【摘要】：根據(jù)衛(wèi)星軌道計算的積分公式,導(dǎo)出了以參考軌道為初值的線性化解算地球重力場的觀測方程,給出了其系數(shù)矩陣的積分計算公式,闡明了動力學(xué)法本質(zhì)上是觀測值相對于參考軌道的線性攝動方法,因此其變分方程力模型參數(shù)的偏導(dǎo)數(shù)初值必定為0。在此公式的基礎(chǔ)上,分析了動力學(xué)法觀測方程的主要特點,即線性化誤差隨軌道弧段增長而快速增大,其觀測方程的性質(zhì)也隨弧段增長而變差,且積分計算誤差將是下一代重力衛(wèi)星數(shù)據(jù)處理的重要瓶頸問題。提出了進(jìn)一步提高動力學(xué)法重力反演精度的方法,主要歸結(jié)為:改進(jìn)以幾何軌道為初值的線性化方法以減小線性化誤差,改變參數(shù)化方式以改善觀測方程的性質(zhì),綜合應(yīng)用解析公式與數(shù)值積分公式以提高軌道計算精度。
[Abstract]:According to the integral formula of satellite orbit calculation, the observation equation of linear solution of earth gravity field with reference orbit as initial value is derived, and the integral calculation formula of coefficient matrix is given. It is shown that the dynamic method is essentially a linear perturbation method with respect to the observed value relative to the reference orbit, so the initial value of the partial derivative of the force model parameters of the variational equation must be 0. On the basis of this formula, the main characteristics of the dynamic observation equation are analyzed, that is, the linearization error increases rapidly with the increase of the orbital arc, and the properties of the observation equation become worse with the increase of the arc segment. The integral calculation error will be an important bottleneck in the next generation gravity satellite data processing. A method for further improving the precision of gravity inversion by dynamic method is proposed. The main results are as follows: the linearization method with geometric orbit as initial value is improved to reduce the linearization error, and the parameterization method is changed to improve the properties of the observation equation. The analytical formula and numerical integral formula are used to improve the accuracy of orbit calculation.
【作者單位】： 同濟(jì)大學(xué)測繪與地理信息學(xué)院;
【基金】：國家自然科學(xué)基金(41474017) 中國科學(xué)院戰(zhàn)略性先導(dǎo)科技專項(B類)(XDB23030100) 高分遙感測繪應(yīng)用示范系統(tǒng)資助項目~~
【分類號】：P223

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