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725results about "Artificial satellites" patented technology

Autonomous Space Flight System and Planetary Lander for Executing a Discrete Landing Sequence to Remove Unknown Navigation Error, Perform Hazard Avoidance and Relocate the Lander and Method

An autonomous unmanned space flight system and planetary lander executes a discrete landing sequence including performing an initial velocity braking maneuver to remove velocity at altitude, coasting during which the planet surface is imaged and correlated to reference maps to estimate cross-track and along-track navigation errors and one or more lateral braking maneuvers are performed to reduce cross-track navigation error, and performing a terminal velocity braking maneuver(s) to reduce the along-track braking maneuver and remove the remainder of the velocity just prior to landing. A bi-propellant propulsion system provides a very high T/M ratio, at least 15:1 per nozzle. Short, high T/M divert maneuvers provide the capability to remove cross-track navigation error efficiently up to the maximum resolution of the reference maps. Short, high T/M terminal velocity braking maneuver(s) provide the capability to remove along-track navigation error to a similar resolution and remove the remaining velocity in a very short time window, approximately 3-15 seconds prior to touchdown. The propulsive efficiency frees up mass which can be allocated to a fuel to remove the unknown navigation errors, perform hazard avoidance and/or relocate the lander by flying it to another site or be allocated to additional payload.
Owner:RAYTHEON CO

Separable micro and nano-satellite configuration

The invention discloses separable micro and nano-satellite configuration which comprises a satellite body, a plurality of separate release sub-satellites, mechanical net claws, a flexible solar cell array and a variable-structure mechanical arm. The separable micro and nano-satellite configuration has the advantages that the integral separable micro and nano-satellite configuration is in such a configuration form that a primary satellite carries the multiple sub-satellites, and functions of separately releasing and hovering the micro and nano-satellites can be realized; the efficiency of the solar cell array can be improved owing to combined configuration comprising flexible solar wings and the variable-structure mechanical arm; mechanical net claw mechanisms are carried on the micro and nano-satellites, so that a function of capturing space targets can be realized; the separable micro and nano-satellite configuration is provided with a plurality of stereoscopic vision imaging cameras, so that a stereoscopic monitoring function can be realized; attitude maneuver and attitude stabilization of the micro and nano-satellites can be implemented by the aid of a solid miniature propulsion technology, so that the sub-satellite separate release control ability can be improved; the separable micro and nano-satellite configuration is applicable to fifty-kilogram-level micro-miniature artificial earth satellites on near-earth orbits and is also applicable to micro-satellite networking, scientific detection aircrafts and relevant micro and nano-satellite space demonstration and experiments.
Owner:NORTHWESTERN POLYTECHNICAL UNIV

Method for optimizing orbital transfer strategy of geostationary orbit satellite

The invention relates to a method for optimizing an orbital transfer strategy of a geostationary orbit satellite, which comprises the following steps of: 1, determining orbital transfer times, orbital transfer circle times and the controlled variable of each-time orbital transfer; and 2, determining time and a thrust direction in each-time orbital transfer. The process of launching the geostationary orbit satellite at present generally comprises the following steps of: launching the satellite into a highly elliptic transfer orbit with an inclination angle by using a carrier rocket; performing apogee/perigee orbital transfer for several times by using a self-contained liquid engine of the satellite, and transferring to a geosynchronous orbit; and correcting and rounding the inclination angle of the orbit to realize a geostationary orbit. For the satellite, operation for changing the transfer orbit into the geostationary orbit by performing apogee/perigee orbital transfer for several times is complex, so too many orbital transfer times is not suitable, and orbital transfer complexity and risk are prevented from being increased; in addition, factors such as the capacity of the liquid engine of the satellite, arc segment loss in an orbital transfer period, and the like are considered, so too few orbital transfer times is not suitable.
Owner:CHINA ACADEMY OF SPACE TECHNOLOGY

Multilevel fault tolerance reinforcement satellite information processing system based on SRAM FPGA

The invention provides a multilevel fault tolerance reinforcement satellite information processing system based on an SRAM (Static Random Access Memory) FPGA (Field Programmable Gate Array), and relates to satellite information processing. The invention aims at solving the problems that when the SRAM FPGA is used as a satellite information processing system, the system reliability is influenced by single event upset and latch-up effects and the like, and a satellite practical task is not combined with a protection measure. The system is realized through the following modules including a memory module, a checking and control module, a memory configuration module, a state storage Flash module, an IO/BUS module, an anti-latch power supply module and a main processing module, wherein the memory module is used for data storage and program loading of a main processing module; the checking and control module is used for single event upset effect immunization; the memory configuration module is used for storing initial configuration files and remote updating configuration files; the state storage Flash module is used for realizing the data access state; the IO/BUS module is used for realizing communication and control; the anti-latch power supply module is used for system single event latch-up effect protection and power supplying to each module; and the main processing module is used for data processing and satellite event management. The multilevel fault tolerance reinforcement satellite information processing system based on the SRAM FPGA is applied to the technical field of satellites.
Owner:HARBIN INST OF TECH
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