DETERMINATION OF LOADS FOR STRENGTH CALCULATIONS OF THE ATTACHMENT FITTINGS OF THE DEVICES AND ASSEMBLIES OF A SPACECRAFT IN A POWERED FLIGHT


Cite item

Full Text

Abstract

The paper presents the technique of the study of the loads on the gyroscopes of the spacecraft motion control system in the flight segment as a part of a space rocket. This problem is a problem of vibration resistance and is solved mainly for the attachments, which is mounted to the body of a vehicle. These attachments can be the mechanisms, antennas, locks, explosive charges, electrical actuators, telemetry transmitters, devices, and assemblies of a spacecraft. In addition to the above mentioned the elements of fastening equipment: fittings, landing planes, brackets, and flanges may be an object of consideration as well.

The goal of the study is the description of the calculation of the loads (dynamic analysis) for the onboard equipment of a spacecraft in the flight segment as a part of a space rocket. The load values are necessary for strength calculations, the results of which are considered when designing the fixtures for the devices and units, as well as when designing and configuring the devices of rocket and space technology.

As an example of calculation, the authors chose the gyroscopes of the motion control system of small spacecraft “AIST-2D”, the load case was “the max-q”. Based on the initial data, the authors constructed a finite element model (FEM) of the plants to determine the loading values. The model is constructed in the FEMAP software program for interactive creation and maintenance. NX NASTRAN is the solver that is used to carry out the dynamic analysis of the structure – the transient analysis.

As a result of the solution, based on the data obtained, the time change of characteristic parameters of loading – acelerations – is shown. Operational overloads influencing the gyroscope assemblies in each direction of the rectangular coordinate system are obtained from the acceleration graphs by dividing by the acceleration of gravity. The authors compared the calculated and experimental data. For the convenience of performance evaluation, the values are shown for one of four gyroscopes mounted in the spacecraft service systems module.

