Modeling the Dependence of the Specific Impulse on the Temperature of the Heater of an Electrothermal Micro-Motor Based on the Results of Its Tests

Microgravity Sci. Technol.

et al. 2022

The paper investigates the issues of a small spacecraft large elastic elements temperature shock influence within the framework of a two-dimensional model of thermal conductivity, taking into account the possible loss of stability during the temperature shock. The loss of stability causes additional movements of large elastic elements sections. The thermoelasticity problem is solved, in which the parameters of the relative motion of large elastic elements, including the loss of stability, are estimated. Additional micro-accelerations resulting from the loss of stability are estimated. Recommendations are given to avoid the loss of stability during the temperature shock.

Section: Introductionmentioning

confidence: 84%

Modeling the Effect of a Temperature Shock on the Rotational Motion of a Small Spacecraft, Considering the Possible Loss of Large Elastic Elements Stability

Sedelnikov

Serdakova

Microgravity Sci. Technol.

et al. 2022

“…Analysis of Expression (10) shows that acceleration ( .. u z (x, t)) is not necessarily opposite to the deflection (u z (x, t)) itself, as in the case when ..…”

Section: Evaluation Of Disturbing Factorsmentioning

confidence: 99%

“…It is more general. In this case, the inertia force (7) depends on the initial deflection, because the first term of the right part (10) contains the second derivative of the initial deflection function (u z0 = u z0 (x, 0)).…”

Section: Evaluation Of Disturbing Factorsmentioning

confidence: 99%

“…This situation is explained by the requirements for the electricity generated by solar panels, which is necessary for the effective functioning of the target equipment of the small spacecraft [6,7]. Some small spacecraft do not have flexible solar panels and are used in uncontrolled motion [7][8][9][10]. The controlled motion of small spacecraft has a number of features due to the more significant influence of flexible elements on this motion [11][12][13].…”

Section: Introductionmentioning

confidence: 99%

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Investigation of Perturbations Arising from Temperature Shock with a Symmetrical Arrangement of Flexible Elements of a Small Spacecraft

Bormotov

2023

Symmetry

This paper investigates the effect of a temperature shock on a small spacecraft with symmetrically arranged flexible elements. A two-dimensional thermoelasticity problem is posed. The disturbing effect of temperature shock on a small spacecraft has been determined. The assessment of the main disturbing factors arising from the temperature shock of flexible elements of a small spacecraft was carried out. Approximate dependences were obtained for the components of the displacement vector of the flexible element points. Numerical simulation was carried out for the symmetric scheme of the small spacecraft with two and four flexible elements. The dependence of the inertia force on temperature shock for the simulated small spacecraft at various initial deflections of the flexible element was constructed. Conclusions were drawn about the significance of the temperature shock influence on the dynamics of a small spacecraft. The results obtained were compared with the results of other studies and can be used in solving problems of remote sensing of the Earth and the implementation of gravity-sensitive processes on board small spacecraft.

“…Studies [1][2][3] show the relationship between the angular velocity of a small spacecraft rotation and the quality of receiving and transmitting telemetric data. If we are talking about small spacecraft for the Earth remote sensing [4][5][6] or for specialized technological purposes [7][8][9], then the values of the angular velocity of rotation in this case should be significantly limited for the successful fulfillment of target tasks.…”

Section: Introductionmentioning

confidence: 99%

Using the -Bdot Algorithm to Reduce the Angular Velocity of Rotation for the Aist Small Spacecraft Pilot Model

Sedelnikov

Advances in Transdisciplinary Engineering

Serdakova

et al. 2022

This article considers the issues of reducing the angular velocity of rotation for a small spacecraft operated in uncontrolled flight. A mathematical model based on Euler’s dynamic equations in the main coupled coordinate system of a small spacecraft has been constructed. The transition of the inertia tensor of the Aist small spacecraft pilot model from the bench coordinate system to the main connected coordinate system was performed. A study and evaluation of the significance of various disturbing factors in modeling the rotational motion of a small spacecraft around the center of mass has been carried out. At the same time, gravitational, aerodynamic and magnetic disturbing factors are considered. The application of the -Bdot algorithm by magnetic executive bodies to reduce the angular velocity has been studied. Results are obtained demonstrating the effectiveness of the -Bdot algorithm application on the example of the Aist small spacecraft pilot model. The results of the presented work can be used in the development of effective algorithms for controlling the movement of a small spacecraft around the center of mass in order to reduce the angular velocity of its rotational motion.