Orbit changing method for reducing space craft gravity loss

Abstract

The invention provides a rail-changing method which reduces the gravity loss of an aircraft, relating to aircraft rail-changing technical field. The invention comprises the steps of (1) before the rail of the aircraft is changed, rail power starting time, initial gesture and gesture angular speed are calculated on the ground; (2) the three parameters of the rail power starting time, the initial gesture and the gesture angular speed are optimized, thus leading the direction of the thrust to be always close to the speed direction of the aircraft in the rail-changing process of the aircraft; (3) the calculated parameters are input to the star; (4) the aircraft uniformly rotates according to the angular speed determined by the ground instruction parameters. The rail-changing method of the invention leads the rail-changing fuel consumption to be extremely close to the fuel consumption of the rail-changing in the speed direction and can effectively reduce the fuel consumption compared with the fixed thrust direction rail-changing method.

Description

technical field [0001] The invention relates to the technical field of spacecraft control, in particular to the technical field of spacecraft orbit change. Background technique [0002] In order to simplify the orbital design and mission analysis of satellites or spacecraft, the analysis of orbital maneuvers is usually approximated by pulse thrust. Impulse thrust assumes that the satellite's position does not change at a certain moment, and that the velocity suddenly gains a change. However, the actual satellite orbit change is limited thrust mode, that is, the engine thrust is fixed, the satellite obtains a certain acceleration under the action of the engine thrust, and a certain speed change can be obtained after a period of time, during which the satellite is still moving in orbit , the satellite position is constantly changing. Because the orbital maneuvering of the actual satellite has limited thrust, it consumes a certain amount of fuel compared with the pulse thrust...

AI Technical Summary

Problems solved by technology

The orbital maneuver of the lunar probe is carried out at perigee, and each orbital maneuver arc is longer. If a fixed thrust direction is used, the gravity loss will be greater, resulting in an increase in fuel consumption.

In order to reduce the loss of gravity, the best way is to move the thrust along the direction of the satellite’s current velocity during the orbital maneuver. However, due to the large amount of calculation required to calculate the orbit in real time on the satellite, it cannot be realized on the satellite, and the velocity direction of the satellite cannot be obtained in real time. , and the angular velocity of the change of the satellite's velocity direction near the perigee is not uniform, which brings great difficulty to the control of the satellite's attitude and pointing, so the method of changing the orbit of the velocity direction cannot be used

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