GB2481438A - Earth to near space umbilical transport system - Google Patents

Abstract

A transport system for use to transfer loads, including cargo and people, between two vertically spaced terminals such as a terminal 1 on earth and a near space terminal 2 comprising a buoyant umbilical 3 linking the terminals. The umbilical has a balloon supportive subsystem carrying a pneumatic delivery subsystem. The umbilical is comprised of balloon segments (6 fig 2A), a central service core (7 fig 2A) and inner transport cores (4,5 fig 2A). Slave balloons (21 fig 8) are positioned at regular interval along the umbilical length. Canisters 15 are sized to transport people or goods and are inserted into the pneumatic transport tubes via doors 17. A ram 11 pushes the canister into the main part of the transport tube where valving allows airflow to drive the canister along the tube. This system is intended to be able to continuously transport a number of people to near space and return them again in a matter of a few hours and at comparatively low running costs.

Description

Earth to Near Space Umbilical Transport System

Field of the Invention

The present invention concerns an umbilical transport! delivery system to transfer loads between a station! terminal on earth and an upper atmosphere or near space station! terminal.

Background to the Invention

The majority of existing launch systems for transportation of people and goods into space rely on use of rocketry to propel the vehicles and, infrastructure cost aside, they are extremely costly to operate per unit load transported. There is currently no transit system whereby large numbers of people and goods may be taken into near space and later returned.

Projects such as the Virgin Galactic flight service aim to give passengers an experience of near space by flying in a two stage craft to reach altitudes of approximately 15 kilometres but the duration of the space is experience is for a very brief minutes and the fuel requirements and operating costs remain high. Accordingly, space, even near space, remains accessible only to the very fortunate few and despite it being many decades since man first entered space, we have only the smallest of toeholds there.

The present invention seeks to provide an efficient, effective and ultimately more economical transport system for access to the upper atmosphere and near space that will benefit mankind as a whole, allowing goods and people to be transported there with comparative ease. An objective of the system is for it to be implemented in a way that facilitates the construction and emplacement! displacement of an increasing number of identical systems around the earth. The system is suitably designed to ultimately enable affordable travel for all to a near space station with a viewing gallery for space tourism. It may also ultirriately serve as a node in a system for space construction, exploration and usage. It is a primary objective of the present invention to simplify and reduce cost of repeat journeys and delivery tasks.

Sum mary of the Invention According to a first aspect of the present invention there is provided an umbilical transport! delivery system to transfer loads between two vertically spaced terminals such as a station! terminal on earth and a near space or upper atmosphere station! terminal, wherein the system comprises the two vertically spaced terminals and a buoyant umbilical linking the terminals, the umbilical having a balloon supportive subsystem carrying a pneumatic transport! delivery subsystem that runs along the umbilical.

is The pneumatic transport! delivery subsystem preferably comprises an ascending transport tube and a descending transport tube. These transport tubes are suitably linked together in a circuit and preferably to a heater and pump at the earth terminal.

Particularly preferably the balloon supportive subsystem of the umbilical comprises a plurality of elongate balloon lengths that extend lengthwise of the umbilical and preferably ensheathing the transport tubes of the umbilical. Particularly preferably the balloon lengths are each formed of elongate segments that have a hinge along their length and may open to close around and enwrap the transport tubes.

The system of the present invention allows individuals to journey into space with the help of an umbilical. On constructing a near space terminal to facilitate initial growth and an earth terminal to provide sustenance, the umbilical serves as the feed link between the two. The umbilical once connected to the near space terminal, is preferably detachable from the earth terminal and capable of being moved and connected with another compatible pre-constructed earth terminal. In effect, what this means is that the first completed near space terminal would be usable to then construct the second near space terminal, and so on.

Various experiments with helium-filled weather balloons have established the viability of balloons reaching altitudes of the order of 18 to 37 km.

