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

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.