Nima Karimi; محمد علی فارسی
Volume 13, Issue 1 , March 2020, , Pages 13-23
Abstract
In the present paper, the process of designing launch abort system is presented for manned spacecraft in sub-orbital mission. For this purpose, by studying the other manned spacecraft launch abort system, a number of dimensionless parameters have been generated for the launch abort system and spacecraft. ...
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In the present paper, the process of designing launch abort system is presented for manned spacecraft in sub-orbital mission. For this purpose, by studying the other manned spacecraft launch abort system, a number of dimensionless parameters have been generated for the launch abort system and spacecraft. using these parameters, the mass, geometric-dimensional characteristics, the launch escape motor thrust and acceleration of the LAS have been estimated. Also The numerical aerodynamic analysis has been used to form the external configuration, and the results of the analysis, along with other effective parameters, have created a design framework. AHP analysis has been used to select the optimal configuration and in order to validation, an analytical model based on the momentum equation used to design the launch escape motor. Comparison of the results of this model and the statistical design has shown that the data produced is correct.
Ghasem Kahe; Maysam Mohammadi-Amin; Arash Sefidan Benisi
Volume 10, Issue 1 , June 2017, , Pages 1-13
Abstract
Various strategies have been developed to increase the safety of spacecraft crews, among which the Launch Abort System has been widely considered by the space centers across the world. The launch abort system should be able to carry the crew module away from the failed launcher or rocket in a short time ...
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Various strategies have been developed to increase the safety of spacecraft crews, among which the Launch Abort System has been widely considered by the space centers across the world. The launch abort system should be able to carry the crew module away from the failed launcher or rocket in a short time in accordance with the predetermined profile and recover the crew module on the ground. While the main part of the vehicle flight consists of the tracking, reorientation, and settling phase; attitude control in the flight path is done via the roll and pitch channel. Non-linear dynamic inversion flight control is considered for the attitude control of the LAS. Tracking the predetermined profile for the angle of attack as well as the sideslip angle and maintaining the stability of the vehicle in the flight path are considered as the control objectives based on the requirements. Simulations and analytical evaluations indicate the outperformance of the proposed controller for the attitude control of LAS in line with the predetermined profile.
