ROTATIONALLY-CATAPULT SYSTEM FOR UNMANNED AERIAL VEHICLE TAKE-OFF AND LANDING

Authors

  • M. F. Tupitsin National Aviation University, Kyiv
  • I. О. Stepanenko National Aviation University, Kyiv

DOI:

https://doi.org/10.18372/1990-5548.64.14864

Keywords:

Rotatable catapult, rotating disk of catapult, rotationally-catapult system

Abstract

In the article is proposed the design of the rotational-catapult system for take-off and landing of unmanned aerial vehicles and determined the algorithm of its functioning. The features of the rotationally-catapult system operation with horizontal and inclined position of the catapult rotational disk are considered in detail. The peculiarities of the rotationally-catapult system functioning include the fact that, on the one hand, the wing span of the unmanned aerial vehicle is limited by the size of the rotating disk of catapult, and an increase in the size of which leads to increased consumption of materials, energy costs, and etc. On the other hand, structural elements of the wing and the unmanned aerial vehicle as a whole, depending on their distance from the rotation axis of catapult and their spatial position, will be affected by centripetal forces of different magnitude and direction, which can damage these elements. In the work an expression for the directing cosines of the unit centripetal acceleration vector is obtained for steady rotational motion of the catapult at its arbitrary inclined position, which makes it possible to simplify the calculation of the unmanned aerial vehicle dynamics motion. The article also provides an example of calculating the landing of unmanned aerial vehicle with characteristics an "Orbiter 3" onto a rotating catapult disk.

Author Biographies

M. F. Tupitsin, National Aviation University, Kyiv

Aviation Computer-Integrated Complexes Department

Candidate of Science (Engineering). Associate Professor

I. О. Stepanenko, National Aviation University, Kyiv

Master of Engineering

References

G. S. Alenchenkov and A. E. Pushkarev, “Structural synthesis of mechanisms of starting devices for the unmanned aerial vehicle of small weight,” Intellectual systems in production. No. 1 (19), 2012, pp. 5–11, (in Russian).

Pat. Utility Model No 98396 RU, IPC B64F 1/06. Catapult/ G. S. Alenchenkov, A. E. Pushkarev. – Declared 05/13/10; publ. 10/20/10, Bull. Number 29.

O. N. Vasiliev, Copyright certificate USSR No. 23783, “A device in the form of a rotatable catapult for launching and landing aircraft,” 10/31/1931.

N. F. Tupitsyn, I. A. Stepanenko, E. I. Voloschenko, and S. S. Shildskyi, “The special case of operative programming method of flight route,” Electronics and Control Systems, no.1 (43), 2015, pp. 36–41. https://doi.org/10.18372/1990-5548.43.8848

http://scask.ru/c_book_agm.php?id=25

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How to Cite

Tupitsin, M. F., & Stepanenko I. О. (2020). ROTATIONALLY-CATAPULT SYSTEM FOR UNMANNED AERIAL VEHICLE TAKE-OFF AND LANDING. Electronics and Control Systems, 2(64), 93–98. https://doi.org/10.18372/1990-5548.64.14864

Issue

Vol. 2 No. 64 (2020)

Section

AVIATION TRANSPORT

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