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CN102495715A - Deep space Doppler speed measurement calculating method defined by double-precision floating point - Google Patents

Deep space Doppler speed measurement calculating method defined by double-precision floating point Download PDF

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CN102495715A
CN102495715A CN2011103997916A CN201110399791A CN102495715A CN 102495715 A CN102495715 A CN 102495715A CN 2011103997916 A CN2011103997916 A CN 2011103997916A CN 201110399791 A CN201110399791 A CN 201110399791A CN 102495715 A CN102495715 A CN 102495715A
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胡松杰
麻永平
曹建峰
贺军
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Beijing Aerospace Control Center
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Abstract

本发明属于数据处理技术领域,公开了一种双精度浮点定义下的深空Doppler测速计算方法。该方法首先依据Doppler测量原理建立Doppler测量方程;然后用泰勒级数展开式来计算积分周期始末时刻的光行时差;最后将光行时差代入测量方程计算Doppler测速。本发明提高了深空探测Doppler测速的计算精度和效率。

Figure 201110399791

The invention belongs to the technical field of data processing, and discloses a deep-space Doppler velocity measurement calculation method defined by double-precision floating points. The method first establishes the Doppler measurement equation based on the Doppler measurement principle; then uses the Taylor series expansion to calculate the light travel time difference at the beginning and end of the integration period; finally, the light travel time difference is substituted into the measurement equation to calculate the Doppler velocity measurement. The invention improves the calculation accuracy and efficiency of Doppler speed measurement for deep space exploration.

Figure 201110399791

Description

双精度浮点定义下的深空Doppler测速计算方法Calculation Method of Deep Space Doppler Velocimetry Under the Definition of Double Precision Floating Point

技术领域 technical field

本发明属于数据处理技术领域,涉及一种双精度浮点定义下的深空Doppler(多普勒)测速计算方法。The invention belongs to the technical field of data processing, and relates to a deep-space Doppler (Doppler) velocity measurement calculation method defined by double-precision floating points.

背景技术 Background technique

目前深空探测中Doppler的计算通常采用《Formulation for observed and computedvalues of Deep Space Network data types for navigation》一书中所述的方法。利用该方法,若采用双精度浮点数计算光行时,由于舍入误差的影响,其计算精度约为

Figure BSA00000629336700011
皮秒左右(其中[]表示取整,R为探测距离,单位为亿千米),此精度在1亿千米以上的探测任务Doppler测量数据的处理中,只能保证1mm/s(1秒积分周期)的计算精度,显然不能满足当前0.1mm/s甚至0.02mm/s的精度要求。通常的做法是在计算光行时使用四精度浮点数代替双精度浮点数,以提高计算精度,但该方法虽然提高了计算精度,却降低了计算效率。At present, the calculation of Doppler in deep space exploration usually adopts the method described in the book "Formulation for observed and computed values of Deep Space Network data types for navigation". Using this method, if double-precision floating-point numbers are used to calculate light lines, due to the influence of rounding errors, the calculation accuracy is about
Figure BSA00000629336700011
About picoseconds (where [] means rounding, R is the detection distance, and the unit is 100 million kilometers), this accuracy can only guarantee 1mm/s (1 second The calculation accuracy of integration period) obviously cannot meet the current accuracy requirement of 0.1mm/s or even 0.02mm/s. The usual practice is to use quadruple-precision floating-point numbers instead of double-precision floating-point numbers when calculating light lines to improve calculation accuracy, but this method reduces calculation efficiency although it improves calculation accuracy.

发明内容 Contents of the invention

本发明的目的在于提供一种双精度浮点定义下的深空Doppler测速计算方法,以提高计算精度和计算效率。The object of the present invention is to provide a deep-space Doppler velocity measurement calculation method under the definition of double-precision floating point, so as to improve calculation accuracy and calculation efficiency.

为实现上述目的,本发明提供的双精度浮点定义下的深空Doppler测速计算方法包括以下步骤:In order to achieve the above object, the deep space Doppler speed measurement calculation method under the double-precision floating-point definition provided by the present invention comprises the following steps:

<1>依据Doppler测量原理建立Doppler测量方程;<1>Establish the Doppler measurement equation according to the Doppler measurement principle;

<2>用泰勒级数展开式来计算积分周期始末时刻的光行时差;<2> Use the Taylor series expansion to calculate the light travel time difference at the beginning and end of the integration period;

<3>将光行时差代入测量方程计算Doppler测速。<3> Substitute the travel time difference into the measurement equation to calculate the Doppler speed measurement.

