produce several thousand degree Celsius with the violent friction of atmosphere, not protection, and airship will turn to dust and ashes.

Overload is closed when flight enters dense atmosphere at a high speed can produce the huge impact overload, does not mentionlet alone the people and can't stand, airship itself also can be run scattered here and therely.

Although bump closes the descending speed that parachute greatly reduces airship, have only tens meters of per seconds, the astronaut still is unable to bear and lands fanatic in a flash " kissing ".

The ground even if drop point pass airship arrives safe and sound, but the rescue group still can not in time arrive.If airship is fallen remote, thickly forested mountains, crag, bring danger also can for astronaut's life.

" facts of life makes scientist have to select: only return returning ground-surface instrument and equipment, N/R is just stayed and is worked on the track or abandon.The flight of airship needs power, so individual propulsion module must be arranged; The astronaut needs the work life area in space, orbit module must be arranged, and this cabin also can be stayed aerial continuation scientific experimentation in the future.Another benefit of the airship of subdivision section is, increased reliability and safety factor, a cabin et out of order, and also can work in other cabins.

Why recoverable module is as individual great bell

Can reenter atmospheric envelope under the effect of gravity when recoverable module returns, therefore the attitude that air-flow is ever-changing will to make the recoverable module of high-speed flight be difficult to be maintained fixed must make recoverable module the shape of tumbler, and end major part is little, is not afraid of the disturbance of air-flow.When acutely rubbing with atmosphere, can produce the high temperature of thousands of degree at the cabin table, if do not solve the solar heat protection problem, airship will also not wait to land and just burn till ashes as meteor.There is one deck heat shield on the recoverable module surface, is to make with special ablative material, and the solar heat protection principle is exactly by the burning of material heat to be taken away, and finds through scientist's experimental investigation, and the shape of great bell helps realizing anti-thermal target relatively.

And this bell recoverable module to return ground be very complicated, high, the high process of paying a price of hazard level.

" when the Shenzhou series of spacecraft recoverable module begins to return ground; at first brake on 344 kilometers high tracks; just as brake; airship was ninety degree turn in orbit before this; orbit module separates with recoverable module then, orbit module continues to carry out earth observation in orbit, and recoverable module and propulsion module change 90 degree again; just in time opposite jet with original heading, plays the effect of deceleration.At this moment recoverable module begins to break away from original track, carry out unpowered flight, enter atmospheric envelope when flying to 100 kilometers apart from ground, produce so-called " black barrier " phenomenon, this is because airship and atmosphere acutely rub, when the height of 80 kilometers-40 kilometers on distance ground of recoverable modules passes through dense atmosphere with the speed of thousands of metre per second (m/s)s, the recoverable module surface temperature can reach 1000-2000 Celsius degree centigrade, if do not take actv. solar heat protection cooling measure, whole recoverable module will be burnt as aerolite is ashes.At this moment must put on one deck " Heat-preventing clothes " to airship, it is sustainable below 40 degrees centigrade to make the temperature of craft's interior be controlled at the astronaut.”

The cooling of airship recoverable module is mainly by three kinds of methods: the one, and the heat absorption type solar heat protection at some position of recoverable module, adopts good heat conductivity, fusing point height and the big metal heat-absorbing material of heat absorption capacity to absorb a large amount of pneumatic heats; The 2nd, the radiant type solar heat protection with having the titanium alloy and the ceramic and other composite material of radiance, distributes heat radiation; The 3rd, ablative thermal protection utilizes the method heat radiation that High molecular material surface portion material when high temperature heats melts, evaporates, distils or decomposition is vaporized and taken away a large amount of heats.

When " black barrier " phenomenon takes place, around airship, produced a plasma shell, make airship temporarily can't with ground communications.During Deng the height that flies to distance ground 80 kilometers to 20 kilometers, the lift control system of airship begins to work, and airship at this moment is just as aircraft, according to the data of ground input, aim at theoretical landing point, rely on spaceborne put-put constantly to adjust flying height and attitude.When flying apart from ground 40 kilometers the time, at this moment airship " black barrier " district that flies out, waits for that already autogyro for a long time just captures the signal that airship sends rapidly, begins search and rescue action.When airship arrived apart from ground 10 kilometers, airship began to cast aside conopy, and takes two tool pilot-parachutes and a tool deceleration parachute rapidly out of, after 24 seconds, mainly fell umbrella and opened, and made the descending speed of airship reduce to about 10 meters of per seconds.In the time of will falling apart from ground 5 kilometers Deng airship, the big end of the solar heat protection of airship is by jettisoning, waits airship overhead during 1.2 meters left and right sides, and the buffering driving engine begins flame earthward, further slows down, and guarantees the airship safe landing.

Have 52 driving engines on three cabins of airship, wherein propulsion module has 28 driving engines, and 4 big being used to change track, track is kept and return braking, and spacecraft attitude is controlled in little being used to; Recoverable module has 8 driving engines, and getting through the earth's atmosphere in the return course to make the spacecraft attitude shakiness, for realizing precision landing, need carry out attitude control to airship simultaneously; Orbit module has 16, provides power half a year for it stays rail.Each cabin driving engine all is an even number, and main frame and backup machine are wherein all arranged.

When needs changed track or attitude, which platform driving engine computing machine can calculate should be worked and how long work, and the instruction that 52 driving engines on the ship obtain computing machine will automatically perform.The principle of return phase is also basic identical

Said process does not need the astronaut to participate in, if et out of order also has a cover manual control system, form by attitude handle, translation handle, optical sight and manual circuit etc., the astronaut can manually control, though ratio of precision is poor automatically, can drives airship safety fully and return.From divine boat No. to No. six, problem never appearred in " automatic steering " function of airship.

In above process, airship becomes a cabin by three cabins, and recoverable module also must be skimmed at the parachute and the big end; The airship weight loss 2/3rds, by being kept to 8 tons more than two tons more; Can be described as and suffer heavy losses.

" just there is earthshaking problem in this therebetween: at first; the observing and controlling cause that is Chinese airship is too big to the dependence of ocean; do not look far into the distance and measure fleet; airship is almost difficult to move even one step; from natural conditions owing to must send ship, so can only be selected in the summer in the southern hemisphere, the time period (the 2-3 month in October to the coming year) that stormy waves is less to the South Atlantic; shortcoming clearly, this is an one.It is two more fatal, the sea power that we are present, and the ability that does not have the whole world to deliver can be imagined under the emergency state, the space flight strength of China will be limited by the deficiency of marine ability greatly.Countermeasure: need develop the space-based TT﹠C system as early as possible, the satellite of relaying observing and controlling just.Secondly, 100% launching success rate is no doubt gratifying, but says that from higher level this is to bring to sacrifice " efficient ", applied satellite field especially, and the satellite of annual emission at all can't meet requirements, and the batch manufacturing of spacecraft also is difficult to accomplish.”

At last, it is the airship return course, from start to finish, requirement for observing and controlling strength, observing and controlling means is too high, too accurate, even so that time-proved five star space flight measurement and control personnel are controlling state-of-the-art spaceflight TT﹠C system and also can get all up tight, be in fear of to occur least bit mistake in the observing and controlling process that airship returns.It is reported the emission of a lot of rockets, airship " therefore the experiment team member has suffered from " rocket syndrome ": face preceding 3 hours of emission, the beginning dry, even will drink away cold water---in subzero more than 20 winters of spending; Also have the palm of the hand to perspire, do not stop going to toilet; After successful launch, they can embrace mad together crying again and laugh at." consult by " illusory military zhyuli " article that http://military.china.com 2005-10-24 11:04:07 delivers " talking about the self-examination of Shenzhou VI heat ebb after excited ", and other is about article.

The purpose of invention: under the prerequisite of the main contour structures of parts greatly that does not change or change less as far as possible divine boat's series manned spaceship, be based on utilizing the existing volume and the existing structure of airship, particularly utilize recoverable module, orbit module, space between the fairing, afterbody at the recoverable module of manned spaceship is loaded onto empennage or tail skirt, load onto fleetline distortion power consumption head at its head, make this recoverable module enter atmospheric envelope and promote its deceleration performance afterwards significantly, solar heat protection burn-out proof performance, flight self-stabilization function, flight lift and heading operating function, and further the airship structure is fundamentally simplified in exploration on this basis, improve the brand-new approach that returns the safety performance and the ratio of performance to price of airship, and further explore it in the missile-borne purposes of reentrying.

The method of invention: on the appropriate location of the afterbody of the recoverable module of manned spaceship, load onto empennage or tail skirt resistant to elevated temperatures, suitable size; Join to load onto fleetline sheet metal distortion quality or balloon-like power consumption head at its head.

Its further method is the powerful aerobraking energy dissipation capacity based on power consumption empennage, tail skirt, utilize and excavate the included space of tail skirt, enlarge the effective volume of recoverable module significantly, and then make the recoverable module of two floors or multi-storey structure or under the prerequisite that keeps original function, change the structure of three cabin formula spacecrafts into two simpler, lighter and handier, more practical, more cheap, the safer cabin formulas of unique construction or the version of single cabin formula.

Its further method be to utilize the powerful braking energy dissipation capacity that the relative high velocity air of the empennage of pneumatic power consumption, tail skirt produces and new, the safer controlled recoverable module power consumption return route of aerodynamic force handling design or the return method of movable empennage.

Below, with the embodiment shown in Fig. 1 to 5 method of the present invention is further described.

