Abstract: A three dimensional flexible assembly of integrated circuits and method of fabricating the assembly of circuits including a folded flexible substrate with integrated circuit chips. The invention has provisions for allowing mechanical and electrically functional attachment of integrated circuit chips to one or both sides of the flexible substrate using flip chip assembly techniques. In addition, a rigid package substrate is provided upon which the folded substrate is secured with the associated chips. The chips are electrically connected to the flexible substrate and the flexible substrate is in turn electrically connected to the rigid substrate. A cover is also provided that covers and protects the flexible substrate and the associated chips as well as a portion of the connected rigid package substrate. In an additional embodiment, the cover and rigid substrate are omitted and instead the combined folded flexible substrate and integrated circuit chips are encapsulated with a suitable compound.

Abstract: A three dimensional flexible assembly of integrated circuits and method of fabricating the assembly of circuits including a folded flexible substrate with integrated circuit chips. The invention has provisions for allowing mechanical and electrically functional attachment of integrated circuit chips to one or both sides of the flexible substrate using flip chip assembly techniques. In addition, a rigid package substrate is provided upon which the folded substrate is secured with the associated chips. The chips are electrically connected to the flexible substrate and the flexible substrate is in turn electrically connected to the rigid substrate. A cover is also provided that covers and protects the flexible substrate and the associated chips as well as a portion of the connected rigid package substrate In an additional embodiment, the cover and rigid substrate are omitted and instead the combined folded flexible substrate and integrated circuit chips are encapsulated with a suitable compound.

Abstract: Spacecraft structure for use in the construction of the outer wall of a spacecraft. The construction of the outer wall of the spacecraft includes a hollow cellular honeycomb material that is sandwiched between a thin outer curved solid panel and a thin solid inner panel that has at least a portion that has a substantially flat inner surface. The inner and/or outer panel have provisions for mounting at least a portion of the payload for the spacecraft utilizing a series of inserts secured to the inner or outer panel. The outer and/or inner spacecraft wall panel structure can also include heat pipes for use in heat transfer. In one embodiment of the invention the outer panel also includes a series of substantially flat surfaces. The invention also includes the method of construction of the spacecraft structure and its method of use.

Abstract: An auxiliary computer system for use on a vehicle that has a main computer. The computer system includes a cartridge computer that is removable from the vehicle and a receptacle in the vehicle for receiving the cartridge computer that is called a data transfer unit. The data transfer unit is electrically connected to the vehicle's normal or main computer. The computer system also includes a stationary station that is located outside of the vehicle. The cartridge computer is inserted into this stationary station for programming and testing of the cartridge computer and for reviewing information in the cartridge computer that was accumulated while the cartridge computer was in the vehicle. The method of using the auxiliary computer system is also set forth. The auxiliary computer system and method are particularly useful in connection with aircraft and spacecraft that have a main computer.

Abstract: A sphere and cable deployer apparatus for deploying a cable and associated spheres from a vehicle such as a spinning satellite. The sphere and cable deployer apparatus has a drum for storing the cable that is driven by a drive shaft and gears form a drive motor to deploy the cable and sphere away from the satellite. The drive motor also drives a drive roller through a series of gears and clutch that applies tension to the cable as it is being unwound from the drum. The sphere and cable deployer apparatus also has a housing with an outer and inner pair of shell-like halves that pivot outward due to spring forces to release the spheres. Each pair of pivoting housing halves also provide a storage compartment for a short cable portion that is attached to that sphere.

Abstract: An integrated circuit package that includes three base substrate support members. One base substrate support member is rigid and has two sides and the other two base substrate members are flexible and are located adjacent each side of the rigid base substrate support member. Each flexible base substrate support member has an inner surface and a series of flip chips are located between the inner surfaces of the flexible base substrate support members and the sides of the rigid base substrate support member. The three base substrate support members are electrically connected together and a termination connection is provided at one end of the assembly. In addition, logic chips are provided that are located adjacent the connector for controlling the various flip chips.

Abstract: Spacecraft structure for use in the construction of the outer wall of a spacecraft. The construction of the outer wall of the spacecraft includes a hollow cellular honeycomb material that is sandwiched between a thin outer curved solid panel and a thin solid inner panel that has at least a portion that has a substantially flat inner surface. The inner and/or outer panel have provisions for mounting at least a portion of the payload for the spacecraft utilizing a series of inserts secured to the inner or outer panel. The outer and/or inner spacecraft wall panel structure can also include heat pipes for use in heat transfer. In one embodiment of the invention the outer panel also includes a series of substantially flat surfaces. The invention also includes the method of construction of the spacecraft structure and its method of use.

Abstract: Deployment apparatus for use in deploying an articulating structure. The deployment apparatus includes two pivotally connected hinge members and a spring that biases the hinge members in their open or deployed positions. An attenuator is also connected to one of the hinge members that prevents oscillatory movement between the hinge members as they are assuming their deployed positions and a cam member and a lobe on one of the hinge members lock the hinge members in position together as the hinge members are being extended to their deployed positions. The attenuator is adjustable and can be used to precisely fix the position of the deployed hinge members. The deployment apparatus is particularly suited for a wide variety of spacecraft applications where it can be used to extend spacecraft structures such as solar panels.

