Technical shape formation of power plant of high-altitude unmanned aerial vehicle

Аuthors

Zinenkov Y. V.^1*, Lukovnikov A. V.^2**, Cherkasov A. N.¹

1. Air force academy named after professor N.E. Zhukovskii and Y.A. Gagarin, Voronezh, Russia
2. Central Institute of Aviation Motors named after P.I. Baranov, CIAM, 2, Aviamotornaya str., Moscow, 111116, Russia

*e-mail: yura2105@mail.ru
**e-mail: Lukovnikof@mail.ru

Abstract

Purpose of the work is development of mathematical model (MM) of calculation of thrust-economic and weight-dimension characteristics of power plant (PP) for the unmanned aerial vehicle (UAV) with a turbojet.
Methods of the work are the analysis and numerical experiment.
Results of the work
At present, development of UAV is one of the priority directions of developing of aviation in the world. High-altitude UAV with long-range and flight duration are especially required for Russia, taking into account the extent of its territory.
Authors developed dual-flow turbojet engine mathematical model for calculation of thrust-economic and weight-dimension characteristics. This MM enables carry out calculations with high precision for minimum time. The MM possesses high stability for carrying out optimizing researches.
Distinctive feature of developed MM is its multi-schemes. Performances of turbojet and dual-flow turbojet (with stream mixing and without it) with various quantity of rotor shaft of the engine (single-shaft, twin-shaft and three-shaft schemes), with afterburner and without it and also dual-flow turbojet with add stage and gear box can be calculated using this MM.
Test calculations of performance of serial engines (D-30KP and PS-90A) which showed high adequacy and reliability of this MM were carried out with using developed the MM of PP.
Parametric investigations of basic variant of dual-flow turbojet were performed.
Application area of results
Results of this work can be used in the scientific and design organizations engaging in development of draft proposal for advanced UAV, in the ordering Air Force organizations and the industry at justification of requirements for new samples of the aircraft equipment, and also in aviation institutes of higher education at improvement of educational process.
Conclusions
As a result of the conducted researches it is possible to draw the following conclusions:
1. Development of aviation engines of various types for domestic UAV, which satisfy modern requirements for specific fuel consumption, specific weight, etc., is actual.
2. For the solving a task on formation of preliminary technical shape of power plant of the UAV it is developed MM, making it possible to solve a wide range of engineering problem at calculation of aviation engines of various schemes.
3. The carried-out verification of developed MM showed its good adequacy and reliability by comparison of design and passport data of a number of serial aviation engines.
4. The performed parametric researches showed that on a number of work process-related parameters of dual-flow turbojet there is their ambiguous influence on thrust and specific fuel consumption. Therefore carrying out of calculating researches on formation of optimal technical shape of PP on the basis of dual-flow turbojet in UAV system is supposed in what follows.

Keywords:

dual-flow turbojet engine, off-design performance, estimation of efficiency of power plant

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