Accompanying drawing 1,2,3 all is elevation profile scheme drawings of recoverable module (1);

Accompanying drawing 4.a is the elevation profile scheme drawing of recoverable module (1); Accompanying drawing 4.b is its schematic top plan view;

Accompanying drawing 5 is the elevation profile scheme drawings that comprise the spacecraft of recoverable module (1), orbit module (3), booster rocket parts (11) arranged side by side.

Wherein: recoverable module (1) propulsion module (2) orbit module (3) empennage (4) tail skirt (5) the head big end (6) distortion power consumption parts (7) air bag (8) dividing plate or floor (9) human body are imported and exported the booster rocket parts (11) of (10) cavity ring tubular or tubular

The recoverable spacecraft that embodiment shown in the accompanying drawing 1 is illustrated, its structure, profile, size, the same substantially with existing divine boat series spacecraft, belong to improvement to it.The head of its recoverable module (1) is put down greatly, tail is little and sharp, be campanula halleri Halleri, its head, tail two ends flexibly connect with propulsion module (2), orbit module (3) respectively, and this recoverable module (1) is afterbody and upwards is installed in the top of firing a rocket when emission, when returning, be head and enter atmospheric envelope downwards; It is characterized in that:

A. the sidewall of this recoverable module (1) afterbody is provided with sheet or ring-type or barrel-contoured empennage in parallel (4) or the tail skirt (5) that adopts the heating resisting metal making with anti-ablative coating or surface layer or is provided with empennage (4) simultaneously and tail skirt (5); The movable empennage that empennage wherein (4) maybe can be controlled for fixing empennage, this empennage (4) can be grid fin or folding wings, the bus length of tail skirt (5) should be suitable, can be simple expansion linear portion or be arbitrarily segment of curve;

B. with respect to movable empennage (4), activity or fixing front wing can be set;

C. the head of this recoverable module (1) can be changed a social system the distortion power consumption nose cone that becomes streamline-shaped with suitable height, suitable sharp degree or the heat-resisting anti-ablation that has suitable height, suitable sharp degree in its of head interpolation.

Illustrate:

In accompanying drawing 1, empennage (4) is made of two parts, the one, the empennage of en plaque, the 2nd, be positioned at peripheral ring-type empennage, the rear end flange of ring-type empennage can be seen tail skirt (5) as, the flange angle of this flange tail skirt can be the right angle, also can be other angle, and the size of flange designs, tests, improves according to the needs of flight stability and brake snub.

Similar structure also has grill-shaped empennage, the ring sail formula empennage (with reference to the fabric parachute that cracks) etc. that cracks greatly; Use the empennage of a kind of pattern in back, can make its performance be similar to the function of resistant to elevated temperatures miniature parachute.

Empennage in accompanying drawing 1 (4) and tail skirt (5) are to consider to make them not influence opening of parachute not to the rearmost end setting; When specific design empennage (4) and tail skirt (5), should coordinate with the Change In Design of parachute compartment.

Head, the afterbody that should be noted that recoverable module (1) is to return heading in the surface process and fixed according to it; At rocket launching and airship in the process of the earth, the working direction of recoverable module (1) be afterbody preceding, head after.

Because after among the reentry, can and produce overload with the violent frictional heating of air, recoverable module (1) has to take three cabin structures, so that alleviate himself weight to greatest extent, its surface is its head particularly, have to adopt the refractory metal manufacturing, and take to be coated with failure-free solar heat protection measures such as anti-ablation coating, the big end of the droppable solar heat protection of installation.

After the sidewall of recoverable module (1) afterbody is provided with and adopts sheet that heating resisting metal with anti-ablative coating or surface layer makes or ring-type or grid-like empennage (4) or tail skirt (5), can share, alleviate the surface thermal load and the overload load of recoverable module (1) significantly, improve it and return safety, flight stability, flight can be handling.

The tubular empennage is meant the cylindrical body arranged side by side with recoverable module as the cluster carrier rocket, has a certain amount of space in its tube.

Sheet empennage and ring-type empennage also can make its thickening hollow, make its inside have a certain amount of space.The tubular empennage can also be provided with booster rocket driving engine or escape rocket motor as hereinafter described therein.

But design the time it should be noted that laminal empennage be the simplest, the lightest, the most cheap, the most firm, help high temperature resistant, the anti-ablation most.

With respect to empennage (4), activity or fixing preceding fin are set, be in order to increase the lift of recoverable module head, make its in atmospheric envelope, fly stable more, more balance, have more handling.Preceding fin should design smallerly as far as possible, weak point.

In accompanying drawing 1, the outer end of the empennage on the recoverable module (1) is equipped with the ring wing, and the flange on this ring wing also can inwardly turn over, and the effect of this flange is equivalent to a little tail skirt when turning up.

Being further characterized in that of recoverable spacecraft shown in the accompanying drawing 1: the empennage (4) that is provided with on the sidewall of recoverable module (1) afterbody or the rear end of tail skirt (5) are no more than the position of the faying face of the afterbody of recoverable module (1) and orbit module (3), or are no more than the residing position, front of orbit module (3); And the maximum gauge of empennage (4) or tail skirt (5) is no more than the internal diameter of the fairing at place, position.

Illustrate:

The front of orbit module (3) is positioned at below this orbit module (3) on rocket the time.

The advantage that such empennage (4) or tail skirt (5) are installed is very little to the change of recoverable module (1), does not particularly need other the big parts and the carrier rocket of airship are made any change at all.Thereby this programme enters enforcement especially easily.This belongs to one of little improvement project of three cabin formula airships.

In the embodiment shown in Figure 2, it is characterized in that:

A. in the front of the flange shape tail skirt (5) of the ring-type empennage (4) of recoverable module (1), be provided with the grid-like movable empennage (4) that to control;

B. ring-type empennage (4) is connected with the side wall surface of recoverable module (1) by tail skirt (5); After adding the back cover of aft end face, formed a leak free interlayer cabin, the mechanical actuation means and the parachute compartment of movable empennage (4), the umbrella cabin of making preparation for dropping all can be arranged in this interlayer cabin.

Illustrate:

The mechanical operating-controlling mechanism of movable empennage (4) can be arranged in the body of recoverable module, in the tail skirt or in the special casing attached to their appearances.Should be noted that with movable empennage bonded assembly axis of revolution to have airtight construction, should be high temperature resistant or be coated with ablative cork coatings.

In the present embodiment, ring-type empennage (4) connects together with tail skirt (5), and can regard a bus as is the whole tail skirt of curve; , utilized the mezzanine space between the bulkhead of this tail skirt and recoverable module efficiently here, the mechanical operating-controlling mechanism and the parachute compartment of movable empennage (4), the umbrella cabin of making preparation for dropping have been arranged in this interlayer cabin.From hereinafter can seeing, what this space also had other efficiently utilizes mode.

Movable or fixing empennage is made grid-like, and its body is smaller and more exquisite, helps unit design.

Parachute compartment, the umbrella cabin of making preparation for dropping are arranged in this interlayer cabin, and their umbrella hatchcover will be arranged on the back cover of aft end face; They should be interconnected with the mechanical actuation means of movable empennage (4), in order to avoid disturb; If the thickness low LCL of interlayer can fall in, borrow some volumes within recoverable module (1).

In accompanying drawing 3,4,5 thereafter, the fixedly empennage (4) on the recoverable module (1) also is drawn as the grid-like ring wing, does like this, and its size is less, aerodynamic force is bigger, and ablation resistance is still fine; And its outer fringe surface can be used as fixedly cylindrical unit (11).

After recoverable module (1) adopts empennage (4) or tail skirt (5), the point of action that the aerodynamic drag that they produce is made a concerted effort will be positioned at the rear end of recoverable module (1), this can make the position of point of action of the overall aerodynamic drag of recoverable module (1) move after significantly, the distance that makes this point of action drop on the center of gravity back of recoverable module (1) strengthens, and the flight stability of recoverable module (1) in atmospheric envelope strengthened greatly; Thereby its flight safety is strengthened greatly.Can say to a great extent that this makes 8 flight attitude control driving engines installing no longer to need, and can cancel on recoverable module; At least can reduce strict demand to their safe reliability and control accuracy, control promptness.

Please note: the whole process of controlling of these 8 driving engines, all occur in overhead 140 kilometers with in the interior return course, recoverable module and air acutely rub therebetween, produce high temperature, disturbance greatly, wherein have distance over half to be among the black barrier of isolated wireless link even.This and thisly control necessary accuracy rate, in time degree, importance degree have formed striking contrast, have formed a pair of incomparable sharp-pointed, the contradiction that is difficult to be in harmonious proportion.What is called is maintained an army for a thousand days, is used military forces for the moment, for controlling of these 8 driving engine these a few minutes, need special what high-tech personnel, the high technology equipment arranged to provide in a conscientious and down-to-earth manner service for it, and in case make a mistake, neglect, fault, consequence will be difficult to the imagination------.In addition, the hypertoxic fuel that these 8 driving engines use can leak into inside and outside the recoverable module, jeopardizes meet sb. at the airport personnel's life and health of cosmonaut and ground, and this also is the problem that the spacecraft design personnel are puzzled one's brains.Can cancel this 8 driving engines now, and following will mention, can high quality, High Performance ground replaces, simplifies the costliness, complexity of airship and vital escape tower, propulsion module, orbit module, all schemes of fairing, method, they can be advanced to the direction of simplifying, integrating, this be how to be worth congratulating, affording general satisfaction thing!

