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 electric to pneumatic transducer including a transducer housing with a primary converting housing section and a relay housing section. The primary converting housing section contains feedback and control electronics and an electronic feedback sensor that are electrically connected. The feedback and control electronics are adapted to be connected to an electronic signal input. The primary converting housing section also contains a nozzle and associated flapper control for controlling the output from the nozzle and the primary converting housing section also contains a bleed orifice. The relay housing section contains a relay control chamber with a positive bias spring that exerts a force on an upper control diaphragm and an associated lower control diaphragm that are in turn associated with a combined exhaust and supply valve.

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: 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 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: 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: Apparatus and method for determination of concentrations of a substance in solution in a sample by determining the time between when the substance first appears and when it disappears. The time between the appearance and the disappearance of the substance is used to determine the concentrations of the substance in a sample. The apparatus includes many elements of a flow injection analysis system but also includes a very important stirred dilution chamber that enables the apparatus to use a simplified detection system that is capable of being used over a wide range of sample concentrations. The apparatus can include a microwave digestion system and in one embodiment a continuous flow microwave digestion system.

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.