进一步的,所述Doppler测量方程如下:Further, the Doppler measurement equation is as follows:

ff DD. == ff RR -- ff 00 == NN CC &Delta;T&Delta;T ++ &delta;f&delta; f ++ vv

其中fD表示Doppler频率偏移量,fR表示接收端接收信号频率,f0表示地面接收站本振频率,NC为一个积分周期内的周计数,ΔT为一个积分周期,δf为观测系统误差,v为观测随机误差。where f D represents the Doppler frequency offset, f R represents the signal frequency received by the receiving end, f 0 represents the local oscillator frequency of the ground receiving station, N C is the cycle count in one integration period, ΔT is an integration period, and δf is the observation system Error, v is the observation random error.

所述计算积分周期始末时刻光行时差的方法如下:The method for calculating the light travel time difference at the beginning and end of the integration period is as follows:

&Delta;&tau;&Delta;&tau; == &tau;&tau; SS ,, ee -- &tau;&tau; SS ,, sthe s

== (( &rho;&rho; SRSR ,, ee -- &rho;&rho; SRSR ,, sthe s )) cc ++ RLTRLT ee -- RLTRLT sthe s

-- {{ [[ TDBTDB RR -- tt (( &tau;&tau; RR )) ]] ee -- [[ TDBTDB RR -- tt (( &tau;&tau; RR )) ]] sthe s }}

++ {{ [[ TDBTDB SS -- tt (( &tau;&tau; SS )) ]] ee -- [[ TDBTDB SS -- tt (( &tau;&tau; SS )) ]] sthe s }}

其中,τS,e,τS,s分别表示星上信号发射端积分周期结束和起始时刻对应的原始,ρSR,e,ρSR,s分别表示积分结束和起始时刻对应的单程几何距离,RLTe,RLTs表示积分结束和起始时刻引力弯曲,TDB表示太阳系质心动力学时,t(τ)表示对应的原时,[]e,[]s分别对应积分结束和起始时刻;Among them, τ S, e , τ S, s respectively represent the original points corresponding to the end of the integration period and the start time of the signal transmitting end on the star, and ρ SR, e , ρ SR, s respectively represent the one-way geometry corresponding to the end of the integration period and the start time Distance, RLT e , RLT s represent the gravitational bending at the end of integration and the beginning moment, TDB represents the dynamic time of the center of mass of the solar system, t(τ) represents the corresponding original time, [] e , [] s correspond to the end and start time of integration respectively;

其中:in:

&rho;&rho; SRSR ,, ee -- &rho;&rho; SRSR ,, sthe s &ap;&ap; -- (( &PartialD;&PartialD; &rho;&rho; SRSR ,, ee &PartialD;&PartialD; rr &RightArrow;&Right Arrow; SRSR ,, ee &Delta;&Delta; rr &RightArrow;&Right Arrow; SRSR ++ 11 22 &Delta;&Delta; TT rr &RightArrow;&Right Arrow; SRSR &PartialD;&PartialD; 22 &rho;&rho; SRSR ,, ee &PartialD;&PartialD; rr &RightArrow;&Right Arrow; SRSR ,, ee 22 &Delta;&Delta; rr &RightArrow;&Right Arrow; SRSR ))

&Delta;&Delta; rr &RightArrow;&Right Arrow; SRSR == [[ rr &RightArrow;&Right Arrow; SS // CC (( TDBTDB SCSC )) -- rr &RightArrow;&Right Arrow; RR (( TDBTDB RR )) ]] sthe s -- [[ rr &RightArrow;&Right Arrow; SS // CC (( TDBTDB SCSC )) -- rr &RightArrow;&Right Arrow; RR (( TDBTDB RR )) ]] ee

&PartialD;&PartialD; &rho;&rho; SRSR ,, ee &PartialD;&PartialD; rr &RightArrow;&Right Arrow; SRSR ,, ee == rr &RightArrow;&Right Arrow; SRSR ,, ee &rho;&rho; SRSR ,, ee