The heating load that the masters such as the big end of head that adopt empennage (4) or tail skirt (5) to share minimizing recoverable module (1) are closed the position also is very favourable: because empennage (4) or tail skirt (5) are positioned at the outside of recoverable module (1), when especially adopting laminal fin, because the heat transfer thermal bridge area is little, the heat of its generation passes to the body part of recoverable module (1) than I haven't seen you for ages, it is damaged; And this empennage or fin blade (4) or tail skirt (5) can adopt the high-temperature alloy steel of metal ingredients such as the high temperature resistant stainless steel, tungstenic, niobium, titanium, nickel, chromium of resistant to elevated temperatures metal such as titanium, high nickel chromium content to make, but heat insulation, the heat proof material of the heat-resisting anti-ablation of surface coated can dispel the heat by coated high temperature high efficient infrared radiation meterial; Particularly empennage (4) can adopt the way of two sides heat radiation, minimizing fin blade thickness, and tail skirt (5) is being taked on the basis of these measures, can also adopt the way of liner thermal insulation layer to reduce the heat of biography to the body part of recoverable module (1).

The head of bell recoverable module itself has had streamline-shaped to a certain degree, the meaning that it is suitably come to a point is that the fleetline degree of the head of recoverable module is strengthened, because added empennage (4), tail skirt (5) afterwards, can significantly be reduced the requirement of the pneumatic braking force of its head; It is suitably come to a point also have other beneficial effect.The heat-resisting anti-ablative nose cone that adds at its head wherein, one or pool of buffer air bag can be installed in the cavity of its vertebra back, this nose cone also can be one and have suitable size, shape, stiffness, evacuated shell container (also can not vacuumizing).Its advantage is very simple, very light a, resistance to heat and heat-proof quality is good especially, reach the performance or the purpose of collision deformation power consumption easily.

As for how to make its structure not only simply, but also have better collision deformation energy-dissipating property, can be with reference to the distortion of the car industry crashproof measure of consuming energy, they have very ripe design and detection experience.

Synthetically say, after adding empennage (4), tail skirt (5) and nose cone, can share the head of bell recoverable module and the pneumatic thermal load of other parts significantly, bear thermal load, disperse thermal load and heat-proof quality is preferably arranged and himself be beneficial to, adopt after them, can improve the safety performance that returns of recoverable module effectively.Here the content that relates to and the benefit of generation and application purpose thereof, also have significantly a lot, as these structures be gently, thin, simple, honest and clean etc., carefully do not state one by one here.

On structure, just as the narration of back, present embodiment or airship of the present invention can be very big to the improvement of three cabin formula spacecrafts, and be a lot; Also can be very little, very unremarkable, just originally useless idle space within utilization and the existing rocket fairing has increased empennage (4) or tail skirt (5) at the recoverable module afterbody simply; Tail skirt (5) as interpolation can be the one slight flange of the tail end of recoverable module (1) towards the side.Yet they may be to the design of returning braking procedure and whole airship, manufacturing and the final in-use performance of recoverable module, produces greatly, very useful effect:

At first, they can produce extra air resistance in atmospheric envelope, move after thereby the point of action that the air resistance that makes recoverable module (1) is made a concerted effort is remarkable, thereby when recoverable module (1) is flown in air, more stable, become the flying body of self-stabilization, the feasible control dynamics that reduces or cancel the spacecraft attitude control of recoverable module (1) becomes possibility; Recoverable module has 8 driving engines, getting through the earth's atmosphere in the return course to make the spacecraft attitude shakiness, for realizing precision landing, need carry out point-device at the right time attitude lift control to airship simultaneously, otherwise, can produce the shaking of extremely harmful recoverable module (1), the action of rolling at any time.In fact, according to second space passenger's narration, the shaking in the recoverable module return course, rock action be very big clearly.And the propellant that these driving engines adopt is dinitrogen tetroxide/dimethylhydrazine etc., belongs to hypertoxic chemicals, and the problem of its micro-leakage is difficult to solve.

Secondly, when the atmospheric envelope high-speed flight, empennage (4) or tail skirt (5) will produce very big flight resistance, very big braking effectiveness, and the deficiency of braking force, braking gross energy is the basic reason that airship adopts three cabin structures.Present empennage (4) or tail skirt (5) by suitable size shape is set, can be as required, almost be braking force and the braking gross energy that increases recoverable module (1) at random, significantly, certain this increase, should be controlled at science, rationally, in the scope of accurate Calculation, experiment confirm, be that the overload that the cosmonaut is subjected to surpasses 6G or other setting overload values at least.Therefore the possibility with very big benefit has occurred: under the prerequisite that enough actv. empennages (4) or tail skirt (5) are installed, can be safely and reliably the weight of the recoverable module of spacecraft increased greatly or its three cabin structures distortion is simplified to two cabin structures or single cabin structure.

Once more, add the empennage (4) or the tail skirt (5) that are provided with and can share the braking heat load at recoverable module outside face, particularly its big end in very big ratio ground, reduce recoverable module because the braking heat load is too big, and the danger of all rough sledding appearance such as thermal environment too worsens in burning of producing, fire damage or the cabin.Because the braking heat of recoverable module outside face load results from the friction drag of it and atmosphere; Be that kinetic energy and the potential energy that is had by it is transformed after all, and recoverable module return kinetic energy and potential energy is certain, can not produce unexpected variation.After the braking heat load at recoverable module outside face, particularly its big end was shared on the big ratio ground of empennage (4) or tail skirt (5), nature can effectively reduce the braking heat or the brake temperature at recoverable module outside face, particularly its big end.The possibility with very big benefit that this is proposed above can causing equally occurs: can be safely and reliably the weight of the recoverable module of recoverable spacecraft increased greatly or its three cabin structures are simplified to two cabin structures or single cabin structure.

In addition, empennage (4) is easy to design and manufacture the movable empennage that can control, manufactures yaw rudder and height rudder, and this movable empennage or rudder can be as the various control rudders of guided missile, and it is laminar to make light weight, and both cheap, resistance to heat is good again; It can control flight as space shuttle to the flight of returning of recoverable module (1), certainly because simplification, the simplicity of this rudder, small-sized property, it is to the handling of recoverable module, also can be weaker, however but be the lifting that has very big degree with respect to the handling of existing bell recoverable module.In fact this make recoverable module have all benefits of space shuttle, and avoided all unfavorable of space shuttle, particularly avoided the costliness, great, complicated, dangerous of space shuttle body.

Those benefits of original relatively airship or space shuttle can reduce:

1, can independently control flight path in atmospheric high level, low layer or middle level actively.This will make airship return ground-surface route form increases greatly, makes this route form break away from existing Apollo airship, Soyuz vehicle, comprises that the rope that the Shenzhou (Divine Vessel) airship returns ground-surface route form ties up; For example, can be with the i.e. black barrier process control of main braking heating process at atmospheric high level and the degree of black barrier is alleviated even disappear, make airship keeping independently controlling flight path under the situation of wireless link actively with ground, get through the earth's atmosphere calmly, return ground.

2, can control airship carry out amplitude comparatively speaking bigger fluctuating, complications, orbit, flight braking distance to airship comprises descending speed, direction route, flight path, the surface heat process is carried out the independently active distribution of controlling, reduce and return hazard level, minimizing reduces the harsh high request to the density of observing and controlling precision and measuring control point to looking far into the distance the dependence of fleet and other ground observing and controlling strength.Thereby can significantly reduce observing and controlling troop, reduce the time span and the region area of observing and controlling, reduce observing and controlling and other relevant work capacitys, can all be arranged in the domestic or domestic a certain area of China, a certain place to the observing and controlling distance of returning of the airship of orbit even, the complexity of returning flight of airship recoverable module is drawn close to the complexity of aircraft or space shuttle landing, thereby reduce the risk and cost of the emission operation of airship significantly.

3, control airship be not rely on gap, of short duration work, must carry out very accurately observing and controlling and the attitude control motor of the costliness controlled and control system, but rely on the aerodynamic lift empennage of the cheapness that can uninterruptedly control continuously to carry out; Both simple and easy cheapness, safe and reliable again.Undoubtedly, this that yes is very useful; Just not saying other advantage of this advantage and airship of the present invention can be prepared design, manufacturing, the emission of airship, launches, moves, returns, ground control, observing and controlling, logistics support and safety thereof, economic performance bring great, breakthrough simplification, improvement, lifting------; Only be the numerous staff that alleviate systems such as design, emission, observing and controlling, guarantee, commanding psychological burden, improve their successful confidence, its huge meaning just can not be underestimated.

4, this kind employing can be controlled the characteristic that empennage is controlled recoverable module heading in air, also very helps launching high-altitude in the airship process accurate pinpoint landing when escaping, and makes it in time obtain relief.When escape in the high-altitude, the location that may land is the marine site of more than 5000 kilometer length, wherein has only three fixed point relief points, how to fly exactly to the relief point, and be a very big difficult problem.Had now can control empennage control recoverable module fall to the relief point, this should be a great good thing.