These altitudes are in the stratosphere! upper atmosphere, also known as near space. The present invention exploits the supportive effect of balloon structures to elevate the umbilical to near space while this is assisted by a io pneumatic transport system that provides a comparatively lightweight solution to moving the cargo payload along the umbilical. Further inventive aspects will become apparent from the following description, drawings and claims

is Brief Description of the Drawings

The present invention will now be more particularly described by way of example, with reference to the accompanying drawings, wherein; Fig 1 is a schematic diagram of the system showing the umbilical attached to the earth terminal and extending up to a point of attachment to a near space terminal, whereas Figure 1A is a corresponding schematic diagram of the system showing the umbilical detached from the earth terminal; Fig 2 is a schematic overview diagram of the pneumatic transport circuit of the system, whereas Figure 2A is a transverse section of the umbilical taken along the line A-A in Figure 2 and Figure 2B is a longitudinal section of part of the umbilical taken along the line B-B in Figure 2; Fig 3 is a detail perspective view of the earth station loading! unloading point of the pneumatic transport circuit, whereas Figure 3A is an elevation view of the umbilical at that location showing the payload withheld prior to injection into the delivery circuit and Figure 3B is a similar view showing the payload being injected; Fig 4 is an elevation view of the receptor part of the earth station end of the pneumatic transport circuit; Fig 5 is a perspective view of a payload canister of the pneumatic transport circuit; io Fig 6 is an elevation view of part of an umbilical showing one of the jacket balloon lengths of the supportive subsystem mounted around the pneumatic delivery cores (transport tubes) and Figure 6A is an exploded assembly view that shows the jacket balloon length demounted from the cores and in hinged open state; is Fig 7 is an elevation view of part of the umbilical showing several balloon lengths and with one removed; Fig 8 is an elevation view similar to Figure 7, showing a servicing balloon and gondola mounted on the umbilical; Figure 9 is a horizontal sectional view through a core junction where the descending transport tube and a horizontal tube of the pneumatic transport circuit meet; and Figure 10 is a schematic diagram of the earth station loading! unloading point similar to Figure 3B but further showing a flow diverter for selectively directing the pressurised gas in the ascending core to push the newly injected canister or to bypass it.

Description of the Preferred Embodiment

Referring to Figure 1A this shows the system as comprising an earth station! terminal 1 and an upper atmosphere or near space station! terminal 2 with an umbilical 3 attached to the earth terminal 1 and extending up to a point of attachment to the near space terminal 2. Figure 1A shows the umbilical 3 detached from the earth terminal 2 as may be required to, for example, relocate the umbilical 3.

The Umbilical io In its design approach the umbilical 3, like the other elements of the system, is of the simplest construction, with a minimal number of component parts while achieving the required functionality.

As illustrated in Figures 2A and 2B the umbilical 3 comprises two main core tubes! transport tubes 4, 5 ensheathed in a plurality of supportive is elongate balloons 6. Each balloon 6 is suitably formed as a pair of vertically hinged balloon segments 6a, 6b (see Figure 6A) and is of a selected length. Each balloon 6 is capable of being inflated with a light gas such as Helium to provide lift, and capable (minimally) of supporting itself and the core tubes! transport tubes 4, 5 (and ancillaries) contained within its length (rendering each segmented length of the umbilical 3 weightless in gravity). In effect a substantial part or the whole length of the umbilical 3 is buoyant and floats between the earth terminal 1 and the upper terminal 2.

The balloon lengths 6 may be inflated to a lesser extent at higher altitudes than at the lower altitudes in view of the reduction in atmospheric pressure at the higher altitudes. The balloon lengths 6 may if desired have gas vented from them as they rise to greater heights. The balloon lengths 6 may be sub-divided into compartments for greater control over pressures for buoyancy and! or to enhance ability to withstand damage.

