31results about How to "Extended life on orbit" patented technology

The present invention provides an on-orbit performance adjustment and compensation method and system of a spacecraft propulsion system, the method comprising: step 1: setting multiple pressure sensors and multiple parallel orbit control self-locking valves on the orbit control pipeline; step 2: Through the stand-alone liquid flow debugging of the rail-controlled self-locking valve, the flow resistance value of a single rail-controlled self-locking valve is obtained respectively; Step 3: Make the ground adjustment value of the inlet pressure of the oxidant path and the fuel path equal when the rail-controlled engine is working; Step 4: The rail-controlled self-locking valve When debugging the liquid flow of a single-machine control engine, ensure that the accuracy of the engine mixing ratio meets the requirements; Step 5: During the orbital flight of the propulsion system, obtain the actual measured value of the engine inlet pressure during the ignition of the orbit-controlled engine; Step 6: Calculate the inlet pressure of the oxidizer circuit and Compared with the actual measured value of the inlet pressure of the fuel line, the on-orbit performance adjustment and compensation strategy is implemented as needed. The invention can actively adjust and compensate the mixing ratio of the orbit control engine within a certain range, and improve the utilization rate of the propellant.

The invention discloses an orbit control strategy on-orbit correction method and system based on thruster deviation estimation. The method includes: separately obtaining the positions of the center of mass of the entire satellite, the first orbital thruster and the second orbital thruster relative to the layout system information; and, obtain the thrust vector directions of the first orbital control thruster and the second orbital control thruster; perform on-orbit identification, and determine the generation of the first orbital control thruster and the second orbital control thruster according to the on-orbit identification results The torque; construct the disturbance torque evaluation function; solve the disturbance torque evaluation function, determine the minimum value of the disturbance torque evaluation function, and calculate the jet pulse width; perform orbit control according to the calculated jet pulse width. The invention adopts the energy optimal principle to update the orbit control thrust distribution strategy on the orbit, and realizes the minimization of the orbit control interference.

The invention discloses a water-based propulsion system and method applied to high-orbit satellites, wherein the system includes a power supply, a water tank, a static water supply proton exchange membrane electrolytic cell, a hydrogen-oxygen management system, and a 100-new level gas-hydrogen-oxygen rail control engine, cow-level gas hydrogen oxygen attitude control engine. The invention solves the problem that the hydrogen-oxygen gas is difficult to manage for a long time in the space environment and the problem that the equivalent mixing ratio of the hydrogen-oxygen gas is difficult to efficiently utilize, and improves the engineering practicability of the hydrogen-oxygen propulsion system on the space flight platform.

The invention discloses a dielectric barrier discharge virtual cathode arc thruster, which includes a metal sleeve, a sealing member, an air inlet, a cathode, an anode with a nozzle, the cathode is a virtual cathode, the virtual cathode is a metal cylinder with a certain length, and the virtual cathode One end is fixed with a glass medium by sintering. The invention sinters and fixes the glass medium on the top of the virtual cathode of the cylinder, which can avoid the ablation effect of the arc propeller on the cathode and anode during the working process, greatly prolong the on-orbit life of the propeller, and improve the practicability of the arc propeller.

The invention discloses a low-thrust long-term position keeping method for a geostationary orbit satellite, which establishes the average orbital motion model of the satellite orbit in-plane and out-of-plane through spherical coordinates; and gives the in-plane and out-of-plane motion model of the geostationary orbit satellite through the phase plane analysis method. Long-period motion law; on this basis, by selecting the fixed-point position maintenance window of the geostationary orbit satellite, the periodic motion trajectory of the satellite in the uncontrolled state within the fixed-point window is obtained, that is, the trajectory of the drift segment; the small thrust control law is designed to obtain satellite control. The trajectory of the motion under the state, that is, the trajectory of the thrust section, makes the trajectory of the thrust section and the trajectory of the drift section form a closed-loop trajectory, thereby completing the long-term position keeping of the geostationary orbit satellite with low thrust.

