Abstract: A timing correction system for fast PN acquisition is provided. The system includes a signal sampler for testing any incoming signal and a real-time clocker coupled to the signal sampler. A parallel correlator is coupled to the real-time clocker for searching for a PN sequence and a burst detector is coupled to the parallel correlator. A chip timing corrector is coupled to the burst detector and a processor is coupled to the chip timing corrector for determining signal timing.

Abstract: A method is disclosed for directing an antenna mounted in a restricted radome on an aircraft. The method can include the operation of determining whether the antenna is directed in a keyhole. A further operation can involve controlling the antenna using an elevation gimbal and an azimuth gimbal when it is determined the antenna is directed outside the keyhole. Another operation can include directing the antenna using an elevation, azimuth, and cross elevation gimbal when it is determined the antenna is pointing in the keyhole.

Abstract: A technique for boresighting an antenna mounted on a moving platform is described. The technique uses a concurrently moving calibration target. Target navigation data and platform navigation data are used to compensate for movement of the target and the platform. The antenna pointing direction is biased in a direction which provides a best signal quality, and the bias used to determine antenna boresight calibration factors. The boresight correction factors can be used for open loop pointing.

Abstract: A method is disclosed for directing an antenna mounted in a restricted radome on an aircraft. The method can include the operation of determining whether the antenna is directed in a keyhole. A further operation can involve controlling the antenna using an elevation gimbal and an azimuth gimbal when it is determined the antenna is directed outside the keyhole. Another operation can include directing the antenna using an elevation, azimuth, and cross elevation gimbal when it is determined the antenna is pointing in the keyhole.

Abstract: An antenna positioned (with rough alignment) on an aircraft is calibrated in position and orientation relative to the inertial navigation system of the aircraft by measuring the corresponding position and orientation parameters of the aircraft and a reference target relative to the Global Positioning System (GPS) and calculating differences between azimuth and elevation parameters of the target measured by the antenna control system and corresponding roll, pitch and heading parameters measured by the aircraft system, thereby providing bias parameters for the antenna output in the coordinates of the inertial navigation system.

Abstract: A method for determining a pre-selected point-to-point separation between a first craft C1 and a second craft C2 is provided. The method includes the step of providing two laser devices, L1, and L2, onboard each craft, C1 and C2, respectively. Then determining a desired skin location vector S2 of craft C2 in L2 coordinates and translating the skin location vector S2 to L1 coordinates; and then determining skin separation between crafts C1 and C2 in accordance with the translated skin location vector.

Abstract: An apparatus for an improved antenna tracking system for antennas mounted on an unstable platform. The system comprising a directional antenna, an attitude heading reference system (AHRS) mechanically connected to the at least one directional antenna, a self-scan acquisition and tracking method and an antenna controller connected to the AHRS.

Abstract: A system and method for determining the position of an aircraft. An aircraft signal is received by a first antenna and a second antenna, the first antenna being at a known baseline distance from the second antenna. A processor is used to calculate the time difference of arrival range between the second antenna and the aircraft using a common time reference signal. The position of the aircraft is determined by a position determinator based upon the baseline distance between the first and second antennas, the range between the first antenna and the aircraft, and the time difference of arrival range between the second antenna and the aircraft.

Abstract: An instrument for indirectly measuring the attitude of a moving aircraft includes three accelerometers, a GPS radio receiver, an electronic estimating module, and an electronic output module. The three accelerometers indicate three accelerations of the aircraft respectively along three aircraft body axes. The GPS radio receiver receives from GPS satellites the position and velocity of the aircraft along an earth fixed axis. The electronic estimating module estimates a vector such that a series of aircraft position changes along the three body axes that are caused by the measured accelerations, times the vector, approximately matches a corresponding series of position changes along the earth fixed axis as given by the receiver. The electronic output module generates a visual display of the roll, pitch, or heading of the aircraft by performing trigonometric functions on the vector.