Aircraft orbit injection control method using space vector matching

A technology of space vector and control method, which is applied in the direction of aerospace vehicles, aerospace vehicle guidance devices, aircraft, etc., and can solve problems such as poor adaptability to large attitude adjustments, adjustment of engine shutdown time, and large position and speed deviations. Achieve the effects of strong engineering application value, strong adjustment ability, and strong real-time performance

Active Publication Date: 2019-03-19
THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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  • Application Information

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Problems solved by technology

[0002] Aiming at space missions for spacecraft to achieve precise orbital entry, the basic stage generally uses multi-stage engines connected in series, and the energy deviation of the engines at each stage will accumulate to the final orbital stage, which will have a large impact on the program angle control of the final stage orbital stage. Influence, especially for the spacecraft with solid engine at the base level, the engine generally adopts the exhaustion shutdown mode, and the engine cannot adjust the shutdown time of the engine according to the current actual situation, so it may

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Embodiment 1

[0029] see figure 1 As shown, the embodiment of the present invention provides a control method for spacecraft orbit entry using space vector matching, including the following steps:

[0030] 1), initialize the spacecraft state parameters;

[0031] 2) Calculate the number of elements in the current orbit of the spacecraft, the radius of the center of the earth, and the rotation angle of the current orbit relative to the standard orbit;

[0032] 3), obtain the standard orbital velocity vector that is adapted to the current orbital state according to the rotation angle of the center of the earth and the current orbit relative to the standard orbit;

[0033] 4), according to the standard orbit velocity vector and the current actual orbit velocity vector, calculate the deviation of the velocity vector, and use the deviation of the velocity vector to calculate the remaining flight time DT, pitch program angle and yaw program angle;

[0034] 5), using the calculated remaining flig...

Embodiment 2

[0037] see Figure 1 to Figure 2 As shown, the embodiment of the present invention provides a control method for spacecraft orbit entry using space vector matching, including the following steps:

[0038] 1), initialize the spacecraft state parameters;

[0039] Before the iterative calculation, it is necessary to initialize the current state parameters of the spacecraft, mainly including:

[0040] Launch latitude, longitude, elevation, shooting direction, current flight time, position, speed, orbital parameter interpolation table that changes with the center of the earth and the rotation angle of the current orbit relative to the standard orbit.

[0041] 2) Calculate the number of elements in the current orbit of the spacecraft, the radius of the center of the earth, and the rotation angle of the current orbit relative to the standard orbit;

[0042] Calculate the orbital element at the current point according to the current orbit state parameters of the spacecraft, and obta...

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Abstract

The invention discloses an aircraft orbit injection control method using space vector matching. The method includes the following steps of initiating state parameters of an aircraft, calculating the root and geocentric radius vector of a current orbit of the aircraft and the rotating angle of the current orbit relative to a standard orbit, obtaining a standard orbit speed vector which a current orbit state should have according to the geocentric radius vector and the rotating angle of the current orbit relative to the standard orbit, calculating the deviation value of the speed vector, the residual flight time DT, the pitching program angel and the yaw program angle according to the standard orbit speed vector and a current actual orbit speed vector, and conducting posture control and shutdown control through the calculated residual flight time DT, pitching program angel and yaw program angle. The invention relates to the technical field of orbit control. The method is high in real-time performance, high in guidance precision and high in orbit adjusting capacity, flight software on the aircraft is simple, and the work requirements for preparing and calculating various elements on the ground are low.

Description

technical field [0001] The invention relates to the technical field of orbit control, in particular to a control method for spacecraft orbit entry by using space vector matching. Background technique [0002] Aiming at space missions for spacecraft to achieve precise orbital entry, the basic stage generally adopts multi-stage engines connected in series, and the energy deviation of the engines at each stage will accumulate to the final orbital stage, which will have a large impact on the program angle control of the final stage orbital stage. Influence, especially for the spacecraft with solid engine at the basic level, the engine generally adopts the exhaustion shutdown mode, and the engine cannot adjust the shutdown time of the engine according to the current actual situation, so it may produce a relatively large position velocity compared with the theoretical situation Deviation, the program angle calculated by the final stage when re-planning the orbit may vary greatly r...

Claims

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Application Information

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IPC IPC(8): B64G1/24B64G1/22
CPCB64G1/22B64G1/24
Inventor 叶昌王志军蒋金龙张力黄鑫鑫郭一江马新普
Owner THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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