The invention provides a pluggable satellite thermal control system, which includes an operating robot, a heat insulation component and a heat dissipation component. The operating robot is connected to the surface of the satellite main body for clamping and installing the heat insulation component and the heat dissipation component; the heat insulation component is arranged on the sun receiving surface of the satellite main body, and is connected to the surface of the satellite main body through a standard interface; and the heat dissipation component is arranged on the The back side of the satellite body is connected to the surface of the satellite body through a standard interface.

The invention discloses a method for determining mounting parameters of orbit control engines of satellites. The method includes determining a mounting position of each engine by the aid of included angles alpha<E>, beta <E> and gamma <E> among a normal line O<m>X<m> of an accurate measurement mirror of the engine and an axis O<sc>X<sc>, an axis O<sc>Y<sc> and an axis O<sc>Z<sc> of a mechanical coordinate system of the corresponding satellite and coordinates x<E>, y<E> and z<E> of the center O<m> of the accurate measurement mirror of the engine on the axis O<sc>X<sc>, the axis O<sc>Y<sc> and the axis O<sc>Z<sc> of the mechanical coordinate system of the satellite. The method has the advantages that change conditions of mass centers of the satellites and thrust vectoring thermal marking results of the engines are comprehensively considered, so that the mounting parameters of the engines can be optimally determined, disturbance torque generated in orbital transfer periods of the satellites can be reduced, satellite propellants can be saved, and the in-orbit lives of the satellites can be prolonged; thrust of each engine points to the average mass center of the corresponding satellite in the corresponding orbit transfer period, so that counterweights for the satellites can be reduced or can be omitted, and the effective load weight of each satellite can be increased.

The invention provides a satellite orbit control engine installation optimization method based on a genetic algorithm. The method comprises the following steps that (1) an objective function of the engine installation optimization is determined according to the requirement of a control system on the satellite layout; (2) according to the engine geometrical parameters and the installation requirements, a constraint function of the engine installation optimization is determined; (3) an AMTLB genetic algorithm toolkit is used for carrying out engine installation parameter optimization. The satellite orbit control engine installation optimization method has the advantages that the interference moment in the orbital transfer period is further reduced, so the satellite fuel is saved, and the satellite on-orbit life is prolonged.

The method for optimizing the installation parameters of spacecraft orbit-changing engines based on the Runge-Kutta algorithm firstly defines each coordinate system, and then establishes the mathematical model between the undetermined coefficients and the theoretical circle center A of the engine installation flange to the theoretical circle center C of the engine installation flange, Calculate the vector from the center A to the target point T, the vector from OS to the center A, the engine thrust vector FEB and the position vector of the action point, the vector from the center A to the target point T, the vector from the center A to the engine thrust vector action point P, and the engine thrust vector Thrust vector and the vector from the engine thrust vector action point P to the target point T, after solving the undetermined coefficient, obtain the installation angle and installation position, the present invention constructs the mathematical model of optimal design, and solves the engine under the premise of satisfying the constraint conditions. The optimal value of the installation parameters satisfies the requirements of the optimization of the installation parameters of the spacecraft orbit change engine to the greatest extent.

The invention discloses an overcharge protection device applied to an S4R-type circuit. The overcharge protection device comprises an S4R charge module, a discharge adjusting module, a balance module and a lower computer module, wherein the S4R charge module carries out voltage control of a whole lithium battery pack, maximal voltage control of single lithium batteries and overcharge current control; meanwhile, the charge states of the lithium batteries are monitored and controlled; control parameters can be changed through the lower computer module; a BOOST mode is adopted by the discharge adjusting module; meanwhile, the discharge adjusting module comprises a busbar voltage overvoltage and undervoltage protection circuit and an output current limiting protection circuit; the balance module provides sampling and power-balancing loops and logic control interfaces of the single lithium batteries and prevents overvoltage of the single lithium batteries; logic control of the balance module is achieved through the lower computer module; the lower computer module comprises a lithium battery temperature control module and a lithium battery charge and discharge management module; and an input signal required by a lower computer is provided by an analogue collection module.