Bringing spacecraft into solar-oriented attitude by the measurements of a single-axis angular-rate sensor and an optical solar sensor

Abstract


The algorithm of the turn of the spacecraft from an initial arbitrary angular position at an arbitrary angular rate to a solar-oriented attitude is investigated. Minimum essential equipment of the motion control system required for the purpose of ensuring maintenance of solar orientation is defined: a solar sensor, a single-axis angular-rate sensor, low-thrust liquid rocket engines. A solution of the problem of defining the spacecraft angular rate vector by the measurements of the deviation of the optical axis of the solar sensor from the sun vector and the single-axis angular-rate sensor is presented. The conditions under which control action on the rocket engines for the purpose of changing the value of the angular-rate vector for the Sun to get into the field of viewing of the solar sensor or for the spacecraft stabilization are defined. Mathematical modeling of the spacecraft attitude control system with the unknown initial state vector of motion is carried out. The results of mathematical modeling confirmed the efficiency of the proposed algorithm in terms of reducing propellant fuel consumption and high-speed performance. In comparison with the known methods of solving the problem of reducing angular speed (a lengthy process with the use of a magnetic system or a fast process with the use of a three-axis angular-rate sensor and rocket engines) the duration of the process of reducing angular speeds is the same as in normal operation, however, at the same time the problem of bringing spacecraft into the solar –oriented attitude is solved.


About the authors

M. G. Shipov

Joint Stock Company Space Rocket Centre Progress

Author for correspondence.
Email: maxim.shipov@gmail.com
ORCID iD: 0000-0002-4265-3734

Russian Federation

Head of the Department of the Development of Spacecraft Motion Control Systems and Spacecraft Center-of-Mass Motion

A. A. Steklova

Joint Stock Company Space Rocket Centre Progress

Email: steklova_aa@mail.ru
ORCID iD: 0000-0002-6016-8417

Russian Federation

Chief of the Sector of the Development of Orientation Systems

A. A. Davydov

Joint Stock Company Space Rocket Centre Progress

Email: arrrtttem@mail.ru
ORCID iD: 0000-0001-9733-6165

Russian Federation

Leading Design Engineer of the Department of the Development of Spacecraft Motion Control Systems  and Spacecraft Center-of-Mass Motion

References

  1. Shipov M.G. Reduction of angular velocities of AIST-2D spacecraft using a system of kinetic moment dumping. Vestnik of Samara University. Aerospace and Mechanical Engineering. 2019. V. 18, no. 2. P. 121-127. (In Russ.). doi: 10.18287/2541-7533-2019-18-2-121-127
  2. Sevast'yanov N.N. Building of orientation modes on Yamal-200 communication satellite without angular speed sensors. Vestnik Tomskogo Gosudarstvennogo Universiteta. Matematika i Mekhanika. 2013. No. 3 (23). P. 104-110. (In Russ.)
  3. Belenky A.D., Vasilyev V.N., Semyonov M.E. Solar pointing mode of the Meteor-M no. 2 satellite. Electromechanical Matters. VNIIEM Studies. 2015. V. 147, no. 4. P. 29-37. (In Russ.)

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