Double-engine helicopter avoidance area curve calculation method

一种计算方法、直升机的技术，应用在设计优化/仿真、仪器、几何CAD等方向，能够解决缺少双发直升机回避区详细计算方法等问题，达到计算结果准确的效果

Pending Publication Date: 2022-06-07
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] Aiming at the deficiencies in the prior art above, the purpose of the present invention is to provide a method for calculating the avoidance zone curve of a twin-engine helicopter to solve the problem in the prior art that there is no detailed calculation method for the avoidance zone of a twin-engine helicopter

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Embodiment Construction

[0198] In order to facilitate the understanding of those skilled in the art, the following in conjunction with the embodiments and accompanying drawings to further illustrate the present invention, the content referred to in the embodiment is not a limitation of the present invention.

[0199] Reference Figure 1 As shown, a twin-engine helicopter avoidance zone curve calculation method of the present invention, the steps are as follows:

[0200] 1) Statistics on twin-engine helicopter parameters and engine parameters used;

[0201] Specifically, the twin-engine helicopter parameters in step 1) include: the total weight of the helicopter G, the rotational angular velocity of the rotor Ω, the number of propeller blades k, the rotor wing type (i.e., the rotor aerodynamic parameters are obtained, such as the rotor type resistance coefficient), the rotor radius R, the rotor solidity σ, the minimum rotational speed of the rotor after a single failure Ω min1 3. The minimum speed of the r...

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Abstract

The invention discloses a double-engine helicopter avoidance area curve calculation method. The method comprises the following steps: counting parameters of a double-engine helicopter and parameters of an engine used by the double-engine helicopter; according to the counted parameters, calculating the power required by forward flight of the double-engine helicopter, and drawing an Nxu-V0 curve; according to the power required for forward flight of the helicopter, the descent rate during single-engine failure and full-engine failure of the double-engine helicopter is calculated, and a descent rate curve is drawn; according to an intersection point of the descent rate curve and the maximum landing speed capable of being borne by the undercarriage of the double-engine helicopter, a double-engine helicopter avoidance area curve key point is calculated; and according to the calculated key points of the double-engine helicopter avoidance area curve, drawing the double-engine helicopter avoidance area curve. Compared with an existing calculation method, the calculation result is more accurate; according to the method, the approximate range of the helicopter avoidance area can be determined before the helicopter is subjected to the flight test, and the method has an advanced guiding effect on the subsequent flight test.

Description

Technical field [0001] The present invention belongs to the field of aviation avoidance zone calculation technology, specifically relates to a twin-engine helicopter avoidance zone curve calculation method. Background [0002] The helicopter has low altitude and low speed high maneuverability, in the air vigilance detection, security patrol, relay communication, detection and combat integration, short and medium-distance transportation, sightseeing and tourism and other fields have a wide range of uses, is the civil aviation market and emergency rescue department of the main products. Therefore, helicopters are widely used worldwide, but this also brings strict safety requirements for helicopters. Once the helicopter has an engine in the air parking or power failure during flight, it can use the rotational kinetic energy stored by the rotor to land safely in a rotational sliding manner, which is a special performance that the helicopter has different from the fixed-wing aircraft....

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/17G06F30/20G06F119/02G06F119/14
CPCG06F30/15G06F30/17G06F30/20G06F2119/02G06F2119/14Y02T90/00
Inventor 龙福坤朱清华刘辉严俊杰
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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