The balloon segments 6a, 6b, being hinged, open along their length and close to envelope and sandwich between them the two main core tubes! transport tubes 4, 5 (one tube 4 serves for ascent and the other 5 for descent). The transport tubes 4, 5 form part of the hermetically sealed pneumatic delivery system and the balloon lengths 6 provide a supportive inflated jacket around those tubes 4, 5.

The balloon segments 6a, 6b also sandwich a smaller central service core 7 that runs the length of the umbilical and which may carry services such as fibre-optic and electrical cabling and which has one or more small bore conduits for liquids/gas etc as shown in Figure 6A. The balloon segments 6a, 6b are suitably inflated or deflated by gaseous exchange with such a conduit of the service core 7 using non-return valves. The inner walls of the balloon segments 6a, 6b that sandwich the inner cores! transport tubes 4, 5 and the service core 7 grip them as the balloon segments 6a, is 6b are inflated. The cut and construction of the outer walls (the cut in the length being waisted in deflated form, and the circumference in the length being banded at regular intervals) are configured to prevent excessive bulging and give as uniform girth as possible.

The inner cores! tubes 4, 5, 7 may be manufactured in continuous lengths by mobile plant working away from the earth terminal 1. The material for the cores 4, 5, 7 could be polystyrene with a low friction material-coated (eg Teflon-coated) inner wall and with the outer wall perhaps encased in tubular plastics sheeting. Other materials may also be suitable, such as for example carbon-fibre, aluminium, or, perhaps, recycled plastic (the umbilical in place being subject to lateral forces and thus suitably being adapted to safely absorb those forces). The outer balloons 6 could be manufactured from a rubberised fabric (again, perhaps utilizing recycled materials).

The overall diameter of the umbilical is selected to accommodate the planned maximum width of the load to be carried by the transfer canisters (see Figure 2B and related description below) while meeting the physics constraints to operate efficiently and effectively. The diameter of canister 15 in turn dictates the diameters of the transport tubes 4, 5 and the diameter of the balloon lengths 6 is dictated by the volume of gas required to achieve the necessary buoyancy.

The Earth Terminal The overall configuration of the earth terminal 1 is suitably as illustrated in Figure 2. This comprises firstly an entry access point! injector 8 for injecting into the pneumatic transport sub-system the transfer canisters 15 io that serve as the transporters to the near space terminal 2; and an exit access point! receptor 9 for removing the transfer canisters 15 received back to earth. These will be described in greater detail in respective sections below.

is Figure 3 shows insertion of a transfer canister 15 into the earth terminal 1 entry access point 8 of the pneumatic transport sub-system through a loading door 8a. The canister 15 is placed over a ram 11 that serves to drive the canister 15 upward, injecting it into the ascending transport tube 4 when an isolator gate valve 12 is opened as will be described in further detail later.

In addition to the entry access point 8 and exit access point 9, the earth terminal 1 also has a pump! turbines 12 to provide the primary propulsion and!or suction for the pneumatic transport sub-system. Heaters 13 are also provided for heating the gas (which may, for example, be air) in the pneumatic transport sub-system suitably both for added lift and to provide acceptable levels of warmth for passengers. Humidity control units and connection points for ancillary supplies are suitably also provided.

The Near Space Terminal Referring to Figure 2, the near space terminal 2, like the earth terminal 1, has an entry access point /injector 8' for injecting canisters 15. The near space terminal 2 injects them into the descending transport tube 5. It also has an exit access point/receptor 9' to receive canisters 15 that have come up from the ascending transport tube 4. The near space terminal 2 initially need only be like a basic flying bedstead' in form, capable of s manoeuvring / maintaining position relative to the earth terminal 1, as torsion and tension on the umbilical 3 should be kept to an absolute minimum (rendering it to be almost passive in nature).

This terminal 2 (connected and under immediate full construction) may become a basic platform for the distribution of the contents of laden canisters 15 to other units built nearby (concerned with other matters). It suitably houses a viewing gallery for visitors. Oxygen! air and ancillary supplies may be siphoned at this terminal 2 for storage and distribution and some of the pressurised gas! air in the pneumatic circuit may be is diverted into a shunt 14 to be used, via a compression valve 16 to feed into the injection! exit access point 9'.

