GB2362145A

GB2362145A - Re-usable space vehicle launch system using air-buoyant craft

Info

Publication number: GB2362145A
Application number: GB0021565A
Authority: GB
Inventors: Marin Dimitrov Guenov
Original assignee: Individual
Current assignee: Individual
Priority date: 2000-05-08
Filing date: 2000-09-04
Publication date: 2001-11-14
Also published as: GB0021565D0; GB0010862D0

Abstract

The reusable space launch system consists of an engine propelled Lighter-than-Air (LTA) craft 1 and a launch platform 2, which accommodates existing or newly built space launch vehicles 3. The air-buoyant vehicle 1 is preferably a rigid or a semi-rigid airship. Platform 2 is an integral part of the LTA craft 1. Alternatively, platform 2 is a self-contained module, to which the launch vehicle 3 is either pre-assembled or is mated with the already mounted launch platform, prior to takeoff and space launch. After reaching the desired launch point at the required launch altitude, the space launch vehicle is released from platform 2 and ascends to orbit. After the launch is completed, the space launch system descends back to the landing site and is moored securely.

Description

2362145 REUSABLE SPACE LAUNCH SYSTEM This invention relates to a system

and a process for launching existing or newly built space launch vehicles. These in turn can carry payloads and perform manned or unmanned missions.

Space launches are very expensive and damaging to the environment processes in respect to noise, vibration, and especially to pollution.

An object of this invention is to provide a reusable system, which delivers a cheaper and environmentally cleaner space launch process.

A further object of this invention is to provide a powered air-buoyant system capable of launching space launch vehicles, which in turn can deliver payloads to earth's orbit or deeper space destinations.

Accordingly, this invention provides a space launch system consisting of a launch platform and a powered Lighter-than-Air (LTA) craft.

A preferred embodiment of the invention will now be described with the reference to the accompanying drawing, in which:

FIGURE 1 shows a side elevation of the space launch system concept.

FIGURE 2 shows an alternative preferred embodiment of the space launch system.

FIGURE 3 schematically illustrates the space launch process carried out by the reusable space launch system of the invention.

FIGURE 4 is an example of an alternative embodiment of the reusable space launch system, which complies with the spirit and scope of the invention.

As shown in Figure 1, the launch platform 2 is attached to the LTA craft 1. The space launch vehicle 3 is mounted on the launch platform 2.

The LTA craft 1 is an air-buoyant vehicle, preferably embodied as a manned, large airship having vectored trust provisions for establishing positive attitude and translational movement control at all air speeds from and above zero. The requirements for high altitude and fairly large payload can be fulfilled best by a rigid airship structure, which is an elongated streamlined truss structure, within which, separate gas cells are contained internally along its length. The truss structure forms a skeleton tube, rounded at the nose and tapered at the tail to produce the streamline form required for least resistance to motion. The truss 2 structure is covered by a strong fabric. A semi-rigid airship containing stiffened keel only or possibly a non-rigid type airship might also be utilised as LTA craft.

The launch platform 2 is of modular construction, capable of accommodating space vehicles of different sizes. The launch platform may contain equipment for hoisting, securing and releasing the space launch vehicle and also equipment related to the space launch vehicle's operation, such as nitrogen purge/cooling reservoir, HVAC and avionics pallets, and (or) other types of equipment. The launch platform 2 in Figure I forms an integral part of the LTA craft I and functions as a silo enclosing the space launch vehicle 3. Alternatively, the space launch vehicle 3 can be externally mounted as shown in Figure 2, which represents another preferred embodiment of the space launch system, in which platform 2 is a self-contained module. In this case the space launch vehicle 3 is mated with the platform 2 and then the whole assembly is mounted on the LTA craft 1 prior to takeoff. Alternatively, the launch platform 2 is mated with the LTA craft I first, and then the space launch vehicle 3 is mated with the launch platforin 2.

The space launch system has its own control, navigation and propulsion systems, enabling it to be manoeuvred in the air. A preferred embodiment of the propulsion system will have provisions for establishing controlled vectored trust forces along the three space axes of the degrees necessary to establish and maintain a level of optimum altitude and airspeed, required during the period of launching the space launch vehicle and also during a normal flight. The same capability of the propulsion system may be required for manoeuvring on approach to the landing/mooring station and during takeoff.

The launch process is shown schematically in Figure 3, starting from the bottom of the figure. The LTA craft is moored securely to a ground-based or sea-based mooring station. The space launch vehicle 3 is mated with the platform 2, in the case of platform 2 being integral part of the LTA craft 1. Alternatively, the platform and the space launch vehicle are preassembled and then are mated with the LTA craft. Another option is that the launch platform 2 is mated with the LTA craft I first and then the space launch vehicle 3 is mated with the launch platform 2. The mating process is assisted by an autonomous lifting device, or alternatively, by a hoisting system, which is mounted on, or is part of the platform 2, or the LTA craft I itself. After the mating is complete, the LTA takes off. The space launch system reaches the desired launch altitude due to the lifting force provided by the LTA craft, which can be a combination of the craft's buoyancy, aerodynamic lift due to the shape of the LTA craft, and the craft's propulsion system. After the desired launch point at the required altitude is reached, the space launch vehicle is released from platform 2. The engines of the space launch vehicle ignite and it starts its ascend to orbit. In some alternative embodiments of this invention, the space launch vehicle may be launched directly from the launch platform, instead of 3 being released and dropped first. After the launch is completed, the space launch system descends back to the ground-based or sea-based station. On approach to the station, the space launch system is manoeuvred into position and is moored securely.

The launch process is envisaged to take place predominantly within the troposphere and the tropopause, but is not limited to these.

The size of the LTA craft is such, so that the sudden weight loss due to the release of the space launch vehicle does not violate the allowable lightness of the airship.

It should be understood that the foregoing disclosure relates only to some typical embodiments of the invention and that numerous modifications or alterations may be made therein without departing from the spirit and scope of the invention as set forth in the appendant claims. An example of an alternative embodiment of the same invention is shown in Figure 4.

1 4

Claims

1, An air-buoyant reusable space launch system is claimed.

2. A powered air-buoyant craft, as part of the space launch system, as claimed in Claim 1.

3. A launch platform, as part of the space launch system, as claimed in Claim 1.

4. An air-buoyant reusable space launch system as claimed in Claim 1, which can be moored or otherwise secured to a ground-based or to a seabased station.

5. An engine propelled, lighter-than-air craft, as claimed in Claim 2, which is preferably an airship, as part of the space launch system, as claimed in Claim 4.

6. A launch platform, as claimed in Claim 3, which is an integral part of the airbuoyant craft, as claimed in Claim 5, with which platform the space launch vehicle is mated prior to takeoff, or alternatively, the launch platform is a self-contained module, to which the launch vehicle is either pre-assembled or is mated with the already mounted on the air- buoyant craft launch platform, prior to the space launch system's takeoff.

7. A reusable space launch system, as claimed in Claim 4, incorporating a powered air-buoyant vehicle, as claimed in Claim 5, and a launch platform, as claimed in Claim 6, capable of accommodating existing or newly built space launch vehicles, which are lifted to and released at a launch point of a required launch altitude.

8. A space launch process, in which the reusable space launch system, as claimed in Claim 7, takes off and reaches a desired launch point at a required launch altitude, where the space launch vehicle is released and launched, after which event the space launch system descends to the ground-based or sea-based station, where it is moored or otherwise secured as claimed in Claim 4.

9. A reusable space launch system substantially as herein described and illustrated in the accompanying drawing.