5, help making the airship that repeatedly comes and goes, because above-mentioned various advantages has been arranged: owing to the deceleration and stopping performance of airship, the lifting that handling can obtain essence; Since many cabin structures of airship can keep and promote simplify greatly, make on the basis of performance airship by comparatively scrappy discrete topology to the big integral structure development of degree of containing, and can increase its volume significantly, increase its workload weight and total weight; This with regard to for this airship is carried out autotelic integration, containing, improvement, can be similar to space shuttle such in order this airship is improved to, the airship of independently controlling, repeatedly coming and going between ground or space has been created best precondition.Certainly this independently controlling only is easy, limited, and repeatedly the airship of Wang Faning and do not require it is the total weight of airship only requires that its main, the most expensive part obtains the utilization of repetition.

6, reach above-mentioned excellent effect, needed cost is minimum.Can do some conservative estimations.

For example, as little improvement, a secondary empennage, tail skirt are set, may only need tens kilograms of metallic materials, be worth maximum tens thousand of units, by considering tens kilogram weights launching costs, total expenses is about 200 to 5,000,000 yuan.And the parts that may simplify, equipment, labor service, service fee can reach more than several ten million yuan, also do not comprise improving safety, accelerate the research and development progress, the bigger benefit of being brought such as recycling and reusing.

For example, as middle improvement, the surface of shell of recoverable module amasss and doubles, is increased to 45m ²The time, its volume can be by 9m ³About be increased to 25m ³About, increase volume more than 175%.Approximately conversion can obtain surpassing 1m for whenever expending 40 kilograms of case materials or 40,000 yuan of costs ³About the available space of recoverable module; The launching costs of considering 40 kilogram weights approximately is 4,000,000 yuan, and total expenses is about 4,100,000 yuan.And the value in this space is calculated according to 900,000,000 yuan launch costs, should surpass 5,000 ten thousand yuan/m ³Both ratios are 1 to 12; This does not also calculate its very huge indirect benefit.

Again for example, in the back, we can see, as big improvement, not only have and improve described 1 to 12 benefit in above-mentioned, also can be from simplifying or go to disappear escape tower, propulsion module, orbit module, fairing etc. obtain bigger benefit the parts greatly.Moreover, by carrying additionally cargo hold, it is had than its also huge much bigger freight-transport capacity of space shuttle of heavy ten times.

We are further noted that: the performance and price of shuttle of the present invention when safety performance itself has been to be better than three cabin formula airships widely, and is just better more than space shuttle.

As the weight of u.s. space shuttle self just reach 77 to 80 tons, no matter transport how many things, personnel, at first will be so big object, serve sky and take back ground, particularly its body contains the unexistent huge parts of three cabin formula airships such as sustainer, main engine, alighting gear, cargo hold of bulky, body irregularity, and its external surface area reaches 2000m ²About, comprising the abominable changeable weak element of stressed huge, hot conditions such as wing, empennage, landing gear compartment, cargo hold, (resistance to elevated temperatures and the stress performance of empennage wherein and the lamellar empennage than small size of the present invention can not be mentioned in the same breath.The face area of recoverable module has only about 2% of space shuttle in addition, has only m more than 20 as the face area of refreshing 6 recoverable modules ²)

In short, the carrying cargo-carrying ability of shuttle of the present invention directly chases after space shuttle, and the potentiality that surpass it are significantly arranged; And performance and price when safety performance will be a lot better much than space shuttle.

Returning safety, reduce it and land impulsive force for the recoverable module that improves airship of the present invention further, eliminate the essentiality that it gets rid of the big end, can adopt Apollo on the sea or the lake surface mode of splashing down, accurately handling, minimum impact dispersion with airship of the present invention to flight path and drop point, situation with the existing reform and opening-up of China, in most of the cases, big inconvenience should be unable to be arranged.

In a word, recoverable module is added empennage as the present invention, though change not quite, its effectiveness really can be breakthrough, essence, historical, very huge; In fact this belong to integrates having carried out a kind of very actv. innovation between existing three cabin formula spacecrafts and space shuttle, guided missile, the parachute; Because this improvement, innovation, integration have above-mentioned various advantages benefit, very are worth promptly carrying out, and deeply excavate.

In fact, the solution of the present invention also has much really can deep ploughing and intensive cultivation, the place of developing.

Utilize as shown in Figure 1 empennage (4) and tail skirt (5) be set, make their rear end be no more than the afterbody of recoverable module (1) and orbit module (3) faying face the position or be no more than the residing position, front of orbit module (3); And the maximum gauge of empennage (4) or tail skirt (5) is no more than the internal diameter of the fairing at place, position; Can only be referred to as little improvement in the present invention.

On the basis that well-designed, as to have necessary, good aerobraking ability empennage is set for recoverable module (1), can carry out the little improvement of the aspects such as profile, diameter, height of recoverable module to three cabin formula airships; Also can carry out the middle improvement that adds aspects such as layer, overstriking of recoverable module; Can also three cabin structures of airship and the escape rocket pattern of trac. mode be improved greatly keeping airship to swing on the basis that emission, forward return.

After changing greatly, can make this airship obtain the performance that many space shuttles just have: its most important point is exactly to make part key, main body of airship can limited repeatedly repeated usage; Another key point is can be with airship of the present invention as " towboat " or " push boat ", as " two-stage or the multistage train formula spacecraft " in traction independence loading cabin.

Embodiment shown in the accompanying drawing 3 can regard the middle improvement to airship as.

In the spacecraft in the embodiment shown in Figure 3, the side of the afterbody of recoverable module (1) is provided with tail skirt (5).The size of tail skirt (5), shape should be come well-designed according to concrete needs and structural possibility; But; In any case, the diameter of tail skirt (5) will be significantly greater than the diameter of the afterbody of bell recoverable module (1); And the difference of these two diameters can design greatlyyer; For example keeping under the fairing diameter unmodified condition, the maximum gauge of the tail skirt of the recoverable module (1) of Shenzhou (Divine Vessel) spacecraft can be designed to be no more than about 3.3 meters, way will can not influence its installation in fairing like this, because the maximum gauge of fairing is 3.6 meters.Note, this diameter of 3.3 meters, more much bigger, much regular than recoverable module (1) diameter (about about 2.3 meters to 1.5 meters) herein; The mezzanine space that comprises between the two is a negligible small size anything but.

In the spacecraft in the embodiment shown in Figure 3, just this sizable volume has been carried out positive utilization; It is characterized in that:

A. the sidewall of recoverable module (1) afterbody is outwards expanded, have the tail skirt (5) that the heating resisting metal of anti-ablation surface layer makes with the employing that on it, is provided with and unite two into one, thereby the shape of this recoverable module (1) is become to having the cylindrical of bigger volume comparatively speaking or being similar to the cylindrical configuration form;

B. the height of recoverable module (1) suitably can be strengthened along axis,, dividing plate or floor (9) with human body import and export (10) are set, make it become two floor structure or multi-storey structures of no stair in the height middle part of the recoverable module of increasing (1);

C. can or the part or all of shell of the nose cone of its interpolation be made the distortion power consumption parts (7) of sheet metal quality with the big end of head (6) of this recoverable module (1); Or in the cavity of the housing back of (6) nose cone that face added before of the big end, the air bag (8) as the distortion power consumption is installed, perhaps the two is combined.

Way like this, very simple and practical, this two floor structures make the performance of spacecraft of the present invention stride forward major step to the performance near huge space shuttle again, the driving compartment of space shuttle is exactly two floor structures, is convenient to very much cosmonaut's rest and work.

If consider merely from the angle of delivery cosmonaut's delivery airship, seat can also be set on two floors, as the represented seat of with dashed lines in the accompanying drawing 3, the manned quantity of this airship is reached more than 6 to 7 people; If further increase diameter, height and the number of floor levels of this recoverable module, even its manned quantity can be increased to about people more than ten, 20 people.This is for carrying out aerospace tourism and other aerospace causes way that gets twice the result with half the effort beyond doubt.Certainly, recoverable module strengthens, has increased the weight of, and the capacity of carrier rocket also must correspondingly be increased.

Embodiment shown in the accompanying drawing 4 and 5 can regard the big improvement to airship as.

A principal character of the airship of the recoverable module with empennage (4), tail skirt (5) among the embodiment shown in Fig. 4 .a is to disappear to be located at the rocket ship fabricate block topmost or at the escape rocket that is the orbit module rear end, and with its reorganization, be deformed into cylindrical unit (11), be installed to the empennage (4) of recoverable module, the position at tail skirt (5) place is gone.

Another principal character of the airship of the recoverable module with empennage (4), tail skirt (5) among the embodiment shown in Fig. 4 .a is the following propulsion module (2) of the recoverable module (1) that is located at the rocket ship fabricate block of disappearing, and with its reorganization, be deformed into cylindrical unit (11), be installed to the empennage (4) of recoverable module, the position at tail skirt (5) place is gone.

Fig. 4 .a is the elevation profile scheme drawing, and Fig. 4 .b is its schematic top plan view.

In Fig. 4 .b, four cylindrical units (11) are arranged, wherein, two are used for installing change rail booster rocket, and two are used to install escape rocket, their symmetrical in twos installations respectively.

