Development of Control Algorithms for the Orbital Motion of a Small Technological Spacecraft with a Shadow Portion of th
- PDF / 758,116 Bytes
- 11 Pages / 595.276 x 790.866 pts Page_size
- 79 Downloads / 184 Views
ORIGINAL ARTICLE
Development of Control Algorithms for the Orbital Motion of a Small Technological Spacecraft with a Shadow Portion of the Orbit A. V. Sedelnikov 1
&
D. I. Orlov 1
Received: 24 April 2020 / Accepted: 27 July 2020 # Springer Nature B.V. 2020
Abstract The paper proposes algorithms for controlling the orbital motion of a small spacecraft for executive bodies with constant and variable thrust. The developed algorithms are aimed at neutralizing the influence of temperature shock on the level of microaccelerations in the area of technological equipment. The influence of the most significant part of the disturbances associated with a change in the size of large elastic elements as a result of temperature shock is leveled out. The developed algorithms can be used in the implementation of technological spacecraft projects such as the “Foton”, “Bion”, SJ series as well as promising small spacecraft such as Vozvrat-MKA. Keywords Control algorithm . Small spacecraft . Microacceleration . Gravitationally sensitive processes
Introduction Te chnological spacecraft require a low level of microacceleration in the working area of technological equipment. It is due to the implementation peculiarities of gravitationally sensitive processes aboard a small spacecraft (Lyubimova et al. 2019; Zemskov et al. 2004; Yasnou et al. 2019; Gaponenko et al. 2019; Mingalev et al. 2020; Sedelnikov 2018). The shadow portion of the orbit of a small spacecraft causes periodic immersion in the shadow and the exit of the spacecraft from it. The phenomenon of temperature shock is associated with it. It is poorly studied, since it has practically no effect on its orbital motion for spacecraft of the middle class (Sedelnikov, and Modeling the effect of temperature deformations of large elements on the dynamics of the orbital motion of a small spacecraft / A.V. Sedelnikov, V.S. Rodina, D.I. Orlov 2019). The ratio of the mass of large elastic elements to the total mass of the spacecraft for a small spacecraft is significantly higher than for a middle-class spacecraft. In this regard, it is necessary to take into account not only the
natural vibrations of large elastic elements but also the consequence of temperature shock to fulfill the restrictions on microacceleration (Sedelnikov, and Modeling the effect of temperature deformations of large elements on the dynamics of the orbital motion of a small spacecraft / A.V. Sedelnikov, V.S. Rodina, D.I. Orlov 2019). The significance of the temperature shock influence on the orbital motion dynamics of a small spacecraft was noted in (Narasimha 2010; Shen 2017; Chamberlain et al. n.d.) as well as in other works. Therefore, it is necessary to develop effective algorithms for controlling the orbital motion of a small spacecraft for the successful use of small spacecraft in space materials science and the implementation of gravitationally sensitive processes on board. The algorithms presented in this paper suggest a decrease in the negative influence of temperature shock with the help of the execu
Data Loading...
