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Amending method for positional error of total static pressure sensor on low-speed unmanned aerial vehicle

An unmanned aerial vehicle and sensor technology, applied in the field of aerodynamics of aeronautics, can solve the problems of endangering flight safety, increasing weight, increasing weight, etc., and achieve the effect of high correction accuracy and simple expression.

Inactive Publication Date: 2008-08-20
BEIHANG UNIV
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AI Technical Summary

Problems solved by technology

On the one hand, position errors cannot meet the needs of UAVs for precise control and route maintenance, and on the other hand, in some cases, unexpected aircraft stalls or low flying altitudes may occur, jeopardizing flight safety.
[0003] Usually there are two ways to eliminate the position error: one is to increase the length of the total static pressure sensor so that it protrudes out of the interference area of ​​the nose to the incoming flow, but this not only increases the weight, but also aggravates the vibration during flight , but the structure of the installation location has to be strengthened; the second is to move the installation location of the total static pressure sensor to another location with less interference, but this will also cause weight increase and difficulties in the layout of aircraft internal pipelines and equipment

Method used

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  • Amending method for positional error of total static pressure sensor on low-speed unmanned aerial vehicle
  • Amending method for positional error of total static pressure sensor on low-speed unmanned aerial vehicle
  • Amending method for positional error of total static pressure sensor on low-speed unmanned aerial vehicle

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Embodiment Construction

[0020] The present invention will be further described in detail with reference to the accompanying drawings and embodiments.

[0021] The invention provides a correction method applied to the position error of the total static pressure sensor on the low-speed unmanned aerial vehicle, such as figure 2 The flow chart of the steps shown, the specific steps are as follows:

[0022] Step 1. Set up two sets of total static pressure sensors in the wind tunnel, respectively measure and calculate a series of flight speeds, heights and atmospheric pressure data.

[0023] Install the total static pressure sensor (herein referred to as the practical total static pressure sensor) that needs to correct the error on the nose, and carry out the wind tunnel test on the combination of the two. Another total static pressure sensor (called the reference total static pressure sensor) is installed in an undisturbed position in the wind tunnel. In the wind tunnel test, two sets of total static p...

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Abstract

The present invention discloses a method for modifying the position error of the total static pressure pick-up. The method uses a wind tunnel experiment to obtain a simple modifying method for modifying the flight speed of the unmanned plane and the atmosphere static pressure data. When the modifying method provided by the invention is applied, the designing of the total static pressure pick-up and the general arrangement of the plane do not need modifying; besides the provided modifying formula is simple and definite formulated, the inner algorithm of the air data computer does not need modifying and the data can be automatically modified in the flight control software; and a higher modifying precision is provided to the typical flight condition.

Description

technical field [0001] The invention relates to a correction method applied to the position error of a total static pressure sensor on a low-speed unmanned aerial vehicle, belonging to the technical field of aerodynamics of aircraft. Background technique [0002] The total static pressure sensor (also known as pitot) is a common device on the aircraft, which is used to sense the total incoming flow pressure and atmospheric static pressure received by the aircraft during flight. On low-speed UAVs, the atmospheric static pressure sensed by the total static pressure sensor is usually used to calculate the flight altitude of the aircraft; the difference between the incoming total pressure and the atmospheric static pressure is used to calculate the flight speed of the aircraft. However, the total static pressure sensor is usually installed at the nose position, such as figure 1 As shown, on the low-speed UAV, due to the disturbance of the nose to the incoming flow in front, the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/02G01L27/00
Inventor 张朔马铁林马东立张云飞王金提
Owner BEIHANG UNIV
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