Say that synthetically these two embodiment are characterised in that:

A. the sidewall of recoverable module (1) afterbody is provided with movable empennage (4) or the tail skirt (5) that fixing empennage maybe can be controlled, or their combination;

B. going disappears is located at rocket ship fabricate block the top or the escape rocket on orbit module, is provided with a pair of or several to escape rocket symmetrically in the outer end of empennage or tail skirt; Perhaps remove the propulsion module (2) of digit absorption below the recoverable module (1) of rocket ship fabricate block, and transition that will be wherein, transfer rail rocket system to design and produce into cavity ring cylindrical unit (11) especially or be designed to identical or identical substantially a pair of or several to cylindrical unit (11), rely on fixing empennage or directly be movably connected in recoverable module (1) or tail skirt (5) on every side or both sides; Perhaps implement this two kinds of changing of designs simultaneously.

C. in original position that propulsion module (2) is installed the underneath type cargo hold can be installed or have the cabin shape goods of barrel wall, in original position that escape tower is installed the inhead type cargo hold can be installed or have the cabin shape goods of barrel wall,

Illustrate:

1. after carrying out the improvement of above-mentioned form, escape rocket can be, breaks away from airship in the time of 120 seconds in emission, and used as third rocket stage or be used for auxiliaryly becoming rail or braking when being used to withdraw from track advances, with the fuel of saving propulsion module, thereby can prolong airship in the rail life-span.

The setting of escape rocket makes astronaut safety's index of airship emission reach 0.997; And the launcher reliability of the Long March-2F rocket is 97%, and this has promoted manned spacecraft astronaut's emission security effectively.But its cost of paying also is great.At first, its structure and control program complexity, its weight reach several thousand kilograms, comprise that the bodily form of jet pipe reaches 8 meters * Φ more than 1.5 meters, and self price reaches tens million of units, has taken the rocket bearing resource of many preciousnesses.Secondly, its body bottom malleation is above the fairing of manned spacecraft, have an accident enable this escape rocket after, after several seconds, it also must break away from airship immediately, so that liberation fairing and be installed in wherein recoverable module, orbit module, propulsion module makes recoverable module further to separate with other two cabin bodies, the parachute-opening landing.And even emission is normal, escape rocket also must be in the time of 120 seconds, and retrofire breaks away from airship and rocket.These two processes definitely be can't permit out least bit mistake, require to have the reliability near 100%.Accident occurs from rocket launching, promptly remedy the aspect, adopt escape rocket, play great role really.But when the rocket normal transmission, adopting escape rocket, but is the launching success rate that has reduced rocket.In order to improve the reliability of airship emission, the very huge cost of change expense has been installed very expensive escape rocket to it, has but brought, two concern the overall situation, the life line that hangs down does not allow to occur critical separation opportunity of a bit mistake, and this is very big very big contradiction really.

Now escape rocket is installed on recoverable module afterbody side or its empennage, is one really and well improves:

At first, its engine nozzle need not turn round, and structure can be simplified, weight can alleviate, price can reduce.

Secondly, escape rocket no longer malleation on fairing, freed to a certain extent with fairing and whole airship extremely closely, extremely dangerous interlock connection.This release is of great benefit to the safe reliability of airship, and for example escape rocket is in the airship side, even escape rocket does not break away from airship, recoverable module also has the way band escape rocket, the parachute-opening landing.

Once more, escape rocket is not lighted a fire in the time of back 120 seconds in emission and is broken away from rocket and airship; Can also save attached to 4 high-altitude escape driving engines and two high-altitude escape engines on the fairing.

In addition, under the normal situation of emission, escape rocket can not lighted a fire in the time of back 120 seconds in emission and be broken away from rocket and airship; This escape rocket can be converted into the driving engine that is used for the airship transition, make it play the effect of third rocket stage or play the effect of auxiliary transition driving engine, play the fuel reserve that increases propulsion module transition, retroengine at least, increase airship in the moving time of trailer or in the effect in rail life-span.Attention: no matter escape rocket adopts solid fuel still to adopt liquid fuel, as long as the own wt of escape rocket designs low weightly, can bring into play this effect.From reducing the angle of rocket fuel kind, to adopt with the same liquid fuel of transition driving engine to well; Way like this, as long as the thrust that strengthens the transition driving engine is to enough degree or increase some engine nozzles in addition, just can make the deposit fuel of transition driving engine, dual-use material: emission is just often controlled, is braked as transition, attitude.When causing danger, as the escape of airship.Just in time, the gross energy of the fuel reserve of these two kinds of rocket engines differs and is not too many, can accomplish dual-use material fully.

2. remove the propulsion module (2) of digit absorption below the recoverable module (1) of rocket ship fabricate block, with apparatus wherein, the rectification distortion is moved the inside or the outside of recoverable module (1) and is gone.Transition wherein, transfer rail sustainer, main engine system can design and produce into the cavity ring tubular especially or be designed to identical or identical substantially two cylindrical units (11), rely on fixing empennage directly be movably connected in recoverable module (1) or tail skirt (5) on every side or both sides.This is actually changes into parallel-connection structure with recoverable module (1) and being connected by cascaded structure of propulsion module (2).In this change, parts except that engine system in original propulsion module or article go among can shunting the recoverable module (1) of packing into after enlarging; This also is of great benefit to the recycling coefficient that improves airship when repeating to recycle airship.But it should be noted that a series of puffers of adjusting spacecraft attitude, should follow the booster rocket driving engine, they can be arranged on the places such as upper end of cylindrical unit (11), make each spout towards demand side to direction.

Also can implement these two kinds of changing of designs simultaneously, escape tower and propulsion module (2) both be moved the empennage position of the side of recoverable module (1) and go.But must be noted that, escape engine system and propelling motor system well should be designed, they are cut apart respectively and be combined into identical or substantially identical tubular stream line pattern cell cube, be configured in the side periphery of recoverable module (1) symmetrically; Its special case is that the single-piece ring bodies is made in their combination shapings, is configured.Flexibly connect, be meant that the attaching parts that can carry out controlled separation by explosive bolt etc. connects.

The advantage of changing into parallel-connection structure by cascaded structure that is connected of recoverable module (1) and propulsion module (2) at first is, reduce the object that recoverable module (1) must be abandoned when returning ground, because increase after the empennage tail skirt, the braking potential of recoverable module (1) can independently increase significantly, thereby its weight and volume all can obtain increasing.Do like this, will bring into play the potential performance of these empennage tail skirts more fully.

Next is, increases after the empennage tail skirt, and as previously mentioned, recoverable module (1) is convenient to make the recoverable module that can repeatedly reuse since will reuse, the ratio of its recycling or be worth ratio yes high more good more.

Be once more, propulsion module (2) is connected with pipeline between the recoverable module (1), can shorten and tail off, in the interlayer that can be hidden in empennage or on empennage, be provided with, this makes recoverable module (1) and is configured in the escape tower of its side and the deformable body of propulsion module (2) can shield without fairing, can reduce, simplify the area and the structure of fairing.

Outside inferior, propulsion module (2) and escape tower are moved away from after the rear end or front end of airship, can be used on the position of the axis of vacating that preposition orbit module or rearmounted orbit module or cargo hold are set or have the cabin shape goods of barrel wall, particularly after configuration high thrust carrier rocket, can do very big very heavyly, in the scope of rocket load-carrying capacity, without limits.

In fact this is exactly passenger-cargo train formula spacecraft that loads in mixture, this wherein, spacecraft has served as the effect of trailer or towboat or the effect of push tug.

This train formula spacecraft is practical much more flexible than the space shuttle of the U.S.: because " the towboat part " in this train formula spacecraft have only at most about 8 tons, only be equivalent to the U.S. space shuttle 1/10th.Adopt the carrier rocket with the space shuttle equal conditions, effective shipping load of train formula spacecraft can reach 100 tons, than nearly 70 tons of effective shipping load increases of space shuttle.

Just think: 100 tons big goods, and be subjected to the restriction of cargo hold volume hardly, how big this be breakthrough! This can easily solve the spacecraft problem of the dealing moon simply; The big goods of monomer that can deliver 15 tons or 20 tons weights also is well, and this is to the Construction Problems that adopts existing long 2-F rocket or its distortion rocket solution space station, to launching large-scale terrestrial satellite, the emission of several satellite in a rocket being had great help more.The big goods of cabin shape of 100 tons of weights, almost, can be with the base portion of a sizable space station, at least be the big fabricate block of many parts, contain all, be in place, transport to the sky quickly, this be how to save trouble, how fast, how safe and reliable, it can make the quantities of cosmonaut's job space reduce to minimum degree.Also can improve the assembly quality of space station; Because in ground-mounted, can use powerful machinery, instrument to operate, can use unworkable assembly technology in the spaces such as welding, riveted joint.This will be the miracle that the space station is built.It has been arranged, and we just can build much bigger space station with much higher quality, faster speed.

Just think again, the cost of this airship is low like that, safety is such height, to high-tech particularly high-techly the dependence of empty precise measurement and control be like that little, its with respect to the advantage of space shuttle and three cabin formula spacecrafts also just very obviously, very outstanding.

Certainly, high-tech, empty precise measurement and control still very important, be of great value, need exert, greatly develop, but what discuss is safety and cost problem that this is the two entirely different things feelings here.Can not change expense to energy chronically, fully, too much on the empty precise measurement and control in ground after all, the gap of we and spacefaring nation is comprehensive, generally, the numerous cadres and masses that we are responsible for designing, engineering manufacturing, emission ensure should also must shift or the energy of liberation part, be used to develop overall, the comprehensive performance of spacecraft and carrier rocket and even space station, just can make aerospace industry develop to such an extent that get twice the result with half the effort more.In fact, spacefaring nations such as US and Russia in space industry also be of walking go from the simple to the complex, again by numerous road to letter, we come out at the characteristic that will walk out China certainly, this must open the visual field of expanding us especially, enlarges our areal of research.

