Preliminary Monte Carlo Analysis of the Arrival State Vectors of a Powered Earth-Venus Direct Interplanetary Trajectory Comprising Case-study of Major Interactive Orbital Perturbations

سال انتشار: 1398
محل انتشار: هجدهمین کنفرانس انجمن هوافضای ایران
کد COI اختصاصی: AEROSPACE18_028
زبان مقاله: انگلیسی
تعداد مشاهده: 460

نویسندگان

M.Sc. Space Engineering Department of Aerospace Engineering, Amirkabir University of Technology, Tehran, Iran

چکیده

In the present research, analysis and case study of a pre-defined direct Earth-Venus interplanetary trajectory, is carried out. Preliminary Monte Carlo analysis utilizing Gaussian distribution including a sample size of 1400 cases, considering the magnitude of the powered Delta-V at the departure point as the faulty source in case of having a faulty thruster system, is implemented; it is assumed that the faulty thruster system is able to generate, on average, 90% of the required Delta-V. It is desired to find out the influences on the amount of deviation occurred in the arrival state vectors, for such a trajectory, and also the radius of the sphere of Circular Error Probability (CEP), in which 50% of the stochastic impact points (with respect to the destination-i.e. Venus), are located. Also, eleven different mission cases are defined to study the individual and accumulative influences of major perturbation components, namely, the Third -body and Solar Radiation Pressure (SRP) , on the arrival state vectors of an imaginary spacecraft en route to the Venus. The solution procedure, using numerical integration of the two-body equation plus perturbation terms, is carried out. The calculation process is simulated in C++ programming language developed in Linux environment, with the numerical accuracy of 50 decimal digits; accompanied by the use of Lambert algorithm and also DE405 planetary state ephemerides. Detailed tabulation of the output results, accompanied by case to case analysis, is carried out.

کلیدواژه ها

Astrodynamics- Interplanetary Trajectory-Monte Carlo Analysis- Third-body Perturbation- Solar Radiation Pressure.

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