Method for optimizing error of micro-nano satellite separation angular velocity
A micro-nano satellite and velocity error technology, applied in the field of satellite separation, can solve problems such as excessive speed and unstable operation of micro-nano satellites, and achieve the effect of reducing the separation angular velocity
Active Publication Date: 2013-12-18
NAT UNIV OF DEFENSE TECH
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[0006] The present invention aims to provide a micro-nano-satellite separation angular velocity error optimization method that can effectively reduce the micro-nano-satellite separation angular velocity, so as to solve the problem that the micro-nano-satellite separation angular velocity is too large and causes the micro-nano-satellite to work unstable
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[0016] The present invention will be described in detail below with reference to the accompanying drawings and examples.
[0017] Such as figure 1 and figure 2 As shown, the micro-nano-satellite 10 is generally fixed on the fixed base 20 by a separation and unlocking device. During the separation process, the separation and unlocking device releases the constraints on the micro-nano-satellite 10 and is located between the fixed base 20 and the micro-nano-satellite 10. The potential energy device 30 pushes the micro-nano-satellite 10 away, so that the micro-nano-satellite 10 is separated from the fixed base 20 . During the separation process, if the action of all the potential energy devices 30 on the micro-nano-satellite 10 is unbalanced, it will cause the micro-nano-satellite 10 to generate an angular velocity, thereby affecting the stable operation of the micro-nano-satellite 10 . According to the micro-nano-satellite separation angular velocity error optimization method ...
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The invention provides a method for optimizing an error of micro-nano satellite separation angular velocity. The method comprises the following steps of S1, measuring mass center of a micro-nano satellite, and building a micro-nano satellite separation movement coordinate system oxyz with the mass center as an original point, wherein the z axis is separation movement direction, and o is the mass center; and S2, respectively calculating potential energy torque of each potential energy device relative to each coordinate axis according to the projection position of an xy plane in the separation movement coordinate system, superposing the potential energy torque of each potential energy device to obtain the sum of potential energy torques, and selecting the smallest combination of the sum of potential energy torques as a launch installation scheme. The method measures separating elastic potential energy produced by the micro-nano satellite in the satellite separating process of each potential energy device, calculates potential energy torque relative to each coordinate axis in the separation movement coordinate system, superposes the potential energy torques to obtain the sum of potential energy torques, and selects the smallest combination of the sum of potential energy torques as the launch installation scheme, so that potential force moment of the angular velocity produced by the micro-nano satellite is smallest, and accordingly the micro-nano satellite separation angular velocity is reduced effectively.
Description
technical field [0001] The invention relates to the field of satellite separation, in particular to a method for optimizing the angular velocity error of micro-nano satellite separation. Background technique [0002] The angular velocity of the satellite after the separation of the satellite and the rocket is an important parameter for the initial state of the micro-nano satellite in orbit. On the one hand, due to the limitation of the directional characteristics of the communication antenna, there is always a zero-gain direction. Micro-nano satellites usually only have weak attitude control capabilities. Completing a frame of communication data transmission makes it impossible to establish a communication link; on the other hand, if the initial angular velocity is large (that is, rollover occurs), it will become more difficult to control the magnetic torque attitude commonly used for micro-nano satellites, and even cannot work stably. All in all, the lower the separation a...
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IPC IPC(8): B64G1/64
Inventor 庹洲慧赵勇胡星志姚雯张为华
Owner NAT UNIV OF DEFENSE TECH