38 results about "Satellite laser ranging" patented technology

The invention discloses a laser receiver system of low yawp and constant temperature. The collimating lens (1), the light filter (2), the angle reflector (3), the photoelectric receiver (5) are set inthe cylinder (0) from the right to the left. The CCD (4), the temperature adjustment system (6) and the transmission gear (7) are set on the top of the cylinder; the transmission gear (7) includes thefirst transmission gear (7A) and the second transmission gear (7B); the light filter (2) is connected to the first transmission gear and the reflector (3) is connected to the second transmission gear (7B); the position of the CCD is correspond to the angle reflector (3). The invention has the function of constant temperature, light filter and light tine adjustment. So it can be used for the lidar , the satellite laser ranging, the spacecraft tracking, the stellar tracking observation and the space fragment dynamic tracking.

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 method for confirming one-way distance in satellite laser ranging (SLR), which comprises the following steps of: acquiring SLR data by utilizing an SLR telescope; and calculating relatively accurate uplink or downlink distance in laser ranging by utilizing a measurement value. Particularly, when a track is confirmed by using single-station ranging and angle measurement,a complete vector having accurate length (ranging value) and accurate direction value in space is needed, and the calculating method of the invention is quite applicable. In short, the method for calculating the one-way distance is more explicit in physical significance and clearer in space geometry.

This invention discloses a real time calculation method for multi-pulse fuzziness in the distance test of satellite laser, which utilizes the global information got in real time and the extrapolate satellite theory orbit to compare it with the actual test result to determine the true value from multiple fuzzy values, 1, getting observation data of part of SLR observation stations of the globe and instant star calendar from the network, 2, utilizing relative software and instant observation data to compute the satellite theory distance value of the latter period of time, 3, applying the precise orbit extrapolation method to select a correct value from the multiple values.

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.