General Dynamics Corporation/convair Div.

General Dynamics Corporation

General Dynamics (Space Systems Division)

General Dynamics Corporation, Convair Division

Edward J Hujsak

LeRoy E Siden

Hans M Stocker

A method and device for protecting a first stage liquid rocket booster from impact damage and environmental damage so as to permit recovery from a sea water landing and reuse without major rehaul of the rocket engine of the booster. A cylindrical double walled structural member encircles the nozzles of the rocket engine and precludes impact damage after the booster has landed nose first in the water. A flexible water impervious sleeve means is carried within the double walled structural member and deployed prior to impact. The sleeve extends from the booster and collapses inwardly upon itself to prevent entry of sea water into the rocket engine and associated equipment.

Method and device for protecting a liquid rocket booster from impact and

The disclosure is directed to a system for recovery of liquid fuel rocket engines used in space flight. The system comprises a sphere with a normally circumferential open portion for containing a rocket engine. The sphere is fixedly attached to the space vehicle. The engine is attached to the inner surface of the sphere in a manner allowing normal engine functions including but not limited to gimbaling. The normal engine hookup is provided via disconnects on the outer surface of the sphere. A pair of sphere closure sections are carried on rails within the sphere adjacent to the normally open portion of the sphere. When the use of the engine in space flight is completed generally prior to vehicle orbit, actuation devices translate the closure sections into the normally open portion of the sphere sealing the opening thereby forming an integral closed sphere, the sphere containing the engine is disconnected from the vehicle by explosive bolts or the like and then the sphere falls from the vehicle towards earth. After reaching the earth's atmosphere, a parachute is deployed to slow the falling speed of the sphere. The sphere can be recovered by air or sea recovery and the system can be reused.

Recovery system for rocket engine

A space rail (10) having two basic elements, a box structure (12) which is configured to permit installation of payload hardware and payload services hardware along its length and a deployable back structure (14) which provides stiffness to the assembly of space rails when deployed. The box structure (10) is preferably a flat rectangular frame comprising body members (12) and the back structure (14) comprises a plurality of struts (24a-d, 30) pivotally attached to the body member (14) and to each other so as to fold into a retracted deployable position and to be deployed (unfolded) by a suitable mechanism.

Space rail for large space systems

Disclosed is an orbital space transfer vehicle comprises essentially a composite hollow cylindrical body structure enclosing a spherical oxygen tank suspended and spaced from the inner wall of the cylindrical body structure, a hollow toroidal hydrogen tank suspended from and spaced from said cylindrical body structure, a main thrust rocket engine, and an aerobrake located at the aft end of the vehicle. This arrangement provides a vehicle with a very short length, lowers the required aerobrake size and maximizes vehicle controllability that may otherwise occur due to non-uniform distribution of the propellants during operation of the vehicle. Thus disclosed is a vehicle which can fully benefit from space basing, easily maintained while stationed in orbit, and transportable in a fully assembled state from earth to low earth orbit. Also disclosed is a space station with which the orbital transfer vehicle may cooperate while in space.

Space based orbit transfer vehicle

Disclosed is a single control thruster having the expanded capability of operating at various thrust levels and more than one propellant fluid so that the number of control thrusters for a maneuvering vehicle can be reduced to one third from that now required for appropriate maneuverability in space, resulting in large cost savings and improved reliability. Also disclosed is a 'plug in' package with control thruster which can be removed from the vehicle and replaced to make the vehicle easily maintainable.

Space maneuvering vehicle control thruster

A deployment system for a deployable truss structure particularly adapted to space applications which has high structural efficiency and can be remotely operated in a controlled, sequential manner. The truss in its deployed configuration exhibits a 'diamond' cross section. Each of the four sides of the structure is essentially a 'Warren' truss. Diagonals on the opposite sides of each diamond incorporate a mid-span hinge and the other two diagonals are rigid tubes. When packaged, all elements of the truss are folded so that they are parallel to one another and contained between two guide rails. The guide rails are located on either side of the diamond truss. The horizontal strut connection points or nodes are fitted with rollers that are locked in the guide rails for movement therealong. The deployment initially lifts upright truss members to the vertical position, forming the basic diamond shape of the truss. A traveling deployment mechanism on each guide rail including unlocking and transport devices on an endless tape unlocks the node of the first truss bay and carries it to its deployed length. Sequentially, the tape is reversed and the devices return to the next node, to unlock it, and deploy each next bay. As the truss grows, the bays are cantilevered beyond the guide rails. The deployment mechanism can be manually operated through hand-held controllers or by an automatic programmed system, as desired.

Mechanism for deploying a deployable truss beam

A two-piece hinge which is spring biased in both its folded position and in its unfolded or deployed position to provide built-in deployment power for structural members and which is provided with trigger/locking mechanisms which are held in an unlocked position when the hinge and the structural members are in their folded position and which triggers and releases the locking mechanisms to lock the hinge in its unfolded or deployed position for positive locking capability. Two trigger-locking mechanisms are used for redundancy.

Hinge for deployable structures self locking hinge

A satellite maintenance system for satellite stations orbiting in the geosynchronous corridor comprising a roving satellite maintenance vehicle capable of operating autonomously in the geosynchronous corridor and containing replacement hardware in modular form by which maintenance operation can be made on the satellite station by the exchange of one module for another thereby repairing or upgrading the hardware in the satellite station to prolong its useful life. The maintenance vehicle is capable of operating in the corridor for prolonged periods of time in a standby mode and capable of proceeding, on command, to the satellite station to perform the maintenance function automatically.

Roving geosynchronous orbit satellite maintenance system

A device for docking or joining large structures or vehicles in earth orbit under automatic and remote sensing and control. A thin flexible boom extending from one vehicle contacts the inner surface of a large open cone on the other as the two vehicles approach each other. The conical surface guides the boom end towards the apex where a reel for drawing in the boom engages the boom. As the boom is drawn in, and the vehicles come into close proximity, a mechanical latch is engaged for final rigidizing and securing.

Space platform docking device

A system for joining or docking large structures in space under remote, automatic control. As the two structures approach each other, a telescoping rigid boom on one structure is extended toward a socket on the other. The boom mount includes mechanisms providing a multidegree of freedom in pointing the boom. The end of the boom is directed into the socket whereupon a locking device holds it in place. Damping apparatus damps the relative motion between the structures. Boom retraction brings the structures together so that a final latching device can clamp the structures rigidly together.

Growing community of inventors

La Jolla, CA, United States of America

Edward J Hujsak