38 results about "Satellite laser ranging" patented technology

The invention relates to a device for real-time high-precision monitoring of laser ranging beam pointing, including: a 45° reflector, a transmitting telescope, a right-angle combined reflector, a receiving telescope, a beam splitter, a monitoring CCD, an acousto-optic modulator, and a controllable small hole Aperture, collimating mirror, detector. The emitting laser is emitted by the emitting telescope, most of it passes through the right-angle combined reflector in the emitting light path, and part of it is reflected by the right-angle combined reflector, and is transmitted parallel to the emitting light path and opposite to the receiving telescope to the beam splitter. A small part passes through the beam splitter and is detected by the monitoring CCD, while the rest is reflected. When the acousto-optic modulator is working, the reflected beam is deflected to the edge of the controllable aperture diaphragm, which avoids light damage to the detector; when the acousto-optic modulator is not working, the laser echo can be transmitted through the controllable aperture. Aperture diaphragm, collimating mirror, to detector. The real-time monitoring of beam pointing is beneficial to the real-time aiming of detection targets in laser ranging, and promotes the development of laser ranging, especially satellite laser ranging.

The invention relates to a coorbital satellite autonomous relative position keeping method based on laser loads. On-satellite autonomous orbit determination is achieved through a navigation constellation or orbit determination is measured through a ground station, the satellite position initial reference is obtained, determination of the relative positions between two space satellites and time unification of systems are achieved by combining inter-satellite laser ranging and communication integrated loads with rotary table pointing information, a target constellation is resolved through the current position of each star of the constellation, the existing position information and the target position information are compared, the relative position keeping requirement of each star is determined, the enveloping and pose deformation requirements of each star are resolved, the change rate of a satellite orbit is changed by solar wing position adjustment and deformation and adjustment of the perturbation influence, and accordingly relative position keeping of coorbital satellites is achieved, all the stars in the constellation can run in a relative good form after the orbit is affected by perturbation, and the orbit decay influence is reduced.