Stress-strain state analysis of the design of full-turning vertical empennage for aero-spacecraft

Cover Page

Cite item


In this work, the most rational schemes to designing the skin of a full-turning vertical empennage element (stabilator) have been studied. Skin designing schemes were chosen according to aero-spacecraft operating conditions in the re-entry trajectory. During designing process, the requirements for reusable structures of tourist-class aero-spacecrafts were taken into account, such as: maximum simplicity and endurance of the product. To determine the mechanical loads acting on the keel during its movement in the air, a numerical simulation of the aerodynamic flow-around the stabilator profile at 5 arbitrary points on the flight path was carried out. The parameters used for the analysis are: flight velocity, density and viscosity of the air. Of the 5 obtained fields of dynamic pressure acting on the stabilator, the field that creates the largest distributed load was used as the boundary condition for the analysis of the stress-strain state of the structure. The problem of mechanical loading of the stabilator was solved separately for each of the previously studied structural schemes of the skin. Based on the obtained calculation results the optimal skin structural scheme was chosen by comparing the displacements on the line connecting ribs.

About the authors

Andrey A. Chistyakov

Bauman Moscow State Technical University (National Research University of Technology)

Author for correspondence.

Master Student of the Department SM-13 Rocket and Space Composite Structures, BMSTU

5 2-ya Baumanskaya St, bldg 1, Moscow, 105005, Russian Federation

Valery P. Timoshenko

Bauman Moscow State Technical University (National Research University of Technology)


Professor of the Department SM-13 Rocket and Space Composite Structures, BMSTU; Dr. Sc.

5 2-ya Baumanskaya St, bldg 1, Moscow, 105005, Russian Federation


  1. Shuttle technical facts. Available from: http://www. Space_Shuttle/Shuttle_technical_facts (accessed: 16.02.2020).
  2. Advanced Aerospace Medicine On-line. Section 4.1.7: Returning from space: Reentry. Available from: https://www. cami/library/online_libraries/aerospace_medicine/tutorial/media/ iii.4.1.7_returning_from_space.pdf (accessed: 16.02.2020).
  3. Space shuttle. Available from: mission_pages/shuttle/main/index.html (accessed: 16.02.2020).
  4. Space shuttle. Issues associated with the Vandenberg launch site. U.S. GAO Briefing Report no. NSIAD-87-32BR, 1986.
  5. ESA space resources strategy. Available from: https:// Space_Resources_Strategy.pdf (accessed: 15.02.2020).
  6. Virgin Galactic. Available from: https://www. (accessed: 22.02.2020).
  7. Blue Origin. Available from: https://www.blueorigin. com/new-shepard/ (accessed: 22.02.2020).
  8. Boeing. Available from: space/starliner/ (accessed: 22.02.2020).
  9. Bigelow Aerospace. Available from: https:// (accessed: 22.02.2020).
  10. Orion Span. Available from: https://www.orionspan. com/ (accessed: 22.02.2020).
  11. Axiom Space. Available from: https://www.axiomspace. com/axiom-station (accessed: 22.02.2020).
  12. SpaceX. Available from: starship (accessed: 22.02.2020).
  13. Ageeva TG, Dudar EN, Reznik SV. Kompleksnaya metodika proektirovaniya konstrukcii kryla mnogorazovogo kosmicheskogo apparata [Complex methodology for designing the wing structure of a reusable spacecraft] Aviakosmicheskaya tekhnika i tekhnologiya [Aerospace Engineering and Technology]. 2010;2:3-8.
  14. Abzug MJ, Larrabee EE. Airplane stability and control. Second edition. A history of the technologies that made aviation possible. Cambridge university press; 2002.
  15. Ko WL, Quinn RD, Gong L. Finite-element reentry heat-transfer analysis of space shuttle orbiter. NASA technical. 1986;paper 2657:56.
  16. Lyndon B. Space shuttle technical conference. NASA conference, 1983; Publication 2342, Part 1: 597.
  17. Reznik SV, Prosuntsov PV, Mikhailovskii KV. Prediction of thermophysical and thermomechanical characteristics of porous carbon-ceramic composite materials of the heat shield of aerospace craft. J. Eng. Phys. Thermophy. 2015;88(3):594-601.
  18. Reznik SV, Mikhailovskii KV, Prosuntsov P.V. Heat and mass transfer in the chemical vapor deposition of silicon carbide in a porous carbon-carbon composite material for a heat shield. J. Eng. Phys. Thermophy. 2017;90(2):291-300. http://
  19. Reznik SV, Prosuntsov PV, Mikhaylovskii KV. Development of elements of reusable heat shields from a carbon-ceramic composite material 1. Theoretical forecast. J. Eng. Phys. Thermophy. 2019;92(1):89-94. s10891-019-01910-0
  20. Reznik S, Prosuntsov P, Mikhaylovskiy K. Development verification of coatings made from porous ceramicmatrix composite materials. MATEC Web of Conferences. 2018; 224: 03019.
  21. The space shuttle and its operations. Processing the shuttle for flight. Available from: johnson/pdf/584723main_Wings-ch3b-pgs74-93.pdf (accessed: 25.02.2020).
  22. Zakkay V, Miyazawa M, Wang C. Lee surface flow phenomena over Space Shuttle at large angles of attack at M infinity = 6. 1975.
  23. Prosuntsov PV, Taraskin NY. Theoretical and numerical characterization of the thermal physical properties of carbon ceramic materials. MATEC Web of Conferences, 2016;72: 1-7.
  24. Zhitomirskij GI. Konstrukciya samoletov [Aircraft design]. Moscow: Mashinostroenie Publ., 1995. (In Russ.)
  25. Ageeva TG. Razrabotka metodiki proektirovaniya teplonagruzhennyh elementov konstrukcij kryl’ev suborbital’nyh mnogorazovyh kosmicheskih apparatov [Development of methods for designing heat-loaded structural elements of wings of suborbital reusable spacecraft]: dis. ... candidate of technical sciences: 05.07.03: defended 06.04.17. Moscow, 2017

Copyright (c) 2021 Chistyakov A.A., Timoshenko V.P.

Creative Commons License
This work is licensed under a Creative Commons Attribution 4.0 International License.

This website uses cookies

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

About Cookies