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1.
Miquel A. Andreu 《Celestial Mechanics and Dynamical Astronomy》2003,86(2):107-130
The computation of translunar Halo orbits of the real Earth–Moon system (REMS) has been an open problem for a long time, but now, it is possible to compute Halo orbits of the REMS in a systematic way. In this paper, we describe the method used for the numerical computation of Halo orbits for a time span longer than 41 years. Halo orbits of the REMS are computed from quasi-periodic Halo orbits of the quasi-bicircular problem (QBCP). The QBCP is a model for the dynamics of a spacecraft in the Earth–Moon–Sun system. It is a Hamiltonian system with three degrees of freedom and depending periodically on time. In this model, Earth, Moon and Sun are moving in a self-consistent motion close to bicircular. The computed Halo orbits of the REMS are compared with the family of Halo orbits of the QBCP. The results show that the QBCP is a good model to understand the main features of the Halo family of the REMS. 相似文献
2.
Impulsive time-free transfers between halo orbits 总被引：1，自引：0，他引：1
A methodology is developed to design optimal time-free impulsive transfers between three-dimensional halo orbits in the vicinity of the interior L
1 libration point of the Sun-Earth/Moon barycenter system. The transfer trajectories are optimal in the sense that the total characteristic velocity required to implement the transfer exhibits a local minimum. Criteria are established whereby the implementation of a coast in the initial orbit, a coast in the final orbit, or dual coasts accomplishes a reduction in fuel expenditure. The optimality of a reference two-impulse transfer can be determined by examining the slope at the endpoints of a plot of the magnitude of the primer vector on the reference trajectory. If the initial and final slopes of the primer magnitude are zero, the transfer trajectory is optimal; otherwise, the execution of coasts is warranted. The optimal time of flight on the time-free transfer, and consequently, the departure and arrival locations on the halo orbits are determined by the unconstrained minimization of a function of two variables using a multivariable search technique. Results indicate that the cost can be substantially diminished by the allowance for coasts in the initial and final libration-point orbits.An earlier version was presented as Paper AIAA 92-4580 at the AIAA/AAS Astrodynamics Conference, Hilton Head Island, SC, U.S.A., August 10–12, 1992. 相似文献
3.
We consider periodic halo orbits about artificial equilibrium points (AEP) near to the Lagrange points L
1 and L
2 in the circular restricted three body problem, where the third body is a low-thrust propulsion spacecraft in the Sun–Earth
system. Although such halo orbits about artificial equilibrium points can be generated using a solar sail, there are points
inside L
1 and beyond L
2 where a solar sail cannot be placed, so low-thrust, such as solar electric propulsion, is the only option to generate artificial
halo orbits around points inaccessible to a solar sail. Analytical and numerical halo orbits for such low-thrust propulsion
systems are obtained by using the Lindstedt Poincaré and differential corrector method respectively. Both the period and minimum
amplitude of halo orbits about artificial equilibrium points inside L
1 decreases with an increase in low-thrust acceleration. The halo orbits about artificial equilibrium points beyond L
2 in contrast show an increase in period with an increase in low-thrust acceleration. However, the minimum amplitude first
increases and then decreases after the thrust acceleration exceeds 0.415 mm/s2. Using a continuation method, we also find stable artificial halo orbits which can be sustained for long integration times
and require a reasonably small low-thrust acceleration 0.0593 mm/s2. 相似文献
4.
常规化探异常信息识别通常都是通过对比观测值与某一异常阈值的高低来判定某样品是否为异常样品,很多方法或者建立在经典统计学基础之上,要求数据符合一定的分布形式,或者面向整个研究区计算异常阈值,而无法顾及实际的地质环境。根据常规方法以数值大小计算异常阈值的原则,并且关注化探数据分布特征信息的分析和挖掘,提出了晕状特征提取方法,该方法能够有效识别局部异常及低缓异常。将此方法用于克拉玛依地区对金矿预测具有指示意义的化探数据的异常信息识别工作,结果表明:该方法能够有效识别化探异常信息,这些异常信息与研究区内已知金矿具有很好的对应关系。晕状特征提取方法在新疆东部的应用案例也显示出较好的结果。该方法可以作为一种有效的化探异常信息识别方法应用于成矿预测实际工作中。 相似文献
5.
Two-point boundary value problems appear frequently in space trajectory design. A remarkable example is represented by the
Lambert’s problem, where the conic arc linking two fixed positions in space in a given time is to be characterized in the
frame of the two-body problem. Classical methods to numerically solve these problems rely on iterative procedures, which turn
out to be computationally intensive in case of lack of good first guesses for the solution. An algorithm to obtain the high
order expansion of the solution of a two-point boundary value problem is presented in this paper. The classical iterative
procedures are applied to identify a reference solution. Then, differential algebra is used to expand the solution of the
problem around the achieved one. Consequently, the computation of new solutions in a relatively large neighborhood of the
reference one is reduced to the simple evaluation of polynomials. The performances of the method are assessed by addressing
typical applications in the field of spacecraft dynamics, such as the identification of halo orbits and the design of aerocapture
maneuvers. 相似文献
6.
对个旧西区陡岩锡矿原生晕的研究,认为金属矿物组合分带有规律,(从内向外)Cu、Sn带→Sn、Pb、Cu带→Sn、Pb带;金属元素水平分带(从内向外):Cu、Bi→Ag→Sn→Pb、Mn→Cd;垂直分带序列(从下至上):Cu→Zn→Sn→Ag→Pb→Mo→In→Bi→As;可将异常划分为:Sn、Cu型,Sn、Cu、Pb型,Sn、Pb型;通过地表、剖面原生晕特征的分析,提出找矿标志;预测花岗岩的深度及成矿有利地段,指出找矿方向。 相似文献
7.
Roberto Armellin Francesco Topputo 《Celestial Mechanics and Dynamical Astronomy》2006,96(3-4):289-309
A sixth-order accurate scheme is presented for the solution of ODE systems supplemented by two-point boundary conditions. The proposed integration scheme is a linear multi-point method of sixth-order accuracy successfully used in fluid dynamics and implemented for the first time in astrodynamics applications. A discretization molecule made up of just four grid points attains a O(h
6) accuracy which is beyond the first Dahlquist’s stability barrier. Astrodynamics applications concern the computation of libration point halo orbits, in the restricted three- and four-body models, and the design of an optimal control strategy for a low thrust libration point mission. 相似文献
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10.
首先介绍了圆型限制性三体问题的非线性常微分运动方程组,利用定性分析方法、级数解法和数值解法,系统地介绍了这个问题的求解分析方法,相应地给出了共线平动点附近的力学特性、条件周期(和拟周期)轨道,并通过分析一个周期处的状态转移矩阵(Monodromy矩阵)分析了各类轨道的稳定性以及几种周期和拟周期轨道之间的关系。另外,还给出了圆型限制型三体模型下Halo轨道的牛顿迭代算法。 相似文献