Abstract: A sphere and cable deployer apparatus for deploying a cable and associated sphere from a vehicle such as a satellite. The sphere and cable deployer apparatus has a drum for storing the cable that is driven by a drive shaft and gears form a drive motor to deploy the cable/sphere away. The drive motor also drives a drive roller through a series of gears and clutches that applies tension to the cable as it is being unwound from the drum. The sphere and cable deployer apparatus also has a sphere housing with two shell-like halves that pivot outward due to spring forces to release the sphere. The pivoting housing halves also provide a storage compartment for a short cable that is attached to the outer surface of the sphere. The pivoting housing halves are held in place by two cables that are under tension and associated pins that fit in holes in the housing halves and are released by cable cutters that cut the cables.

Abstract: An integrated circuit package that permits high density packaging of circuit chips. The integrated circuit package has a base substrate support member with an upper and a lower surface. A cavity is located in its upper surface and a similar cavity is located in its lower surface. Two circuit chips are located in each cavity that are connected together in back to back relationship. The cavities are closed or sealed by lids that are bonded to mounting surfaces that are located on the base substrate support member and surround the cavities. A series of terminating leads are located on two sides of the base substrate support member that are electrically connected to the circuit chips. A single cavity embodiment is also set forth that is designed for use when a lesser density is acceptable or desired.

Abstract: A space utility conduit for use in space structures such as space stations. The space utility conduit includes a plurality of substantially identical interconnectable conduit segments or modules. Each module contains a plurality of utility lines for transporting a fluid or electricity or the like throughout the space structure. The modules have a lazy S-shape that enables them to be easily installed and removed from the space structure. The S-shaped module is rotatably connected to the space structure prior to it being connected to adjacently located modules. A module is also provided that allows access to the utility lines through a connector or port that is connectable to a connector located exterior to the space structure.

Abstract: A spacecraft thermal disturbance control system for controlling the torque exerted on the main portion of a spacecraft as a result of a thermal gradient being applied to a portion of the spacecraft that projects from the spacecraft's main portion. The spacecraft thermal disturbance control system includes a network of distributed temperature sensors located on the surfaces of the projecting portion of the spacecraft, a microcomputer operatively connected to the temperature sensors for receiving temperature information from the temperature sensors and a reaction wheel assembly operatively connected to the microcomputer. The microcomputer provides command signals to the reaction wheel assembly based upon temperature information received from the temperature sensors to cause the reaction wheel assembly to generate a torque that counteracts the torque exerted on the main portion of the spacecraft as a result of the thermal gradient applied to the projecting portion of the spacecraft.

Abstract: A change of state coupling for controlling the rotation of a rotatable shaft in a housing through the application of heat. A disk is secured for rotation with the portion of the shaft that is located within the housing. Heaters are also located within the housing and a liquid predetermined temperature change of state material is located in the housing around the disk and the heaters. The predetermined temperature change of state material for use in the housing is selected for a melting point that insures that the predetermined temperature change of state material is solid at the temperature to which the housing is usually exposed. However, when heat is applied to the predetermined temperature change of state material by the heaters the normally solid predetermined temperature change of state material becomes liquid and thus permits the rotatable shaft to rotate within the housing.

Abstract: A redundant fluid coupling with two coupling assemblies adapted to engage each other and permit fluid flow between the coupling assemblies when they are connected. Each coupling assembly has two functionally independent valves for closing off the fluid flow from the coupling assembly when the coupling assemblies are disconnected. The independent valves are reciprocally operated by coil springs and since they are functionally independent, the failure of one valve of the coupling assembly to operate will not affect the operation of the other valve. The interior portions of each coupling assembly are pivotally mounted which permits the coupling assemblies to be connected together even though they may be offset from each other and/or form an angle with each other.

Abstract: A method for generating power and a power supply for use in the atmosphere on Mars that use the Martian atmosphere as a working fluid. The power supply has an open Brayton cycle combined turbocompressor and turbogenerator that use the Martian atmosphere for their operation. The Martian atmosphere working fluid picks up heat derived from a nuclear heat source that transfers the heat to the working fluid by laminar flow heat exchange. The combined turbocompressor and turbogenerator have provisions for separating dust from the dust laden Martian atmosphere and for operating with any residual Martian atmospheric dust that is ingested into the combined turbocompressor and turbogenerator. Reliability of operation is achieved by having two functionally separate power operating units that each have their own combined turbocompressor and turbogenerator and by only using one power unit at a time.

Abstract: A spacecraft connector for making an electrical or similar connection with a spacecraft. The connector has on board portion that is attached to or forms part of the spacecraft and an externally located portion. Both the on board portion and the spacecraft portion have paired hook shaped portions that are adapted to contact each other in a manner that permits the connection and disconnection of the connector. The connectors provide an interface without exerting undue forces upon the spacecraft.

Abstract: A recorder for recording and playing back information. The recorder is particularly useful in vehicles such as aircraft and space vehicles. The recorder has no moving parts and has a plurality of power levels. The recorder has the capability of detecting errors in its memory and to avoid using portions of the memory that have errors. The recorder has multiple channels that can be programmed for input or output use. On demand memory assignment capability permits maximum use of the memory array.