Abstract: An easy to use, and reuse, separation connector is disclosed that comprises a first component having a plurality of leaf elements with protrusions, and a second component having a recess for receiving the leaf element protrusions. The protrusions of the leaf elements are secured within the recess by a tensioned band, or in an alternative embodiment, by an expansion band; the protrusions and recess are formed so as to provide an efficient and effective load and torque bearing surface that requires minimal tension on the tensioned band, or minimal compression on the expansion band. A shearing structure is also presented that minimizes translation of the leaf elements with respect to the receiving surface. When the band is released, springs or other means urge the leaves away from the mating surface, thereby allowing for the separation of the connected items. Preferably, the leaves are hinged, allowing for ease of coupling and decoupling to the mating surface.

Abstract: The in situ remote sensing system of this invention includes a plurality of sensors that are distributed about an area of interest, and a satellite communications system that receives communications signals from these sensors. The satellite communications system determines the location of each sensor at the time that the sensor transmits its communications signal, thereby facilitating the mapping of the value of the sensed parameter about the area of interest. In a preferred embodiment, the satellite communications system transmits a trigger signal to the sensors that are within the satellite antenna's field of view, and the sensors transmit only in response to the trigger signal. The sensors may be conventional active transmitters or passive transponders that receive their operating energy from a received trigger signal. The sensing devices within the sensor may also provide the operating energy for the sensor using, for example, photocells, piezoelectrics, and thermocouples.

Abstract: An inspection satellite is deployed in proximity to another satellite. The inspection satellite contains monitoring equipment and provides diagnostic information to a earth station to facilitate diagnosis of the other satellite and its equipment. The inspection satellite includes a flight control system that maintains the probe satellite in proximity to the satellite being monitored. In a preferred embodiment, the flight control system can also maintain the inspection satellite in an orbit about the satellite being monitored, to facilitate diagnostics based on patterns of signals. The monitoring equipment in a preferred embodiment for a transponder satellite includes an ability to monitor incoming signals and to compare the emissions from the satellite to them, to determine performance characteristics of the satellite equipment being monitored, such as phase shift and gain.

Abstract: The excess space and weight capacity of a conventional geosynchronous-transfer launch vehicle is used to deploy satellites to a low-earth orbit (LEO). In a preferred embodiment, an orbit-transfer vehicle provides the navigation, propulsion, and control systems required to transport a payload satellite from a geosynchronous-transfer orbit (GTO) to a predetermined low-earth orbit. Upon entering low-earth orbit, the payload satellite is released from the orbit-transfer vehicle. To reduce the fuel requirements for this deployment via the orbit-transfer vehicle, a preferred embodiment includes aerobraking to bring the satellite into a low-earth orbit.

Abstract: A spacecraft architecture is defined that distinguishes components and sub-systems based on both functional and physical dependencies. On one side of the interface are kernel components that are both functionally and physically independent of the vehicle configuration and functionally and physically independent of the mission-specific system. On the other side of the interface are components that depend on either the spacecraft configuration or the mission-specific system. The kernel components can be included in a variety of spacecraft, independent of the spacecraft architecture and independent of the spacecraft mission. The kernel includes a communications system for communicating with an earth station, a command and data handling processor, and a power regulation and distribution system.

Abstract: A switch status sensor is provided for counting on/off events of a switch of a water meter. When an on/off event is detected by a microcontroller, the microcontroller supplies a “signature” signal, which is distinguishable from electromagnetic noise, to the switch. If this “signature” signal is detected as having passed through the switch by the microcontroller, then it can be confirmed that the switch is closed. Alternatively, if the “signature” signal is not detected as having passed through the switch by the microcontroller, then it is verified that the switch is open. Thus, the switch status sensor can distinguish between false switch events caused by electromagnetic noise and true on/off events of the switch.

Abstract: The control element according to the invention which for example can be in the form of a pushbutton switch or display element, is intended to be fastened to a front panel having at least one circular opening. It has a housing with an essentially cylindrical section and, at its front, a collar projecting radially outward and beyond the cylindrical section. The cylindrical section is provided with at least one all-around groove in which a ring of an elastically deformable material is present. When the control element is inserted into the front panel, it is fixed into the opening by virtue of the fact that a support surface of the collar rests on the front plate on the one hand and by the ring being pressed against the lateral surface of the groove by the lower edge of the opening on the other hand.