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应用捷联惯性测量组合,确定宇宙飞行器空间位置的计算方法。 捷联惯导系统的发展,引起了我们对计算技术和确定宇宙飞行器空间位置计算方法更大的注意[1]。在这方面,首先要考虑应用四元数（K_BaTEPHNOH）,方向余弦和固有欧拉方程的可能性。因为完全再现飞行条件是非常困难的,所以根据数字模拟结果所得的方法多半都是《经验》公式,虽然在文献[2]中所作的解析和试验结果肯定了四元数的应用,但是在捷联惯导系统中对算法阶数和重复速度的选择问题,仍是一个有待解决的问题,对于宇宙飞行器的导航系统特性来讲,更是如此。
Application of strapdown inertial measurement combination to determine the spacecraft spacecraft calculation method. The development of SINS has drawn more attention to computational techniques and methods for determining the space position of space vehicles [1]. In this regard, we first consider the possibility of applying the quaternion (K_BaTEPHNOH), the direction cosine and the Euclidean equation. Since it is very difficult to fully reproduce the flight conditions, most of the methods based on numerical simulation results are “empirical” formulas. Although the analytical and experimental results in [2] confirm the application of quaternions, The problem of choice of algorithm order and repetition speed in the joint inertial navigation system is still an issue to be solved, which is even more so for the characteristics of the navigation system of a space vehicle.