&PartialD;&PartialD; 22 &rho;&rho; SRSR ,, ee &PartialD;&PartialD; rr &RightArrow;&Right Arrow; SRSR ,, ee 22 == -- 11 &rho;&rho; SRSR ,, ee Xx SRSR ,, ee 22 &rho;&rho; SRSR ,, ee 22 -- 11 Xx SRSR ,, ee YY SRSR ,, ee &rho;&rho; SRSR ,, ee 22 Xx SRSR ,, ee ZZ SRSR ,, ee &rho;&rho; SRSR ,, ee 22 Xx SRSR ,, ee YY SRSR ,, ee &rho;&rho; SRSR ,, ee 22 YY SRSR ,, ee 22 &rho;&rho; SRSR ,, ee 22 -- 11 YY SRSR ,, ee ZZ SRSR ,, ee &rho;&rho; SRSR ,, ee 22 Xx SRSR ,, ee ZZ SRSR ,, ee &rho;&rho; SRSR ,, ee 22 YY SRSR ,, ee ZZ SRSR ,, ee &rho;&rho; SRSR ,, ee 22 ZZ SRSR ,, ee 22 &rho;&rho; SRSR ,, ee 22 -- 11

其中,X,Y,Z分别表示飞行器在广义相对论太阳系质心坐标系下的位置分量,下标S表示发射端,R表示接收端,s表示积分开始时刻,e表示积分结束时刻。Among them, X, Y, and Z represent the position components of the aircraft in the barycentric coordinate system of the general relativity solar system, the subscript S represents the transmitting end, R represents the receiving end, s represents the integration start time, and e represents the integration end time.

本发明通过泰勒级数展开来计算积分周期始末两个时刻的光行时差,避免了直接使用差分距离观测量获取Doppler、损失计算精度的缺点,消除了在双精度浮点定义时因字长不足所产生的舍入误差对计算精度的影响,达到四精度浮点数计算的精度,保证了计算效率。The present invention calculates the light travel time difference between the beginning and the end of the integration period through Taylor series expansion, avoids the shortcomings of directly using the difference distance observation to obtain Doppler and loss of calculation accuracy, and eliminates the lack of word length when defining double-precision floating points The impact of the rounding error generated on the calculation accuracy reaches the accuracy of four-precision floating-point number calculation, which ensures the calculation efficiency.

附图说明 Description of drawings

图1火星探测器使用常规方法与通过本发明计算的Doppler进行比较结果。Fig. 1 Mars probe uses the conventional method to compare the result with the Doppler calculated by the present invention.

具体实施方式 Detailed ways

本发明提供的双精度浮点定义下的深空Doppler测速计算方法包括以下步骤:The deep-space Doppler velocity measurement calculation method under the double-precision floating-point definition provided by the present invention comprises the following steps:

1.依据Doppler测量原理建立Doppler测量方程1. Establish the Doppler measurement equation according to the Doppler measurement principle

积分Doppler的观测量是地面站接收信号频率相对标准频率的偏移量fD,通过测量一个积分周期内的周计数得到,即The observation value of the integrated Doppler is the offset f D of the received signal frequency of the ground station relative to the standard frequency, which is obtained by measuring the cycle count in an integration period, that is,

ff DD. == ff RR -- ff 00 == NN CC &Delta;T&Delta;T ++ &delta;f&delta; f ++ vv -- -- -- (( 11 ))

其中fR表示接收端接收信号频率,f0表示地面接收站本振频率,NC为一个积分周期内的周计数,ΔT为一个积分周期,δf为观测系统误差,v为观测随机误差。Among them, f R represents the signal frequency received by the receiving end, f 0 represents the local oscillator frequency of the ground receiving station, N C is the cycle count in an integration period, ΔT is an integration period, δf is the observation system error, and v is the observation random error.

地面接收站的一个积分周期ΔT内累积的Doppler周计数NC的变化可以推导出Doppler观测量fD。对于给定的地面测站,连续的Doppler观测有连续的积分周期。积分周期可以短到0.1s,也可以长到半天(43200s),典型的积分周期是几秒到几千秒的区间。The Doppler observation f D can be derived from the change of the accumulated Doppler cycle count N C within an integration period ΔT at the ground receiving station. For a given surface station, successive Doppler observations have successive integration periods. The integration period can be as short as 0.1s or as long as half a day (43200s), and the typical integration period is in the range of a few seconds to several thousand seconds.

