Method for obtaining limit circling performance of piston-type propeller-driven aircraft

A piston and propeller technology, which is applied in the fields of instrumentation, calculation, electrical and digital data processing, etc., can solve the problems of ambiguous curve trajectory, difficult to accurately judge the limit hovering performance of piston propeller aircraft, etc., and achieve the effect of improving the accuracy rate.

Inactive Publication Date: 2017-05-24
PLA AIR FORCE AVIATION UNIVERSITY
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Problems solved by technology

The existing limit circling performance curves were obtained by hand-drawing by ...

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  • Method for obtaining limit circling performance of piston-type propeller-driven aircraft
  • Method for obtaining limit circling performance of piston-type propeller-driven aircraft
  • Method for obtaining limit circling performance of piston-type propeller-driven aircraft

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specific Embodiment approach

[0060] In order to further illustrate the technical solution of the present invention, in conjunction with the accompanying drawings, the specific implementation of the present invention is as follows:

[0061] In this embodiment, it includes obtaining the minimum circling radius and the shortest circling time of the piston propeller aircraft

[0062] The existing method for judging the limit circling performance of a piston propeller aircraft is based on the limit circling performance curve. The curve that determines the radius, time, and slope of the limit circling change with the circling speed is called the limit circling performance curve. Such as figure 1 As shown, the limit circling performance curve is divided into a flight limit line according to the jitter angle of attack and a flight limit line according to the maximum thrust. The flight limit line at the jitter angle of attack is the curve of the relationship between the circling radius R and the speed V when the aircr...

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Abstract

The invention discloses a method for obtaining limit circling performance of a piston-type propeller-driven aircraft. While the tension cannot balance the resistance, the speed and gradient at this moment are the speed and gradient corresponding to the minimum circling radius, so the minimum circling radius of the piston-type propeller-driven aircraft is obtained; and under different speeds, the maximum thrust of the aircraft is used as the boundary condition, so the shortest circling time of the piston-type propeller-driven aircraft is obtained. The technical solution is capable of overcoming the defect in the prior art that the limit circling performance of the piston-type propeller-driven aircraft is only obtained by finding a hand-painted blurred limit circling performance curve, and greatly improving the accuracy rate of obtaining the limit circling performance data, such as the minimum circling radius and shortest circling time of the piston-type propeller-driven aircraft. The adequate preparation is provided for the aircraft in order to obtain the advantageous attack posture in the fight process.

Description

Technical field [0001] The invention belongs to the technical field of aircraft hovering performance research, is suitable for piston-type propeller aircraft, and specifically relates to a method for obtaining the ultimate hovering performance of a piston-type propeller aircraft. Background technique [0002] Directional maneuverability refers to the ability of an aircraft to change its direction in the air, and is an important tactical and technical performance of a fighter. In order to give full play to the directional maneuverability of the aircraft, the pilot should learn how to select the speed and overload (gradient), and then judge to obtain the ultimate circling performance including the minimum circling radius and the shortest circling time. [0003] The smallest radius hovering can achieve a small radius S sharp turn of the aircraft. In actual flight, this tactical action can be used to get rid of the enemy's tail biting attack. For example, when the enemy aircraft is be...

Claims

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Application Information

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IPC IPC(8): G06F19/00
CPCG16Z99/00
Inventor 秦硕刘永学华欣李伟杰杨永志李万青
Owner PLA AIR FORCE AVIATION UNIVERSITY
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