两个新的Hansen系数的递推公式

推导给出了两个新的Hansen系数X_k~(-(n+1),m)的递推关系:■其中,n、m和k是Hansen系数X_k~(-(n+1),m)的3个指标,e为轨道偏心率.递推公式(R5)可以执行普通Hansen系数的向后递推,需要一行初值,公式简单.递推公式(R6)可以执行偏心率函数的向前递推,需要两行初值,比Vakhidov给出的递推公式明显简单.算例说明,这两种递推是有效的.     

Hansen系数及其导数的直接计算方法

回顾总结了7种Hansen系数及其导数的直接计算方法,比较分析了这些方法的计算效率和计算稳定性.研究表明:Hansen系数的递推关系可以用来判别计算结果的稳定性.最后指出, Wnuk方法(双精度计算)和McClain方法(4精度计算)是稳定的,可以用来计算人造卫星轨道摄动.由于大多数人造卫星采用小偏心率轨道,需要计算无奇点摄动,推荐使用McClain方法1 (4精度计算).     

倾角函数的四精度计算试验

倾角函数是天体力学分析理论中一种常用的函数.当把摄动方程展开成时间和根数的形式时需要用到.历史上提出了很多经典的倾角函数递推算法,并在双精度平台下开发了Fortran程序.进行了1次四精度计算倾角函数的试验,结果表明:L平面递推方法的四精度计算精度可达10-22,计算速度比双精度Jacobi方法快6倍.     

两种利用d-函数计算倾角函数方法的比较

利用d-函数的Blanco递推(d-funl)和Risbo递推(d-fun2),可以得到两种计算倾角函数及其导数的方法.这两种方法均有较高的精度和稳定性.对于小倾角,d-fun2的精度优于d-fun1,而对于大多数其他倾角,d-fun1的精度优于d-fun2;但d-fun2的稳定性明显优于d-funl;计算速度d-funl比d-fun2约快7倍.但是这两种方法均有sin I=0的奇点.另外,d-函数方法直接计算出来的就是正规化的倾角函数,不能实现倾角函数的无奇点计算,因此不适合在小倾角卫星动力学中应用.     

倾角函数递推稳定性分析

历史上曾经提出了较多的倾角函数递推算法,但有一些已经被证明在高阶是不稳定的.通过对递推方向上倾角函数的数量级分析,可以判断倾角函数递推的稳定性.对于常用的3项递推,只有Mk(l)递推是稳定的,其他递推均是不稳定的.但是对于多项递推比较复杂,还需深入分析.     

论倾角函数递推公式中的一种特殊的奇点

在推导倾角函数的递推公式时,通常利用(A)1Al-1,m,p(I)+A2Al,m,p(I)+A3Al+1,m,p(I)=0和(C)1Al,m,p-1(I) +(C)2Al,m,p(I)+(C)3Al,m,p+1(I)=0来定义倾角函数的l递推和p递推.指出:这样建立的递推公式将包含cosI=1/n(n为整数)的奇点,使得倾角函数的计算出现错误.该奇点可以通过改变l递推和p递推的定义来克服.     

RKNF方法和大偏心率轨道数值积分

本文比较在建立中等和大偏心率轨道的精密数值历表时几种数值方法的计算效率,特别推荐国内轨道工作中尚未见使用的直接积分２ 阶微分方程的ＲＫＮＦ 方法。数值实算表明,在方程右函数显含速度和中等或大偏心率轨道情况下,嵌套的７ 阶方法ＲＫＮＦ７８ 是一个普适性好、效率高、程序设计简单的方法。     

倾角函数展开及其在分析法轨道预报中的应用

田谐项摄动是分析法轨道预报中的重要部分,其中包含大量倾角函数及其偏导数的计算.由于具有精度更高、速度更快的优点,倾角函数一般通过递推方法计算.以文献中提出的改进Gooding方法为基础,将其给出的程序稍加改进,在计算2–50阶倾角函数时缩短了约24%的计算时间.考虑到分析法预报过程中轨道平倾角变化很小,以泰勒展开式计算倾角函数,可极大提高计算速度,较大程度地减小分析法预报耗时,且引力场阶次越高,减小幅度越大,取50阶时预报耗时缩短了48%.另一方面,以2阶展开式计算倾角函数时,与改进Gooding法相比,分析法预报星历偏差很小.对于500 km高度的低轨卫星,分别以改进Gooding法和2阶泰勒展开式计算倾角函数,预报3天,当地球引力场阶次不高于50时,二者预报星历偏差RMS (Root Mean Square)低于1 mm,且随着轨道高度的增加,预报星历偏差RMS逐渐减小.     

利用Jacobi多项式计算倾角函数

研究了一种利用Jacobi多项式计算倾角函数的方法,该方法表达式非常简单,不存在k和l是否同奇偶和计算非整数阶乘的问题,也不存在k＜0和k≥0的转换问题,递推公式可使用标准的Jacobi多项式的递推公式.而且,计算精度和适应阶数可与Gooding方法相当,计算时间比Gooding方法省9％.     

Vega碎片盘的结构特性研究

Vega的碎片盘在早期的观测中出现特殊结构,这可能是其内部存在潜在的高偏心率行星导致的.但是,近期对Vega的多波段高分辨率观测显示,Vega的碎片盘是一个平滑的盘结构,这虽然不能否定其内部存在行星的假说,但是对其中潜在行星的某些轨道参数提供了限制条件.使用数值模拟的方法对Vega系统的碎片盘和可能存在的行星进行模拟.模拟中碎片盘位于80～120 AU,盘中尘埃尺寸为10～100 μm,轨道偏心率与倾角都非常小.通过多组计算的结果发现,如果Vega系统中不存在行星,那么其碎片盘演化结果与最新的观测结果吻合得较好;如果存在行星,且行星偏心率较大(比如e=0.6)时,那么行星的轨道半长径不能大于60 AU,否则碎片盘会在行星的影响下产生明显的聚集现象.行星与碎片盘的2:1平运动共振是导致碎片盘产生结构的主要原因.     