The overall structure of the spacecraft that the present invention cabin recited above body is parallel can also further be simplified, alleviate.To simplify fairing now; It is characterized in that:

A. simplify at relevant external component (comprising various pipes, line) each cabin, on the basis of shaping, reinforcing, cancellation integral type fairing;

B. replace the local rectifying cover or streamlined contour and the sealing locking and the structure of unblanking are reinforced, added to cell panel of outermost of each solar battery array, make them have the function of local fairing.

Illustrate: for the solar cell windsurfing of the parallel spacecraft of the present invention cabin recited above body, can all concentrate, be arranged on the both sides of orbit module, also can be arranged on the side of recoverable module, because, recoverable module strengthens, adds after the layer, and the function of orbit module no longer is indispensable under many situations; Under a lot of situations, there has been the recoverable module of large volume just much of that, can have cancelled orbit module.And the weight of the recoverable module of large volume can be light than the total weight in original two cabins many, and considerably cheaper.

Among described each embodiment, not changing shape, the size of recoverable module main body cover in the above, only is to load onto empennage tail skirt to it, can be regarded as for a short time to change.Loading onto empennage tail skirt to it when, change shape, the size of recoverable module main body cover, as utilize tail skirt section branch, enlarge the scheme of the diameter of this section recoverable module, on this scheme basis, further increase the scheme of recoverable module bottom-to-top-height and further recoverable module is changed into scheme of two floors or multi-storey structure or the like, change in can be regarded as.Relating to propulsion module, escape tower modification of other formed the scheme of parallel-connection structure with recoverable module, and further adds underneath type cargo hold, inhead type cargo hold or have the scheme of train formula loading spacecraft of the cabin shape goods of barrel wall, can be regarded as greatly to change.From above narration as can be known, all multi-schemes that change or change greatly in not saying so, very big even the scheme that changes for a short time also is that benefit is a lot, have breakthrough meaning.On the other hand, even the scheme that changes greatly, do not grow up owing to have the difference of essence or improve on original basis as the corresponding object of the Control Software of each cabin on basis or each big parts, airship and control hardware, technology path and former airship, it is made with use and all can use original or similar technology, controlling equipment, control method, control route.Its cost of manufacture will almost or slightly reduce with original spacecraft; Its ratio of performance to price will have the lifting of huge amplitude than original spacecraft.

Still the breakthrough of the technical and economic performance of product is unobvious for spacecraft of the present invention, and on using method, can have different greatly with the using method of original bell recoverable module yet:

According to the return method with recoverable spacecraft of magnetic tape trailer wing recoverable module (1) recited above, the return method of the recoverable module of its return method and existing three cabin formulas or two cabin formula airships is close, it is characterized in that:

A. airship propulsion module engine ignition braking, propulsion module break away from recoverable module (1), recoverable module (1) after the height about 120 kilometers enters atmospheric envelope, the movable empennage (4) that utilization can be controlled flies along predefined flight path earthward in the scope of its within the reach, simultaneously handle recoverable module (1) in the scope of the hypergravity that the astronaut is easy to bear;

B. with to be subjected to the approximate parabolical flight path of a little lift different in the return course of existing recoverable module, under the controlling of movable empennage (4), recoverable module (1) is behind reentry, and the flight path of taking is bigger descent path of the mild degree of level or the flat compound route that flies route or fluctuating route or spiral route or any zigzag path or these routes;

C. movable empennage (4) adopts the method for ground remote control or computer program control or manual control or three kinds of method mixing controls to control; The method of manual control is carried out controlling of empennage (4) as can adopt control on high speed opportunity, low speed the time;

D. when speed is reduced to the 1000 meter per second left and right sides, how high regardless of highly having, can throw the big end;

E. the root of parachute rope or acting point can be arranged near the tail end or side center of gravity of recoverable module (1);

F. can splash down at the darker water surface band umbrella of the depth of water consciously, and cut umbrella after before falling moment.

Illustrate:

Movable empennage (4) can take the laminal empennage, its plane can parallel or vertical with the axis of recoverable module (also can have certain angle), its control mode can be with reference to the control mode of various guided missile yaw rudder sheets, its control power can adopt spacecraft the pressure gas that must carry, anyway start manipulation activities empennage (4) afterwards, maximum half an hours, the airship ground that just is bound to get back to, these gases stay more does not have great effect yet.The weight of so movable empennage system can be very light, and price can be very low, realizes easily that also automation or manual control control.This will be to the handling of recoverable module flight path less than aircraft or space shuttle, but can be a lot better than bare bell recoverable module; After even recoverable module adopts 8 posture adjustment driving engines that adopt poisonous fuel, effect does not have effective and lasting that pneumatic rudder face controls yet.

Owing to installed movable empennage (4) additional, recoverable module (1) is behind reentry, and the flight path of taking can be the slow degree of horizontal bigger descent path or the flat compound route that flies route or fluctuating route or spiral route or any zigzag path or these routes.This means recoverable module (1) when returning ground, can take the method for orbit, last parachuting.The function of movable empennage (4) also comprises, proofreaies and correct the left and right sides tilted position that enters the recoverable module in the atmospheric envelope, make its keep in just.

This can simplify the return course of recoverable module (1) greatly, can send signal by ground or cosmonaut self in any moment, any place when approach China, starts return information.Return in the ground-surface all or part of process, ground or cosmonaut self be the change of flight route at any time.This can make the front, rear, left and right that start the projected position point return and fix on the landing place, in any position.

This just may significantly reduce ground-surface commander, control, the total quantity of the establishment of the personnel of administrative service, equipment, significantly reduces the degree of dragging in many people, and can reduce even cancel setting out of " looking far into the distance " fleet.The restriction of launch time that so also can make manned spacecraft is by any time that expands to autumn and winter throughout the year.This can reduce the cost of China emission manned spacecraft greatly, the speed of development that quickens China's aerospace cause greatly, the tremendous development that the aerospace cause of China is got twice the result with half the effort more.

Because a big chunk of the aerodynamic drag of airship recoverable module of the present invention has been distributed to the empennage parts, also owing to point can be done in the big end of head of this recoverable module, reduce its aerodynamic drag, thereby, after entering atmospheric envelope, the compaction forces that the big end is fitted in the recoverable module head will significantly reduce or disappear, thereby, the resistance or the difficulty of throwing the big end can diminish, and this helps throwing at any time at the big end.When speed was reduced to the 1000 meter per second left and right sides, the pneumatic heat of generation can further not improve the temperature of recoverable module head, can cool off it on the contrary, therefore can throw in advance at the big end.Can certainly be as previously mentioned, the big end, thrown in cancellation, cancels big bottom parts.

To land impulsive force in order further reducing, can to make the big end of distortion power consumption as previously mentioned, or distortion power consumption nose cone, splashing mode or water surface downhill race mode can also be adopted.

The tail diameter of airship recoverable module as described above, after the expansion, parachute compartment, the umbrella cabin of making preparation for dropping, and their umbrella hatchcover all can be shifted on the aft end face of recoverable module, are positioned at the side of hatch door.Wherein, parachute also can be located at the top, side of recoverable module, makes it can keep horizontality when landing, and this is applicable to drop in water surface.

Because the airship recoverable module adds and puts after the well-designed empennage tail skirt, particularly after installing the empennage tail skirt of similar miniature parachute additional, its aerobraking power can rise significantly, by the thermal boundary district, when arrival releases a parachute, the sinking speed of its air counterbalance can be little balancing speed than it by being reduced to one about 180 present meter per seconds, for example is reduced to 100 meter per seconds; The impulsive force that is subjected to when parachute is opened reduces greatly, makes to use the relatively more parachute of small size, perhaps can use no special crack or crack less, comparatively cheapness and small-sized parachute.(parachute that cracks is the ringsail parachute or the fabric umbrella that cracks)

Be the emission flying method that has the recoverable spacecraft of magnetic tape trailer wing recoverable module (1) according to recited above equally, the emission flying method of the recoverable module of its method and existing three cabin formulas or two cabin formula airships is close, it is characterized in that:

A. escape rocket is arranged on the side of recoverable module (1) by empennage or tail skirt, or is set directly at the side of recoverable module (1);

B. with the range extension on igniting opportunity of escape rocket to when the recoverable module braking becomes rail and begins Returning ball, make it can bring into play more effect: be included in preceding 900 seconds of rocket launching enter the orbit to airship in as the escape power of the airship in the middle of the whole rocket launching process or when airship becomes rail as the change rail power of airship or when airship leaves the right or normal track reentry, as the brake power of airship.

Such propulsion module of the present invention or become the rail rocket, the recoverable spacecraft in parallel with recoverable module return flying method, can also be further improved.

The return method of the recoverable module of its return method and existing three cabin formulas or two cabin formula airships is close, it is characterized in that:

A. transition that will be wherein, transfer rail, retrorocket system to design and produce into cavity ring cylindrical unit (11) especially or be designed to identical or identical substantially bitubular shape device (11), rely on fixedly empennage or tail skirt or directly be movably connected in recoverable module (1) on every side or both sides;

B. the disengaging of cavity ring cylindrical unit (11) or identical or substantially identical two cylindrical units (11) and recoverable module (1) is selected in it opportunity and enters appropriate time after the atmospheric envelope.

