Propeller engine matching optimization method suitable for long-endurance turboprop power unmanned aerial vehicle

An optimization method and long-endurance technology, applied to aircraft parts, power plant types, ground installations, etc., to achieve the effect of simplifying the selection process

Active Publication Date: 2020-03-31
CHENGDU AIRCRAFT DESIGN INST OF AVIATION IND CORP OF CHINA
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AI Technical Summary

Problems solved by technology

[0005] However, although there are related literatures at home and abroad that introduce the theory of propeller-engine matching design, most of them focus on the selection of piston engines and fixed-pitch propellers, and there is no matching design data for free turbines and constant-speed variable-pitch propellers.

Method used

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  • Propeller engine matching optimization method suitable for long-endurance turboprop power unmanned aerial vehicle
  • Propeller engine matching optimization method suitable for long-endurance turboprop power unmanned aerial vehicle
  • Propeller engine matching optimization method suitable for long-endurance turboprop power unmanned aerial vehicle

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Embodiment Construction

[0027] The three dimensionless parameters of the present invention to characterize the aerodynamic characteristics of the propeller are respectively the pull coefficient C T , power coefficient C P and advance than J:

[0028]

[0029]

[0030]

[0031] Among them, T is propeller thrust (pull force), P is engine output power, ρ is atmospheric density, n is propeller speed, D is propeller diameter, and V is flight speed.

[0032] The propeller aerodynamic characteristic data provided by the propeller manufacturer usually includes the propeller efficiency η corresponding to different power coefficients and forward ratios, that is, the propeller efficiency can be determined by the two dimensionless quantities of forward ratio and power coefficient. For each power coefficient, there is a corresponding advance ratio that maximizes propeller efficiency.

[0033] Taking the power input as the starting point, using the power coefficient and forward ratio, introducing a dime...

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Abstract

The invention relates to aircraft design, in particular to a propeller engine matching optimization method suitable for a long-endurance turboprop power unmanned aerial vehicle. The method comprises the following steps: 1, calculating a matching power coefficient according to aerodynamic characteristic data of a propeller; 2, calculating matching power coefficients under different power coefficients CP and advancing ratios J to obtain a corresponding relation between the propeller efficiency and the matching power coefficients; 3, designing a flight working condition, and giving a matching power coefficient under the position of an engine air door; and 4, determining the optimal efficiency and the advancing ratio corresponding to the matching power coefficient according to the corresponding relation in the step 2 and the step 3 and the matching power coefficient. Through selection of matching working points of the engine and the propeller, the shaft power of the engine is fully utilized, the propulsion efficiency is improved, and the optimal flight performance of the aircraft in the whole flight envelope can be achieved.

Description

technical field [0001] The invention relates to aircraft design, in particular to a propeller-engine matching optimization method suitable for long-endurance turboprop-powered unmanned aerial vehicles. Background technique [0002] Turboprop engines, especially free turboprop engines equipped with constant-speed variable-pitch propellers, are widely used in long-endurance UAVs at home and abroad as high-efficiency power with a power-to-weight ratio superior to that of piston engines. [0003] For aircraft design, the selection of the matching operating point of the engine and propeller is very important. The propeller-engine matching process refers to the process of converting the output power of the engine into forward thrust. It is necessary to integrate the power characteristics of the engine and the aerodynamic characteristics of the propeller, and make a reasonable trade-off between propulsion efficiency and flight speed in order to achieve a wide range of use. The bes...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/00B64D27/02
CPCB64F5/00B64D27/02Y02T90/00
Inventor 吴以婷张效瑜袁正中杨水锋张相闻陈拓
Owner CHENGDU AIRCRAFT DESIGN INST OF AVIATION IND CORP OF CHINA
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