Erecting The Umbilical Just as a pipe or cable is joined and laid over a great distance, so the umbilical may be manufactured and laid or coiled on the earth's surface with slave balloons 16 (see Figure 8) threaded onto its length at given points. Initially, the supportive balloon segments 6a, 6b would be inflated to provide the buoyancy. Then, beginning at the end of the umbilical 3 that will eventually be connected to the near space terminal 2, the slave balloons 16 are inflated and the umbilical will begin to ascend. Lifting gas can also be pumped into the cores 4, 6, 7 temporarily to provide additional lift.

Once the umbilical 3 reaches its optimum ceiling height (subject to atmospherics) it is then pulled up by means of a cable lowered from the near space terminal 2 and finally connected to that terminal.

The hinged balloon segments 6a, 6b are suitably capable of removal from the umbilical 3 (for the purposes of being repositioned on the umbilical 3 or return to earth), of being inflated and deflated, or of being partially or wholly deflated and filled with an insulating medium. Once the umbilical 3 is permanently connected to the near space terminal 2 and the inner cores 4, 5, 7 have assumed their basic functions, the umbilical 3 should then be capable of being disconnected at the earth terminal 1 for adverse weather conditions or for movement to another earth terminal 1 (see Fig la). The disconnecting end of the umbilical 3 is suitably provided with a flanged plate or annulus at that end of the tubes 4, 5 that is releasably secured to the terminal by a clamping device on the terminal. The clamping device may be hydraulically operated.

The Transfer Canister The diameter of the canister 15 (see Fig 5) will, as noted previously, be governed by the maximum width of load to be carried. This will likely be dictated by the size of basic modular panels that would suitably be used to construct the outer skin of the near space terminal 2 and all subsequent buildings constructed adjacent to the terminal. Also, the diameter of the canister 15 should suitably be such as to enable a desired number of personnel to be transported in comfort (given that the ascent or descent time, unbroken, would likely be about an hour). The diameter suitably also corresponds to the diameter of a load comprising a planned small space transport vehicle (the equivalent of a car on earth), which could arrive for immediate use on local trips between sites (in the most simple form these vehicles could be propelled along guide wires using a pedal type arrangement. The canisters 15 might also even be used to carry hazardous waste (eg for incineration by being propelled towards the sun and forgotten). The length of the canister 15 could vary greatly dependent upon laden weight.

The body of the canister 15, not being in contact with the umbilical 3, can be manufactured from different materials (dependent on what it is carrying) and might be of carbon-fibre, plastic, glass-fibre, aluminium, or even polystyrene. The canister seals 18 would be subject to friction and wear but a non combustible felt type seal that can be replaced quickly, cheaply, and regularly by means of a simple locking ring may suffice. It would also allow for the expansion, contraction, and possible distortion of the transport tubes 4, 5 and would absorb moisture to some extent. The seals must be of a type that keeps wear on the transport tubes 4, 5 to a io minimum. Canisters 15 may also be fitted with braking shoes, or expansion rings for emergency use on the transport tubes 4, 5 wall (manually/automatically operated). Such braking shoes, or expansion rings may also be used on canisters 15 equipped to carry out maintenance inspection and repair on the transport tubes 4, 5. is

The Propulsion System When connected to both terminals 1, 2 the air within the sealed pneumatic transport system is continuously set circulating using the one or more turbines 12 at the earth terminal as illustrated in Fig 2. Pressure, temperature and humidity are suitably constantly regulated. Canisters 15 with all manner of inspection! test equipment can be sent up and down prior to initial usage (variable turbine speed). Inter alia sensors in the test equipment may monitor for lean of the umbilical 3 and enable correction. It is envisaged that once the umbilical 3 is fully functional, it should be used continuously without interruption. Ascending canisters 15 would be assisted by the canisters 15 descending. Small amounts of energy may be harvested at the near space terminal 2 from wind turbines situated in the air return core between the ascending and descending transport tubes 4, 5 during those periods when no canisters 15 are present in the system. The system may also be sub-heated at the near space terminal 2 using solar energy.