Illustrate:

For present Shenzhou (Divine Vessel) airship, as enter after the atmospheric envelope,, be difficult to make propulsion module to separate, because the resistance of high velocity air can be pressed on propulsion module on the recoverable module with recoverable module (1) unless add extra high thrust separation rocket.And recoverable module is controlledly sent into after the atmospheric envelope, separate propulsion module again, help the movable empennage of recoverable module or fixing empennage, produce immediately and control lift or stable lift for flight, make it can before entering atmospheric envelope in a flash out of control the or unstability of flight not take place.

The recoverable module of the magnetic tape trailer wing of the present invention and but very huge for the effect simple in structure, that principle concisely can obtain of the spacecraft of core by it; Its empennage, tail skirt that add to be provided with can do for a short time, thin, light, honest and clean, the effect of its generation but can be very big very big, but also for the further simplification of recoverable module, spacecraft, carrier rocket, improvement, perfectly provide solid good basis.It belongs to effectively and efficiently integrating that spacecraft and space shuttle carry out, the raising of its performance and potentiality very obviously, very huge, it can be with the weight of space shuttle 1/10th, 1/10th cost, finish and the similar similarly task of space shuttle, wherein in some aspects, as aspect the manned cargo-carrying alerting ability, but aspect the weight limits of carrying goods, volume restrictions, even substantially exceed space shuttle.For example space shuttle is through the improvement of decades, also just from tens tons of originally load carrying abilities, bring up to afterwards 29.5 tons, unless the bigger space shuttle of design will increase the weight of, strengthen carrying capacity again, has been possibility seldom; Yet train formula spacecraft of the present invention adopts the ultra-large type object that just can launch 100 tons of weights with the carrier rocket of space shuttle the same terms.In addition, its emission and the safety performance that returns, economic performance have also surpassed space shuttle very significantly.

Spacecraft of the present invention and three cabin formula spacecrafts carry out performance comparison, and situation is similar with it, will not describe in detail at this.

The recoverable module of the magnetic tape trailer wing of the present invention and by it for the spacecraft of core can the structure of three cabin formula spacecrafts be changed for a short time, in change, change greatly, wherein each improvement has an abundant and deep content more.

Little improvement wherein, basic structure and member profile to carrier rocket and airship all need not to change, can directly utilize the existing Shenzhou spacecraft and carrier rocket system thereof, implement this scheme, it only is to utilize idle space within the fairing, simple empennage, tail skirt section part are installed on recoverable module, just can significant effective ground improves the aerodynamic lift ability on flight stability behind its reentry, flight safety, all directions and returns load-carrying capacity; And very big potential can also be arranged, make it can design the load-carrying capacity that improves recoverable module significantly, for spacecraft of the present invention changes in carrying out and reforms the necessary condition of making greatly.

Middle improvement wherein can increase the effective volume of recoverable module greatly, even it can be designed and produced into two floors (or multi-story) structure, makes its cumulative volume by about 9m ³Increase sharply to 25m ³More than, for example can reach 50m ³Thereby the number that makes delivery cosmonaut or space tourist is increased to 6 to 8 people even is increased to more than 15 people from 3 people; And the weight of whole spacecraft still can be no more than 10 to 15 tons.In other words, can make the total weight of this airship and total seating capacity's ratio be reduced to 1 (ton/people) by 3 (ton/people).

And the ability of the bearing load of refreshing 6 spacecraft carrier rockets is more than 9 tons, after making improvements slightly, can reach more than 11 tons.In other words, by middle improvement, we can bring up to the passenger carrying capacity in short-term of refreshing 6 spacecrafts more than 6 to 11 people, also just mean, when the time comes, can 6 to 11 cosmonaut or passenger be served or connect down the space station quickly.

Certainly, we also can carry some less, and some research equipments of overloading can also be exploited potentialities, and increase the capacity of carrier rocket; After having increased capacity, can according to actual needs delivery content, delivery task be handled flexibly fully.Please note, double-deck recoverable module, it is very different carrying out series connected effect with recoverable module, orbit module, does not need to be provided with complicated and vital air tight door between the former layer and the layer, even do not need to be provided with hatch door, it is just passable only need to open a bigger manhole (10).Note that also the cabin is simple, failure-free is many than two in a cabin, it is easy to be many, safe many that its operation is wanted, and its weight is light, and price is much cheap.As for, really be to have when the needing of orbit module is set, on recoverable module or below orbit module still can be set, wherein the underneath type orbit module can be set, this belongs to an advantage of spacecraft of the present invention, when escaping, can get rid of this orbit module at the very start, this can effectively reduce the thrust size of escape rocket.The difference of orbit module and cargo hold is also not obvious in fact, and in fact orbit module is equivalent to a cargo hold that is used to stay the rail operation.

Big improvement wherein, except can be because of the cause that installs empennage, tail skirt additional, and as middle improvement, increase the effective volume of recoverable module greatly, increase outside its capacity, propulsion module and escape rocket can also be moved to the lateral location of the afterbody of recoverable module by the two ends distortion of the axis of airship, structure simplification greatly, safety and the cost performance of whole airship and carrier rocket are improved greatly; More can haul the also helpless super-big and overweight object of space shuttle with the form of train formula spacecraft, for building the large space station, implement the manned flight of landing on the moon, carrying out the aerospace tourism creation passenger and freight carrier strip spare of the scale of going up as accompanying drawing 5.In accompanying drawing 5 and accompanying drawing 4, the booster rocket device (11) of tubular there are two labels; Another label is (2), and this illustrates that this booster rocket device (11) is improved, simplifies, is shifted by propulsion module.It shall yet further be noted that and say to a certain extent as previously mentioned that escape rocket also can merge in the tubular booster rocket device (11) and go.(in accompanying drawing 5,, wash out cargo hold in order to prevent the booster rocket high-temperature gas, can high temperature gas flow on the right direction, be coated with the coating of anti-the ablation, or take other measures such as canted nozzle.)

More than little, in, the big improvement, help that all recoverable module is partly had or surpass some critical nature of space shuttle, as the self-stabilization function of in air, flying, control manned function of the function of heading, reusable function, a large amount of loading or the like by the aerodynamic lift fin, thereby make the performance of recoverable module of the present invention or manned spacecraft draw close the performance boost of making a breakthrough property to the performance of space shuttle.

More than these improvement, all can be based on the relevant condition of existing divine boat's spacecraft and carrier rocket thereof and ground control, observing and controlling, logistics support system, can use cost seldom, very short time, very the failure-free mode builds the High Performance of the sinotype that reaches world-class levels, manned, the loading spacecraft system of low cost come out.

Spacecraft of the present invention is after the special design of further making specific aim, keen-witted and capableization, can promptly return ground-surface rescue spacecraft as the space station, can also can be used as the manned main body of inferior orbiting spacecraft as visitor, the goods traffic delivery means between space station and other aerospace flying body.

In sum, spacecraft of the present invention also can be referred to as the simple and easy space shuttle of magnetic tape trailer wing recoverable module parachuting formula module combinations.

Moreover, core of the present invention---magnetic tape trailer wing recoverable module also has great learning value, military value.

In above-mentioned article, we design recoverable module bigger as far as possible, now, act in a diametrically opposite way, with its design try one's best little and solid, the aerodynamic force that can rely on tab arrangement in atmospheric envelope that utilizes it to have comes the feature of change of flight direction, be used as breaking through the penetration missile of reentrying of antimissile system, the tail end that this guided missile has carrier rocket, recoverable module or bullet (1), this recoverable module or bullet (1) is provided with empennage (4), the tail skirt (5) that comprises the movable empennage that can control, also front wing can be set, this kind method is characterised in that:

A. with the requirement of recoverable module (1) and empennage (4) thereof, tail skirt (5), front wing, dwindle, streamlining, and load onto " conventional or nuclear " warhead to it according to the high-speed missile bullet;

B., petty action amount attitude control motor system still is installed on this recoverable module (1) or the military bullet;

C. utilize petty action amount attitude control motor system to control this recoverable module (1) or military bullet in extraatmospheric flight; Utilization activity empennage (4) is controlled this recoverable module (1) or the flight of military bullet behind reentry; Then can adopt two kinds of control methods simultaneously at the atmospheric envelope edge, the flight path of taking is bigger descent path of the mild degree of level or the flat compound route that flies route or fluctuating route or spiral route or any zigzag path or these routes;

D. these flight paths are for formulating at random, have nothing in common with each other, but be by computer program critically set and control, and as far as possible accurately the guiding regulation land the place;

E. the shape of this recoverable module (1) or military bullet and finish coat can be according to the requirement designs of radar stealth and optics stealth.

Illustrate: change recoverable module into the bullet of reentrying, to the guidance program, all have special and requirement accurately preferably has the GPS global positioning system as the observing and controlling benchmark the observing and controlling precision; Also needing has control accurately to the lift handling of empennage fin, makes its manipulation force stablize greatly, and resistance is less again simultaneously.This all needs the aerodynamic force theory of empennage and its main body is carried out more deep discussion, research, test.

