Abstract
A new approach to synthesize a robust controller for the angular motion of the Earth lander by decomposition method of output modal control is proposed. A universal analytical solution for the problem of stabilizing the angular position of the lander is obtained. A comparative analysis of the presented algorithm with the currently used onboard algorithm for descent control of the manned spacecraft Soyuz is carried out. The advantages of the new algorithm relative to the existing algorithm are presented, both in terms of stabilization accuracy and the consumption of the working fluid of the control motors.
Highlights
The descent and landing of spacecraft are one of the most important and crucial stages of their flight [1,2]
It should be noted that the standard control of the capsule-type spacecraft orientation in the atmosphere [12,13] is aimed at damping the angular velocities and tracking the programmed roll angle
Channel, described by a completely controllable and completely observable triple of matrices (16) and spectrum (17). This is a problem with one control input, which means that the state regulator matrix is uniquely found using the Ackerman formula [30]: KP = 0
Summary
The descent and landing of spacecraft are one of the most important and crucial stages of their flight [1,2]. It should be noted that the standard control of the capsule-type spacecraft orientation in the atmosphere [12,13] is aimed at damping the angular velocities and tracking the programmed roll angle. In this case, the balancing position of the spacecraft at the other two angles (attack and glide) is maintained only due to the static stability of the spacecraft—the accuracy of such stabilization is low. The novelty of the approach lies in the fact that due to the parameterization of the matrices with the desired spectra and the proper choice of the assigned poles, it is possible to achieve independence of the control channels for pitch, roll and yaw, both from each other and from the aerodynamic parameters of the spacecraft
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