The Iniector Unit The earth terminal 1 injector unit 8 illustrated in Figure 3 comprises an extension tube length of the ascending transport tube 4 extending downwardly beyond the circuit part of the pneumatic transport system. An equivalent injector unit 8' is provided at the near space terminal 2 as an extension tube length of the ascending transport tube 4 extending upwardly beyond the circuit part of the pneumatic transport system.

io The injector unit further comprises a hydraulic ram 11, the arm of the ram 11 having a perforated head which pushes transfer canisters into the transport tubes 4, 5. A canister 15 is loaded into the unit via the loading door 17 in the transport tube 4 wall. The isolator valve 12 is then opened, allowing the ram 11 to push the canister into the transport tube 4. While is this takes place, the airflow in the pneumatic transport circuit is diverted forward of the canister 15 being injected (see Fig 10). Once the canister is in place it is held in position by a simple supporting device, such as hinged arms. The supporting devicef arms suitably fold into the transport tube 4 wall as the canister 15 passes and fall back to project to support the canister 15 base as the ram is withdrawn. When the ram 11 is withdrawn the isolator valve 12 is closed. The airflow in the system is then diverted to the rear of the canister 15 and the canister 15 is subject to system propulsion, driving it up the ascending transport tube 4.

The Receptor Unit The earth terminal 1 receptor unit 9 illustrated in Figure 4 comprises an extension tube length of the descending transport tube 5 extending downwardly beyond the circuit part of the pneumatic transport system. An equivalent receptor unit 9' is provided at the near space terminal 2 as an extension tube length of the ascending transport tube 4 extending upwardly beyond the circuit part of the pneumatic transport system.

The earth terminal 1 receptor unit is equipped with an isolator valve 16 at its mouth, a compression unit 16 at its end and, in-between the two, a door 17 for removing canisters 15 in the core wall (Fig 3). Referring to Figures 4 and 9, the canister 15 in the descending transport tube 5 approaching the receptor unit 9 passes a junction area 19 of wall at a junction with a substantially horizontal linking tube length 20 that leads to the ascending transport tube 4. The wall at this junction 19 is perforated to allow the main airflow to pass in and be naturally diverted along the horizontal tube length while the canisters 15 pass by without fouling the junction 19. The airflow that enters the horizontal linking tube length 20 is then directed by a flow diverter 25 to be selectively directed to the base of the ascending transport tube 4 below a newly injected canister 15 to push the canister 15 or is diverted to bypass canister 15.

On the exterior of the junction 19 there are vertical support vanes 24 bridging between descending transport tube 5 and the horizontal tube length 20.

With the isolator valve 10 in the open position the canister 15 is able to enter the receptor unit 9, and isolator valve 10 closes as the canister 15 passes. The air trapped in front of the canister 15 is then forced against the compression unit 16 and the canister 15 is slowed to a stop by a regulated flow of the trapped air by the unit 9, and (optionally) a bristle-like lining in the tube extremity. Air passing through the compression unit 16 is returned to the main circuit of the pneumatic transport system via a secondary tube! shunt 14 equipped with a non-return valve.

