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Air speed correction method for helicopter maneuvering flight

An airspeed correction method and maneuvering flight technology, applied in the direction of speed/acceleration/shock measurement, test/calibration of speed/acceleration/shock measurement equipment, measurement device, etc. The effect of handling burden and improving flight comfort

Active Publication Date: 2016-04-06
TAIYUAN AERO INSTR
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  • Abstract
  • Description
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AI Technical Summary

Problems solved by technology

[0003] The invention aims to solve the problem of the reverse change of the airspeed when the helicopter slides down rapidly and climbs rapidly during large maneuvers

Method used

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  • Air speed correction method for helicopter maneuvering flight
  • Air speed correction method for helicopter maneuvering flight
  • Air speed correction method for helicopter maneuvering flight

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Experimental program
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Effect test

Embodiment

[0022] Embodiment: When a certain type of helicopter descends rapidly from 1200m to the lowest 620m and then climbs rapidly, it can be seen from the recorded data that the measured airspeed has an obvious reverse change process, and the maximum reverse speed reaches 30km / h. h (see figure 1 ), this reverse airspeed is enough for the automatic stabilization system to control the reverse movement of the elevator rudder surface, resulting in instability of the airframe, which is obviously not what the pilot wanted.

[0023] In order to solve the problem of airspeed reverse change, the inertial vertical acceleration measured by the inertial sensor is filtered according to formula (1) with a moving integration window. The processed acceleration is shown in figure 2 ,Depend on figure 2 It can be seen that when the altitude changes to the lowest position each time, the acceleration value reaches the peak value, which can well locate the position where the airspeed changes reversely...

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Abstract

The invention belongs to the helicopter atmosphere system field, particularly to an air speed correction method for helicopter maneuvering flight, and solves the problem of air speed change in reverse direction when a helicopter performs large maneuvering movements like changing from rapid downslide to rapid climbing. An inertia sensor on the helicopter measures a vertical acceleration a; the vertical acceleration a opens a mobile points window for low pass filtering processing; the vertical acceleration is corrected after filtering processing to obtain a correction air speed that is close to a real air speed. <{EN3}>The correction of the air speed that is has a local distortion benefits controlling the flight stability by the automatic stationary system, reducing pilot's control burden and improving flight comfort level.

Description

technical field [0001] The invention belongs to the field of helicopter atmospheric systems, and in particular relates to an airspeed correction method for helicopter maneuvering flight. Background technique [0002] Usually the airspeed of the helicopter is obtained by calculating the head-on total pressure and the static pressure of the fuselage measured by the total static pressure pitot tube of the atmospheric system. It is difficult to find a total static pressure measurement position that is not affected by the rotor, and it is inevitable that the total static pressure measurement will be disturbed by the rotor. In the normal stable flight of the helicopter, the total static pressure source can be corrected by the measured forward flight airspeed, but when the helicopter performs rapid glides, spins, rapid climbs and large maneuvers, due to the drastic change of the downwash flow field, the downwash flow will The influence of the total pressure increases instantaneous...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01P21/02
CPCG01P21/025
Inventor 朱应平陈文鋆曹钦华
Owner TAIYUAN AERO INSTR
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