De-orbit braking closed circuit guidance method satisfying constrains on reentry angles and flying ranges
A technology of off-orbit braking and re-entry angle, applied in three-dimensional position/channel control and other directions, which can solve the problems of initial position error, initial speed error, low range control accuracy, inability to guarantee range accuracy, and limitations in improving accuracy, etc.
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[0043] Suppose a spacecraft uses a constant thrust rocket engine to de-orbit from an initial circular orbit at a height of 300km through one braking, and meet the requirements of reentry angle and range at the atmospheric boundary at a height of 120km. Because it is flying outside the atmosphere, the force on the spacecraft is mainly the thrust of the rocket engine and the gravity of the earth.
[0044] Establish the motion equation of the aircraft in the return to inertial coordinate system. When the earth is considered as a homogeneous sphere, that is, when the two-body dynamics model is adopted, the motion equation is
[0045]
[0046] Among them: (x, y, z) is the position of the spacecraft, (v x ,v y ,v z ) Is the speed of the spacecraft, m is the mass of the spacecraft, P is the thrust of the rocket engine, ψ z Is the attitude angle representing the thrust direction of the engine, μ e Is the earth's gravitational constant, r is the distance between the center of the spacecraft...
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