Abstract: An airborne vehicle lighting control apparatus and method for automatically controlling activation and deactivation of an airborne vehicle lighting system. A processor for automatically controlling the lighting system can be employed and having one or more sensors operatively connected to the processor for sensing the current flight operating mode and geographical position of an airborne vehicle. The processor can activate or deactivate lighting based on the current flight operating mode and position.

Abstract: An automatic trim system and method is disclosed for automatically trimming a flight control surface of an aircraft. A force sensor measures a force applied by a pilot to a flight control system actuator. The length of time that the force is applied by the pilot is then timed by a timer. A trim system to reduce the applied force is included on the flight control surfaces. A processor determines if trim is required if a predetermined amount of time is exceeded based on the force sensor measurement. The processor can set the trim system to the trim required therein. An airspeed sensor is used to verify that the aircraft has sufficient speed for flight. A force sensor can be utilized to measure the input force being applied by the pilot. If a pilot input force is applied to the controls and the aircraft is in a steady state, a timer can be activated.

Abstract: A fuel pump system for an aircraft engine having a booster pump that is always on during maneuvers and malfunction of primary fuel pump is disclosed. During fuel pressure loss, the boost pump and warning systems for the pilot are activated. The booster pump off and on up process are continued up to a maximum of a predefined number of times at a predetermined time interval in order to confirm that the low pressure was not due to an air bubble, or sensor glitch. The cyclic on and off process is performed only when the aircraft is at a safe altitude above ground level. If the aircraft is in close proximity to the ground and the pressure drops, the boost pump will be activated and remain on without cycling until the aircraft is at a safe altitude, or the aircraft is parked and the engine has been turned off.

Abstract: An airborne vehicle lighting control apparatus and method for automatically controlling activation and deactivation of an airborne vehicle lighting system. A processor for automatically controlling the lighting system can be employed and having one or more sensors operatively connected to the processor for sensing the current flight operating mode and geographical position of an airborne vehicle. The processor can activate or deactivate lighting based on the current flight operating mode and position.

Abstract: An automatic trim system and method is disclosed for automatically trimming a flight control surface of an aircraft. A force sensor measures a force applied by a pilot to a flight control system actuator. The length of time that the force is applied by the pilot is then timed by a tinier. A trim system to reduce the applied force is included on the flight control surfaces. A processor determines if trim is required if a predetermined amount of time is exceeded based on the force sensor measurement. The processor can set the trim system to the trim required therein. An airspeed sensor is used to verify that the aircraft has sufficient speed for flight. A force sensor can be utilized to measure the input force being applied by the pilot. If a pilot input force is applied to the controls and the aircraft is in a steady state, a timer can be activated.

Abstract: Certain embodiments of a personal computer system include an all-in-one personal computer or a panel personal computer. For example, the all-in-one computer may include a computer enclosure consisting essentially of a single panel shaped structure and a flat panel display integrally mounted inside the computer enclosure. By further example, the panel personal computer may include a flat panel display and a personal computer integrated at least substantially into one shared panel enclosure. Some embodiments of the computer have a center leg. In addition, some embodiments of the computer have substantially flat sides and faces that are substantially perpendicular to one another.

Abstract: Methods and apparatus are provided for active motion damping of a spacecraft whose attitude control system (SACS) has experienced a partial failure. In a preferred embodiment, the apparatus comprises, an attitude control processor (ACP), a motion damping controller (MDC) coupled to the ACP, a control moment gyro (CMG) comprising a gimbal loop controller (GLC) coupled to the MDC and a gimbal motor with input coupled to the GLC and gyroscopic torque output coupled to the satellite. Normally, a gimbal rate command (GRC) from the ACP passes to the GLC for execution to rotate the CMG gimbal and the coupled satellite. If the ACP output becomes invalid, the MDC assumes control and can modify CMG operation in several ways to safely decelerate a moving satellite without hazardous mechanical stress. Following such active motion damping, the CMG remains quiescent until a RESET is received whereby further valid GRCs are then executable.

Abstract: Certain embodiments of a personal computer system include an all-in-one personal computer or a panel personal computer. For example, the all-in-one computer may include a computer enclosure consisting essentially of a single panel shaped structure and a flat panel display integrally mounted inside the computer enclosure. By further example, the panel personal computer may include a flat panel display and a personal computer integrated at least substantially into one shared panel enclosure. Some embodiments of the computer have a center leg. In addition, some embodiments of the computer have substantially flat sides and faces that are substantially perpendicular to one another.

Abstract: A method for monitoring a system operating in real-time includes monitoring the system for a triggering event or events, recording data about the system to a first memory in real time prior to and/or for a set time subsequent to when the triggering event occurs, and sending the stored data from the first memory to a second memory or an interface for retrieval.

Abstract: One disclosed embodiment of a personal computer system includes a personal computer integrated entirely within a flat panel display having a single panel shaped housing. The personal computer system also includes a desktop mount integrated into a rear wall of the single panel shaped housing, wherein the desktop mount has a pivotal leg angled outwardly from the rear wall at a central region midway between left and right sides of the single panel shaped housing.

Abstract: An electronic postal scale measures the weight of an item in metric or in avoirdupois units, at the user's election. The scale also calculates a postal or shipping rate for the item, in accordance with a stored rate table defined in either metric or avoirdupois units. When the user selects a class of service, the scale determines whether there is a stored rate table for that class in the currently elected weight units. If not, the scale automatically changes to the other weight units and calculates a rate according to a stored table in those other units.

Abstract: An electronic postal scale displays operator prompt messages and generates reports in more than one language. The language to be used in selectable by the operator of the scale. In a preferred embodiment there are two languages, English and French.