对于NCFor N C there is

NN CC == &Integral;&Integral; tt sthe s tt ee (( ff RR -- ff 00 )) dtdt == &Integral;&Integral; tt sthe s tt ee ff RR dtdt -- ff 00 &Delta;T&Delta;T -- -- -- (( 22 ))

== &Integral;&Integral; &tau;&tau; sthe s &tau;&tau; ee ff SS d&tau;d&tau; -- ff 00 &Delta;T&Delta;T

其中f0为地面接收站的本振频率,小写的下标s,e表示积分起始和结束,t表示地面测站时间,一般采用协调世界时UTC时间系统,τ表示信号发射端的原时。Where f 0 is the local oscillator frequency of the ground receiving station, the lowercase subscript s, e represent the start and end of the integration, t represents the time of the ground station, generally using the Coordinated Universal Time (UTC) time system, and τ represents the original time of the signal transmitter.

考虑比较理想的状态,即发射标准频率fS是一个常数,则有:Considering the ideal state, that is, the emission standard frequency f S is a constant, then:

fRΔT=fSes)=fSΔτ                           (3)f R ΔT = f Ses ) = f S Δτ (3)

为了方便区分,ΔT为接收端一个积分周期,Δτ为接收端一个积分周期对应的发射端的原时差。For the convenience of distinction, ΔT is an integration period of the receiving end, and Δτ is the original time difference of the transmitting end corresponding to one integration period of the receiving end.

2.用泰勒级数展开式来计算积分周期始末时刻的光行时差2. Use the Taylor series expansion to calculate the light travel time difference at the beginning and end of the integration period

考虑到深空探测中光行时一般在广义相对论太阳系质心坐标系下建立,原时差可由下公式计算:Considering that light travel time in deep space exploration is generally established in the barycentric coordinate system of the general relativity solar system, the original time difference can be calculated by the following formula:

&Delta;&tau;&Delta;&tau; == &tau;&tau; SS ,, ee -- &tau;&tau; SS ,, sthe s

== (( &rho;&rho; SRSR ,, ee -- &rho;&rho; SRSR ,, sthe s )) cc ++ RLTRLT ee -- RLTRLT sthe s (( 44 ))

-- {{ [[ TDBTDB RR -- tt (( &tau;&tau; RR )) ]] ee -- [[ TDBTDB RR -- tt (( &tau;&tau; RR )) ]] sthe s }}

++ {{ [[ TDBTDB SS -- tt (( &tau;&tau; SS )) ]] ee -- [[ TDBTDB SS -- tt (( &tau;&tau; SS )) ]] sthe s }}

其中,τS,e,τS,s分别表示星上信号发射端积分周期结束和起始时刻对应的原始,ρSR,e,ρSR,s分别表示积分结束和起始时刻对应的单程几何距离,RLTe,RLTs表示积分结束和起始时刻引力弯曲,TDB表示太阳系质心动力学时,t(τ)表示对应的原时,[]e,[]s分别对应积分结束和起始时刻。Among them, τ S, e , τ S, s respectively represent the original points corresponding to the end of the integration period and the start time of the signal transmitting end on the star, and ρ SR, e , ρ SR, s respectively represent the one-way geometry corresponding to the end of the integration period and the start time Distance, RLT e , RLT s represent the gravitational bending at the end and the beginning of the integration, TDB represents the dynamic time of the center of mass of the solar system, t(τ) represents the corresponding original time, [] e , [] s correspond to the end and the beginning of the integration respectively.

对于深空探测(如火星探测)而言,(4)式右端第1项的数值约在200-1300s之间,第2、3项为相对论效应项,数值约为10-6s量级,而第4、5项的数值在10-9s量级。因此,在双精度浮点定义下,按照式(4)计算光行时,右端第一项引入的舍入误差约为3×10-12s,对应8.4GHz的X波段的Doppler测量误差为1mm/s(1s积分周期),远低于当前的测量精度。因此,为了满足双精度浮点系统的精度要求,需将上式右端第一项计算改为以下:For deep space exploration (such as Mars exploration), the value of the first item on the right side of (4) is about 200-1300 s, and the second and third items are relativistic effect items, and the value is about 10 -6 s. However, the values of items 4 and 5 are in the order of 10 -9 s. Therefore, under the definition of double-precision floating point, when calculating the light line according to formula (4), the rounding error introduced by the first item on the right end is about 3×10 -12 s, and the Doppler measurement error corresponding to the 8.4GHz X-band is 1mm /s (1s integration period), far lower than the current measurement accuracy. Therefore, in order to meet the precision requirements of the double-precision floating-point system, the calculation of the first item on the right side of the above formula needs to be changed to the following:

&rho;&rho; SRSR ,, ee -- &rho;&rho; SRSR ,, sthe s &ap;&ap; -- (( &PartialD;&PartialD; &rho;&rho; SRSR ,, ee &PartialD;&PartialD; rr &RightArrow;&Right Arrow; SRSR ,, ee &Delta;&Delta; rr &RightArrow;&Right Arrow; SRSR ++ 11 22 &Delta;&Delta; TT rr &RightArrow;&Right Arrow; SRSR &PartialD;&PartialD; 22 &rho;&rho; SRSR ,, ee &PartialD;&PartialD; rr &RightArrow;&Right Arrow; SRSR ,, ee 22 &Delta;&Delta; rr &RightArrow;&Right Arrow; SRSR )) -- -- -- (( 55 ))

这里,here,

&Delta;&Delta; rr &RightArrow;&Right Arrow; SRSR == [[ rr &RightArrow;&Right Arrow; SS // CC (( TDBTDB SCSC )) -- rr &RightArrow;&Right Arrow; RR (( TDBTDB RR )) ]] sthe s -- [[ rr &RightArrow;&Right Arrow; SS // CC (( TDBTDB SCSC )) -- rr &RightArrow;&Right Arrow; RR (( TDBTDB RR )) ]] ee

&PartialD;&PartialD; &rho;&rho; SRSR ,, ee &PartialD;&PartialD; rr &RightArrow;&Right Arrow; SRSR ,, ee == rr &RightArrow;&Right Arrow; SRSR ,, ee &rho;&rho; SRSR ,, ee

&PartialD;&PartialD; 22 &rho;&rho; SRSR ,, ee &PartialD;&PartialD; rr &RightArrow;&Right Arrow; SRSR ,, ee 22 == -- 11 &rho;&rho; SRSR ,, ee Xx SRSR ,, ee 22 &rho;&rho; SRSR ,, ee 22 -- 11 Xx SRSR ,, ee YY SRSR ,, ee &rho;&rho; SRSR ,, ee 22 Xx SRSR ,, ee ZZ SRSR ,, ee &rho;&rho; SRSR ,, ee 22 Xx SRSR ,, ee YY SRSR ,, ee &rho;&rho; SRSR ,, ee 22 YY SRSR ,, ee 22 &rho;&rho; SRSR ,, ee 22 -- 11 YY SRSR ,, ee ZZ SRSR ,, ee &rho;&rho; SRSR ,, ee 22 Xx SRSR ,, ee ZZ SRSR ,, ee &rho;&rho; SRSR ,, ee 22 YY SRSR ,, ee ZZ SRSR ,, ee &rho;&rho; SRSR ,, ee 22 ZZ SRSR ,, ee 22 &rho;&rho; SRSR ,, ee 22 -- 11

其中,X,Y,Z分别表示飞行器在广义相对论太阳系质心坐标系下的位置分量,下标S表示发射端,R表示接收端,s表示积分开始时刻,e表示积分结束时刻。Among them, X, Y, and Z represent the position components of the aircraft in the barycentric coordinate system of the general relativity solar system, the subscript S represents the transmitting end, R represents the receiving end, s represents the start time of integration, and e represents the end time of integration.

如果Doppler积分周期相对较短(<100s),可以忽略式中相对论修正项的影响,由此引入的误差不会超过0.3mm,可以优于1ps的计算精度要求。If the Doppler integration period is relatively short (<100s), the influence of the relativistic correction item in the formula can be ignored, and the error introduced by it will not exceed 0.3mm, which can be better than the calculation accuracy requirement of 1ps.

3.将光行时差代入测量方程计算Doppler测速3. Substitute the light travel time difference into the measurement equation to calculate the Doppler speed measurement

将上述(4)-(5)式代入公式(1)即可得到深空Doppler测量值。该计算方法对差分单程距离的计算使用了泰勒展开,避开了直接使用差分距离观测量获取Doppler,损失计算精度的缺点,实现了使用双精度浮点数进行高精度的Doppler计算,保证了计算精度,提高了计算效率。Substituting the above formulas (4)-(5) into formula (1) can obtain the measured value of Doppler in deep space. This calculation method uses Taylor expansion for the calculation of differential one-way distance, avoids the disadvantage of directly using differential distance observations to obtain Doppler, and loses calculation accuracy, and realizes high-precision Doppler calculations using double-precision floating-point numbers, ensuring calculation accuracy , improving the computational efficiency.