The advantage of this prominent anti-bullet is: stealthy, simple, cheap, light and handy, be easy to make, be easy to guidance; Enter atmosphere After, that the great efforts that its dynamics of controlling for heading is controlled than petty action amount attitude control motor system get is very many, during continuity Between long, free of discontinuities, do not need too many machinery to control energy reserves. For example can be with a light and handy cheap compressed air cylinder conduct Its mobile wing control the energy. So, just, can give this bullet high-altitude, at a high speed, high maneuverability, the motor-driven route of overlength prominent Anti-ability makes antimissile system helpless. (" Russia is new to consult the article that Yu Muye delivers at 2005-12-2 " Yangzi Evening " The type guided missile does not move parabolically the U.S. and can't tackle ")

Since it simple, cheap, light and handy, be easy to make, this is so that it is suitable for the making multiple warhead missile.

In the future, can also be on its surface label resistant to elevated temperatures efficient reflector layer so that the anti-guided missile laser weapon that may occur in the future pair It is also at one's wit's end.

Claims (10)

1. recoverable spacecraft, its recoverable module (1) is campanula halleri Halleri, and its head, tail two ends flexibly connect with propulsion module (2), orbit module (3) respectively, this recoverable module (1) is when emission, be afterbody and upwards be installed in the top of firing a rocket, when returning, be head and enter atmospheric envelope downwards; It is characterized in that:

A. the sidewall of this recoverable module (1) afterbody is provided with sheet or ring-type or barrel-contoured empennage in parallel (4) or the tail skirt (5) that adopts the heating resisting metal making with anti-ablative coating or surface layer or is provided with empennage (4) simultaneously and tail skirt (5); The movable empennage that empennage wherein (4) maybe can be controlled for fixing empennage, this empennage (4) can be grid fin or folding wings, the bus length of tail skirt (5) should be suitable, can be simple expansion linear portion or be segment of curve arbitrarily;

B. with respect to empennage (4), activity or fixing front wing can be set;

C. the head of this recoverable module (1) can be changed a social system the distortion power consumption nose cone that becomes streamline-shaped with suitable height, suitable sharp degree or the heat-resisting anti-ablation that has suitable height, suitable sharp degree in its of head interpolation.

2. spacecraft according to claim 1 is characterized in that: the empennage (4) that on the sidewall of recoverable module (1) afterbody, is provided with or the rear end of tail skirt (5) be no more than the afterbody of recoverable module (1) and orbit module (3) faying face the position or be no more than the residing position, front of orbit module (3); And the maximum gauge of empennage (4) or tail skirt (5) is no more than the internal diameter of the fairing at place, position.

3. spacecraft according to claim 1 and 2 is characterized in that:

A. in the front of the flange shape tail skirt (5) of the ring-type empennage (4) of recoverable module (1), be provided with the grid-like movable empennage (4) that to control;

B. ring-type empennage (4) is connected with the side wall surface of recoverable module (1) by tail skirt (5), after adding the back cover of back, formed a leak free interlayer cabin, the mechanical actuation means and the parachute compartment of movable empennage (4), the umbrella cabin of making preparation for dropping can be arranged in this interlayer cabin.

4. according to the described spacecraft of claim 1 to 3, it is characterized in that:

A. the sidewall of recoverable module (1) afterbody is outwards expanded, have the tail skirt (5) that the heating resisting metal of anti-ablation surface layer makes with the employing that on it, is provided with and unite two into one, thereby the shape of this recoverable module (1) is become to having the cylindrical of bigger volume comparatively speaking or being similar to the cylindrical configuration form;

B. the height of recoverable module (1) suitably can be strengthened along axis,, dividing plate or floor (9) with human body import and export (10) are set, make it become two floor structure or multi-storey structures of no stair in the height middle part of the recoverable module of increasing (1);

C. can or the part or all of shell of the nose cone of its interpolation be made the distortion power consumption parts (7) of sheet metal quality with the big end of head (6) of this recoverable module (1); Or in the cavity of the housing back of (6) nose cone that face added before of the big end, the air bag (8) as the distortion power consumption is installed, perhaps the two is combined.

5. spacecraft according to claim 1 is characterized in that:

A. the sidewall of recoverable module (1) afterbody is provided with movable empennage (4) or the tail skirt (5) that fixing empennage maybe can be controlled, or their combination;

B. going disappears is located at rocket ship fabricate block the top or at the escape rocket that is the orbit module upper end, is provided with a pair of or several to escape rocket symmetrically in the outer end of empennage or tail skirt; Perhaps remove the propulsion module (2) of digit absorption below the recoverable module (1) of rocket ship fabricate block, and transition that will be wherein, transfer rail rocket system to design and produce into cavity ring cylindrical unit (11) especially or be designed to identical or identical substantially a pair of or several to cylindrical unit (11), rely on fixing empennage or directly be movably connected in recoverable module (1) or tail skirt (5) on every side or both sides; Perhaps implement this two kinds of changing of designs simultaneously.

C. in original position that propulsion module (2) is installed the underneath type cargo hold can be installed or have the cabin shape goods of barrel wall, in original position that escape tower is installed the inhead type cargo hold can be installed or have the cabin shape goods of barrel wall.

6. according to claim 1,2,5 described spacecrafts, it is characterized in that:

A. simplify at relevant external component (comprising various pipes, line) each cabin, on the basis of shaping, reinforcing, cancellation integral type fairing:

B. replace the local rectifying cover or streamlined contour and the sealing locking and the structure of unblanking are reinforced, added to cell panel of outermost of each solar battery array, make them have the function of local fairing.

7. according to the described emission flying method with recoverable spacecraft of magnetic tape trailer wing recoverable module (1) of claim 1 to 6, the return method of the recoverable module of its method and existing three cabin formulas or two cabin formula airships is close, it is characterized in that:

A. airship propulsion module engine ignition braking, propulsion module break away from recoverable module (1), recoverable module (1) after the height about 120 kilometers enters atmospheric envelope, the movable empennage (4) that utilization can be controlled in the scope of its within the reach, in the scope that the astronaut is easy to bear, handle recoverable module (1) simultaneously and fly earthward along predefined flight path;

B. with to be subjected to the approximate parabolical flight path of a little lift different in the return course of existing recoverable module, under the controlling of movable empennage (4), recoverable module (1) is behind reentry, and the flight path of taking is bigger descent path of the mild degree of level or the flat compound route that flies route or fluctuating route or spiral route or any zigzag path or these routes;

C. movable empennage (4) adopts the method for ground remote control or computer program control or manual control or three kinds of method mixing controls to control; The method of manual control is carried out controlling of empennage (4) as can adopt control on high speed opportunity, low speed the time;

D. when speed is reduced to the 1000 meter per second left and right sides, how high regardless of highly having, can throw the big end;

E. the root of parachute rope or acting point can be arranged near the tail end or side center of gravity of recoverable module (1);

F. can splash down at the darker water surface band umbrella of the depth of water consciously, and cut umbrella after before falling moment.

8. according to claim 5,6 described emission flying methods with recoverable spacecraft of magnetic tape trailer wing recoverable module (1), the emission flying method of the recoverable module of its method and existing three cabin formulas or two cabin formula airships is close, it is characterized in that:

A. escape rocket is arranged on the side of recoverable module (1) by empennage or tail skirt, or is set directly at the side of recoverable module (1);

B. with the range extension on igniting opportunity of escape rocket to when the recoverable module braking becomes rail and begins Returning ball: be included in preceding 900 seconds of rocket launching enter the orbit to airship in as the escape power of the airship in the middle of the whole rocket launching process or when airship becomes rail as the change rail power of airship or when airship leaves the right or normal track reentry, as the brake power of airship.

9. according to the flying method that returns of claim 5,6 described recoverable spacecrafts with magnetic tape trailer wing recoverable module (1), the return method of the recoverable module of its return method and existing three cabin formulas or two cabin formula airships is close, it is characterized in that:

A. transition that will be wherein, transfer rail, retrorocket system to design and produce into cavity ring cylindrical unit (11) especially or be designed to identical or identical substantially bitubular shape device (11), rely on fixedly empennage or tail skirt or directly be movably connected in recoverable module (1) on every side or both sides;

B. the disengaging of cavity ring cylindrical unit (11) or identical or substantially identical two cylindrical unit devices (11) and recoverable module (1) is selected in it opportunity and enters appropriate time after the atmospheric envelope.

10. according to the method for designing of claim 1,2,7 described method design-calculated high altitude penetration guided missiles, the tail end that this guided missile has carrier rocket, recoverable module or bullet (1), this recoverable module or bullet (1) is provided with empennage (4), the tail skirt (5) that comprises the movable empennage that can control, also front wing can be set, this kind method is characterised in that:

A. with the requirement of recoverable module (1) and empennage (4) thereof, tail skirt (5), front wing, dwindle, streamlining, and load onto " conventional or nuclear " warhead to it according to the high-speed missile bullet;

B., petty action amount attitude control motor system still is installed on this recoverable module (1) or the military bullet;

C. utilize petty action amount attitude control motor system to control this recoverable module (1) or military bullet in extraatmospheric flight; Utilization activity empennage (4) is controlled this recoverable module (1) or the flight of military bullet behind reentry; Then can adopt two kinds of control methods simultaneously at the atmospheric envelope edge, the flight path of taking is bigger descent path of the mild degree of level or the flat compound route that flies route or fluctuating route or spiral route or any zigzag path or these routes;

D. these flight paths are for formulating at random, have nothing in common with each other, but be by computer program critically set and control, and as far as possible accurately the guiding regulation land the place;

E. the shape of this recoverable module (1) or military bullet and finish coat can be according to the requirement designs of radar stealth and optics stealth.

Images