About the authors

A. A. Popkov

Academician S.P. Korolev Samara State National Research University

Author for correspondence.
Email: fake@neicon.ru
Россия

V. A. Filatov

Academician S.P. Korolev Samara State National Research University

Email: fake@neicon.ru
Россия

A. G. Filipov

Academician S.P. Korolev Samara State National Research University

Email: fake@neicon.ru
Россия

References

  1. Chebotarev V.E., Fateev A.V. Features of orientation of navigating spacecrafts. Kosmicheskie apparaty i technologii, 2018, vol. 2, no. 2, pp. 84–88.
  2. Zimin I.I., Valov M.V., Chebotarev V.E. The principles of submodular design of the unified space platform. Issledovaniya naukograda, 2017, vol. 1, no. 4, pp. 161–165.
  3. Demenko O.G., Biryukov A.S. Special features of verification for EXOMARS-2020 Spacecraft Composite Descent Module shock strength. Vestnik NPO imeni S.A. Lavochkina, 2018, no. 2, pp. 71–77.
  4. Park T.Y., Jeon S.H., Kim S.J., Jung S.H., Oh H.U. Experimental Validation of Fatigue Life of CCGA 624 Package with Initial Contact Pressure of Thermal Gap Pads under Random Vibration Excitation. International Journal of Aerospace Engineering, 2018, vol. 2018, article number 2697516.
  5. Mikrin E.A. Outlook for our country’s manned spaceflight development (to mark the 110th anniversary of S.P. Korolev). Kosmicheskaya tekhnika i tekhnologii, 2017, no. 1, pp. 5–11.
  6. Kirilin A.N., Akhmetov R.N., Shakhmatov E.V., Tkachenko S.I., Baklanov A.I., Salmin V.V., Semkin N.D., Tkachenko I.S., Goryachkin O.V. Opytnotekhnologicheskiy malyy kosmicheskiy apparat “AIST- 2D” [Experimental and technological small spacecraft “AIST-2D”]. Samara, Samarskiy nauchnyy tsentr RAN Publ., 2017. 324 p.
  7. Ermakov D.A. Methodological support of the solution of mathematical problems. Molodoy uchenyy, 2018, no. 8, pp. 15–17.
  8. Kurochkina I.V., Milokhova V.I., Mokshanova R.A., Voronkova G.V. Solution of spatial frame structure with large node displacements by finite elements method in a mixed form. Mezhdunarodnyy nauchno-issledovatelskiy zhurnal, 2017, no. 7-3, pp. 45–50.
  9. Zhang H.-M., Shang D.-G., Lv S. FES of the effect of free vibration treatment on fatigue damage recovery for notched copper film. MATEC Web of Conferences, 2018, vol. 165, article number 14008.
  10. Popkov A.A., Filatov V.A., Filipov A.G. The method of calculation of loads for installations on-board equipment of the spacecraft. Sovremennye nauchnye issledovaniya i razrabotki, 2018, no. 12, pp. 722–727.
  11. Kyi A.M., Htwe E.E., Maung W.P. Transient Response Analysis and Modelling of Elevating Screw for Radial Drilling Machine. International Journal of Scientific and Research Publications, 2018, vol. 8, no. 10, pp. 683–691.
  12. Losev N.N., Golovkov V.V., Kindyakov D.G., Ulanov R.O., Trunov K.A. Universal stand Assembly and testing of equipment on-board information and navigation system of the spacecraft “GLONASS-K2”. Kosmicheskie apparaty i tekhnologii, 2018, vol. 2, no. 3, pp. 175–179.
  13. Bezmozgiy I.M., Bobylev S.S., Sofinskiy A.N., Chernyagin A.G. The effect of thrust cut-off the third stage of the launch vehicle on the loading and strength of the transport cargo vehicle structure. Kosmicheskaya tekhnika i tekhnologii, 2017, no. 2, pp. 63–79.
  14. Vostrukhin A.A., Golovin D.V., Kozyrev A.S., Litvak M.L., Malakhov A.V., Mitrofanov I.G., Mokrousov M.I., Tomilina T.M., Grebennikov A.S., Laktionova M.M., Bakhtin B.N. Microphonics in scintillation gamma-spectrometer in vibration environment onboard spacecraft. Kosmicheskaya tekhnika i technologii, 2017, no. 1, pp. 82–88.
  15. Igolkin A.A., Safin A.I., Filipov A.G. Modal analysis of the dynamic mockup of “AIST-2d” small spacecraft. Vestnik Samarskogo universiteta. Aerokosmicheskaya tekhnika, tekhnologii i mashinostroenie, 2018, vol. 17, no. 2, pp. 100–108.
  16. Mezhin V.S., Obukhov V.V. The development and experimental verification of solar array in folded configuration dynamic finite element model with taking into account an air environment. Kosmicheskaya tekhnika i tekhnologii, 2018, no. 1, pp. 98–108.
  17. Avershev A.S., Bobylev S.S., Falin K.A. The updated verification procedure of detailed finite element structural models of rocket-space technology for analysis of dynamic loading in flight by the example of the Progress MS cargo transport vehicle. Kosmicheskaya tekhnika i tekhnologii, 2018, no. 1, pp. 40–53.
  18. Sedelnikov A.V., Puzin Yu.Ya., Filippov A.S. Method of flight operation of software and hardware for controlling parameters of the rotational motion of small spacecraft of the AIST series. Aviatsionno-raketnoe i energeticheskoe mashinostroenie, 2018, vol. 2, no. 3, pp. 35–42.
  19. Dorosinskiy A.Yu., Gerasimov O.N., Artamonov D.V. The Influence of shock loading on structural materials and wire wound resistors. Nadezhnost i kachestvo slozhnykh system, 2017, no. 3, pp. 33–36.
  20. Gerasimov O.N., Dorosinskiy A.Yu., Berezin M.N. Study of the effect of the action of vibration loads on the structural materials of electronic devices. Nadezhnost i kachestvo slozhnykh system, 2017, no. 3, pp. 37–42.

Supplementary files

Supplementary Files
Action
1. JATS XML
Download

Copyright (c)



This website uses cookies

You consent to our cookies if you continue to use our website.

About Cookies