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Achieving High Navigation Accuracy for Spacecraft Using High-Order Representation Model of disturbing gravity

Achieving High Navigation Accuracy for Spacecraft Using High...

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第37届中国控制会议

作者： Lei Wang Wei Zheng Xiang Zhou College of Aerospace Science and Engineering National University of Defense Technology

Aiming at the low precision of gravity model in the Inertial Navigation System（INS） of the vertical launch vehicle, a disturbing gravity representation model which covers the launch area was presented in this paper. Even trading accuracy against speed, the results achieved by this method have sufficient precision for navigation calculation. By this means, the disturbing gravity is assigned to the navigation computation loop within a very short time and with an extraordinary accuracy. Several numerical simulations have shown that the average approximation error of disturbing gravity is less than 2 mGal at any height level and the relative approximation error is less 2%.

关键词： Inertial Navigation System vertical launch vehicle disturbing gravity representation model approximation error

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On-line compensation of disturbing gravity for ballistic missiles in the launching area

On-line compensation of disturbing gravity for ballistic mis...

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第三十九届中国控制会议

作者： Lei Wang Qi-fei Yan Chang-jiang Fei Wei Zheng College of Information and Communication National University of Defense Technology College of Aerospace Science and Engineering National University of Defense Technology

With the improvement of hardware level of the inertial navigation system, the disturbing gravity of the earth gradually becomes one of the main factors affecting the accuracy of missiles. In this paper, the effect mechanism of the disturbing gravity as well as its error propagation mechanism along the trajectory are analyzed in the first place, and then an analytical formula for predicting the burn-out state deviation caused by the disturbing gravity is derived based on the state space perturbation method. By using this analytical formula, an on-line compensation strategy of disturbing gravity in the launching area is then presented under the closed-loop guidance framework. In the new guidance schedule, the disturbing gravity does not need to be calculated at each step, but only at some equidistant discrete points. When the last-stage engine of missile is close to shutdown, the disturbing gravity function with respect to time is fitted by the precomputed discrete values and used to predict the burn-out state deviation according to the presented analytical formula and correct the required velocity online. Numerical simulations have been done to verified the method proposed in this paper, results imply that the presented analytical formula has relatively high precision with the relative error percentage below 2.5% in each case, and the on-line compensation strategy is also effective with the landing error of missile less than 3 m in each case.

关键词： inertial navigation system disturbing gravity online compensation closed-loop guidance ballistic missile

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