Computational Efficiency of the Recursion of Hansen Coefficents

Computational efficiency of the recursion of eccentricity functions is investigated, and a kind of batch recursion method is given. Its computational efficiency is significantly superior to the direct calculation method. Moreover, this kind of batch recursion is forward so that the magnitudes of eccentricity functions experience from small to large change in the recursive process. Hence in this way the high accuracy of the recursion of eccentricity functions can be guaranteed.     

Direct Calculation Methods of Hansen Coefficients and Their Derivatives

Seven direct calculation methods of Hansen coefficients and their derivatives are reviewed. The computational efficiencies of these methods are compared, and their computational stabilities are analyzed. We show that the recursion relations of Hansen coefficients can be used to determine the stabilities of calculation results. Finally, it is pointed out that Wnuk's method (double precision computation) and McClain's methods (quadruple precision computation) are stable, which can be used to calculate orbit perturbations. Because of small orbital eccentricities of most satellites, the perturbation calculations without singularities are required, and McClain's first method (quadruple precision computation) is recommended.     

On the calculation of perturbations in the radial position of satellites

With the aim of analyzing the errors in the radial position of satellites, we give in this paper the expressions for the radial perturbation which include the complete zeroth- and first-order terms in the orbital eccentricity. A simpler and faster method of calculating the perturbation is given.     

月球探测器过渡轨道的短弧定轨方法

论述的短弧定轨,是指在无先验信息情况下又避开多变元迭代的初轨计算方法,它需要相应的动力学问题有一能反映短弧内达到一定精度的近似分析解．探测器进入月球引力作用范围后接近月球时可以处理成相对月球的受摄二体问题,而在地球附近,则可处理成相对地球的受摄二体问题,但在整个过渡段的力模型只能处理成一个受摄的限制性三体问题．而限制性三体问题无分析解,即使在月球引力作用范围外,对于大推力脉冲式的过渡方式,相对地球的变化椭圆轨道的偏心率很大(超过Laplace极限),在考虑月球引力摄动时亦无法构造摄动分析解．就此问题,考虑在地球非球形引力(只包含J2项)和月球引力共同作用下,构造了探测器飞抵月球过渡轨道段的时间幂级数解,在此基础上给出一种受摄二体问题意义下的初轨计算方法,经数值验证,定轨方法有效,可供地面测控系统参考．     

Motion near the 3/1 resonance of the planar elliptic restricted three body problem

The global semi-numerical perturbation method proposed by Henrard and Lemaître (1986) for the 2/1 resonance of the planar elliptic restricted three body problem is applied to the 3/1 resonance and is compared with Wisdom's perturbative treatment (1985) of the same problem. It appears that the two methods are comparable in their ability to reproduce the results of numerical integration especially in what concerns the shape and area of chaotic domains. As the global semi-numerical perturbation method is easily adapted to more general types of perturbations, it is hoped that it can serve as the basis for the analysis of more refined models of asteroidal motion. We point out in our analysis that Wisdom's uncertainty zone mechanism for generating chaotic domains (also analysed by Escande 1985 under the name of slow Hamiltonian chaotic layer) is not the only one at work in this problem. The secondary resonance _p = 0 plays also its role which is qualitatively (if not quantitatively) important as it is closely associated with the random jumps between a high eccentricity mode and a low eccentricity mode.     

First-order theory of weakly eccentric orbital motion

Starting from the analytical theory of perturbed circular motions presented in Celestial Mechanics (Bois, 1994), this paper presents an extended resolution valid also for small eccentricity orbits. The solution is of the first order of a small parameter characterizing the magnitude of disturbing forces. The solution has the form of Fourier series with the coefficients given by iterative formation laws. The solution is free from singularities due to small eccentricity or inclination. As an example of numerical application the equatorial artificial satellite orbits are analyzed. For some high satellite orbits with small eccentricity the difference between the numerical integration and the analytical model does not exceed few centimeters per one revolution.On leave from Astronomical Observatory of A. Mickiewicz University, Soneczna 36, PL60-286 Pozna, Poland.     

Evaluation of the light changes for distorted eclipsing binaries

This paper discusses a method for improving on the numerical evaluation of the light changes exhibited by a distorted eclipsing binary system.In the theory formulated by Kopal (1959), certain boundary integrals due to the distortion of both components have been calculated in terms of the Appell hypergeometric series of the first kind. The values of the four parameters appearing in these series differ according as to whether one is dealing with a partial or an annular eclipse.To accelerate the numerical evaluation of the light changes one should avoid recomputing such infinite series for contiguous values of the parameters. This can be achieved by making use of certain recursion formulae which hold for the foregoing series.We have provided here a procedure that yields forty-eight recursion formulae for the Appell hypergeometric series and have specifically calculated four new independent recursion formulae relevant to the astrophysical problem.     

Improved equations for eccentricity generation in hierarchical triple systems

In a series of papers, we developed a technique for estimating the inner eccentricity in hierarchical triple systems, with the inner orbit being initially circular. However, for certain combinations of the masses and the orbital elements, the secular part of the solution failed. In this paper, we derive a new solution for the secular part of the inner eccentricity, which corrects the previous weakness. The derivation applies to hierarchical triple systems with coplanar and initially circular orbits. The new formula is tested numerically by integrating the full equations of motion for systems with mass ratios from 10⁻³ to 10³. We also present more numerical results for short-term eccentricity evolution, in order to get a better picture of the behaviour of the inner eccentricity.