本发明已经成功应用于火星探测器的轨道计算中。图1为使用双精度常规方法进行计算与使用本发明计算的残差(观测值与计算值的差)比较。图1上半部分为常规方法计算结果,下半部分为使用该专利方法的计算结果,可以看到使用该方法计算的Doppler残差基本为白噪声,Doppler的计算值精度提高一个量级。The invention has been successfully applied to the orbit calculation of the Mars probe. Fig. 1 is a comparison of the residual error (the difference between the observed value and the calculated value) calculated using the double-precision conventional method and calculated using the present invention. The upper part of Figure 1 is the calculation result of the conventional method, and the lower part is the calculation result of the patented method. It can be seen that the Doppler residual calculated by this method is basically white noise, and the accuracy of the Doppler calculation value is increased by an order of magnitude.

Claims (2)

1. computing method that test the speed of the deep space Doppler under the double-precision floating point definition is characterized in that may further comprise the steps:
< 1>sets up Doppler according to the Doppler measuring principle and measure equation;
< 2>calculate integration period light equation constantly at the whole story with taylor series expansion;
< 3>Equation for Calculating Doppler being measured in the light equation substitution tests the speed.
2. the double-precision floating point as claimed in claim 1 definition deep space Doppler down computing method that test the speed, it is characterized in that: said Doppler measurement equation is following:
f D = f R - f 0 = N C &Delta;T + &delta;f + v
F wherein DExpression Doppler frequency offset, f RThe expression receiving end receives signal frequency, f 0Expression ground receiving station local frequency, N CThe week counting that integration period is interior, Δ T is an integration period, and δ f is the recording geometry error, and v is the observation stochastic error.
The method of the said calculating integration period moment at whole story light equation is following:
&Delta;&tau; = &tau; S , e - &tau; S , s
= ( &rho; SR , e - &rho; SR , s ) c + RLT e - RLT s
- { [ TDB R - t ( &tau; R ) ] e - [ TDB R - t ( &tau; R ) ] s }
+ { [ TDB S - t ( &tau; S ) ] e - [ TDB S - t ( &tau; S ) ] s }
Wherein, τ S, e, τ S, sRepresent that respectively signal transmitting terminal integration period on the star finishes original with correspondence of the initial moment, ρ SR, e, ρ SR,, sRepresent the one way geometric distance that integration finishes and the initial moment is corresponding respectively, RLT e, RLT sThe expression integration finishes and initial moment gravitational deflection, when TDB representes solar system barycenter dynamics, and during t (τ) expression correspondence former, [] e, [] sRespectively corresponding integration finishes and the initial moment;
Wherein:
&rho; SR , e - &rho; SR , s &ap; - ( &PartialD; &rho; SR , e &PartialD; r &RightArrow; SR , e &Delta; r &RightArrow; SR + 1 2 &Delta; T r &RightArrow; SR &PartialD; 2 &rho; SR , e &PartialD; r &RightArrow; SR , e 2 &Delta; r &RightArrow; SR )
&Delta; r &RightArrow; SR = [ r &RightArrow; S / C ( TDB SC ) - r &RightArrow; R ( TDB R ) ] s - [ r &RightArrow; S / C ( TDB SC ) - r &RightArrow; R ( TDB R ) ] e
&PartialD; &rho; SR , e &PartialD; r &RightArrow; SR , e = r &RightArrow; SR , e &rho; SR , e
&PartialD; 2 &rho; SR , e &PartialD; r &RightArrow; SR , e 2 = - 1 &rho; SR , e X SR , e 2 &rho; SR , e 2 - 1 X SR , e Y SR , e &rho; SR , e 2 X SR , e Z SR , e &rho; SR , e 2 X SR , e Y SR , e &rho; SR , e 2 Y SR , e 2 &rho; SR , e 2 - 1 Y SR , e Z SR , e &rho; SR , e 2 X SR , e Z SR , e &rho; SR , e 2 Y SR , e Z SR , e &rho; SR , e 2 Z SR , e 2 &rho; SR , e 2 - 1
Wherein, X, Y, Z represent the location components of aircraft under general relativity solar system geocentric coordinate system respectively, and subscript S representes transmitting terminal, and R representes receiving end, and s representes to represent integration zero hour, e integration finish time.
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