Slave Balloons Referring to Figure 8, the slave balloons 21 threaded onto the umbilical 3 can simply remain in a passive buoyant state at regular intervals up to their ceiling height. Spaced thus, they may provide lift or drag on the umbilical 3 as required. They would also take on the role of facilitating the maintenance of the supporting casing balloon lengths 6, and their removal or repositioning. They would also be used to assist with the vertical lifting (umbilical 3 disconnected) and lateral movement of the umbilical 3 and near space terminal 2 (when moving between earth Terminals 1, or when lifting to avoid dangerous weather conditions etc.). Canisters 15 locked off at intervals in the transport tubes 4, 5 with lifting gas trapped between them could also assist in the same way. Slave balloons 21 locked onto the outer casing balloon lengths 6 and deflated would assist in lowering the umbilical 3, as would canisters 15 filled with ballast and sent down the descending transport tube 5 (end capped). Some balloons 6 or 21 could also be equipped with propellers to assist with the lateral movement of the umbilical 3.

is Damacie To The Umbilical As a safety measure against the risks of the umbilical 3 being punctured or severed, air-bags (like those in motor vehicles) may be built into the transport tube 4, 5 walls at regular intervals to inflate and seal them temporarily. Slave balloons 21 located above the break can descend to the break, lock on and wait to assist in the splice repair, or they can simply drop off of the end of the umbilical 3 and descend to earth. Below the break slave balloons 21 can rise to as near the break as possible and lock off, helping to maintain the vertical position, and prior to assisting in the splice repair, or, can descend on the umbilical 3. The severed umbilical 3 can also have a canister 15 locked off in the ascending transport tube 4 and be filled with a lifting gas as in the initial lift. In the worst case, even if some outer casing balloons 6 of both transport tubes 4, 5 and the tubes 4, are completely destroyed by an explosion or a collision, the upper part should simply swing free below the near space terminal 2, and the lower part (if distant from a slave balloon 21) will simply flop over and sway about.

Above 30,000ft a break is highly unlikely. The upper part of the break can be manoeuvred directly above the lower part of the break by the near space terminal 2, which can then descend to effect the splice utilising external slave balloons 21 and internal maintenance canisters 15 (from both terminals 1, 2). From a gondola 23 suspended beneath a slave balloon 21 on the exterior of the umbilical 3, cleaning up the severed ends of the umbilical 3 and splicing them together isn't out of the question (even if the repair is only temporary until a full repair is effected inside the transport tube 4, 5).

Where lightning strike risk is concerned, the umbilical 3 may be fitted with a conductor built into a ladder strip 23 on which a crawler gear or brake wheel can locate. With a suitable contour made in the fabricated inner wall of the slave balloon 21, personnel and goods could be transferred from slave balloon 21 to slave balloon 21 (ascent or descent) aided by this strip 23. As lightning strikes up as well as down, conducting the charge to earth (as opposed to insulating against strike) is probably best. However, that would not work when the umbilical 3 is disconnected from the earth terminal 1 (unless the end of the umbilical 3 is close enough to drag a conductor). If a way can be found of discharging strikes via the near space terminal 2 into space, and siphoning off the energy and storing it, then umbilicals 3 in the future could be positioned directly above storms prior to intruding and following them.

Establishing a landing in near space that anyone can set foot on will be a giant step for mankind. Until that happens only man's corporations will be taking big steps, and those steps will be governed by money and power, not by mankind. The use of umbilicals of the present invention will open up possibilities to solve many of our most pressing problems. Ascending to one near space terminal, travelling to another terminal in space and descending could be a relatively pollutant free way of travel. Craft may be permanently based in space to carry passengers and goods between terminals. Being able to despatch radio-active waste (and other hazardous waste) to space for complete disposal (by directionally ejecting it) would make nuclear power much more acceptable.

The one off cost of purchasing an umbilical system should be well within the grasp of the majority of nations and would, in time, be self-financing through paying visitors. Instead of merely being able to deliver a handful of uniquely fortunate people into space at great expense, once every so often, when all of the millions of component parts and conditions are right; the present invention will deliver any number of people including ordinary civilians at low cost, continuously, day or night, rain or shine, and bring them back again, in a matter of a few hours. Suitably commercial companies or states investing in the technology and infrastructure for this system will be obliged to provide affordable access to all as a condition for their license to purchase, build and! or operate the apparatus! system.