A Method for Equivalent Flight Test of Aircraft Residual Thrust Based on Parameter Identification
A parameter identification and aircraft technology, applied in the field of effective flight test, can solve the problems of low test flight efficiency, high flight test cost, and long flight test period, and achieve the effects of improving test flight efficiency, saving flight test cost, and shortening the flight test period
Active Publication Date: 2021-06-08
CHENGDU AIRCRAFT INDUSTRY GROUP
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Problems solved by technology
[0003] For a long time, the flight test missions have been arranged one by one according to the flight test subjects and flight test content. There are problems such as long test flight cycle, high test flight cost, and low test flight efficiency.
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Embodiment 1
[0091] The purpose of the present invention is to construct a parameter identification-based aircraft residual thrust equivalent flight test method, aiming at improving flight test efficiency, shortening test flight period, and saving test flight cost. In order to achieve the above object, the present invention adopts technical solutions including:
[0092] 1) In the track coordinate system, the dynamic equation of the center of mass of the aircraft motion is as follows:
[0093]
[0094] Among them, m is the mass of the aircraft, V is the true speed, P is the available thrust, L is the lift force, D is the drag force, Z is the sideslip force, α is the angle of attack, β is the sideslip angle, γ is the roll angle, and θ is the flight angle. track inclination angle, ψ is track deviation angle, is the installation angle of the engine, and g is the acceleration due to gravity;
[0095] 2) On the basis of 1), without considering the side-slip motion of the aircraft, under th...
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The invention discloses an aircraft residual thrust equivalent flight test method based on parameter identification. The aircraft climbs and descends without side slipping, and if the flight path inclination γ during the climbing motion is negative, the flight path inclination γ during the descent is positive, the corresponding longitudinal overload n x negative and positive, respectively, the track inclination γ and the longitudinal overload band n x The symbols are the same, and the equivalent flight test model of the remaining thrust of the aircraft is n Z 2 -1=qCn x , where n Z is the normal overload, nx is the longitudinal overload, q is the dynamic pressure, and C is the parameter of the equivalent flight test model. The present invention can directly obtain the performance index that needs to be tested through the model, without obtaining the performance index through the actual flight test of the aircraft. The present invention improves the flight test efficiency, shortens the flight test period, and saves the flight test cost through the equivalent flight test model of the remaining thrust of the aircraft.
Description
technical field [0001] The invention belongs to the technical field of aircraft flight test models, and in particular relates to an aircraft residual thrust equivalent flight test method based on parameter identification. Background technique [0002] Flight test is the process of conducting scientific research and product testing under real flight conditions. It is the last of the four links necessary for the birth of a new generation of aircraft. It plays an important role in the entire development cycle. It has extremely complex flight test content, The flight test is risky and repetitive, and the test flight is costly. [0003] For a long time, the arrangement of flight test tasks has been carried out point by point according to the flight test subjects and content of the flight test. There are problems such as long test flight period, high test flight cost, and low test flight efficiency. Based on this, the present invention proposes an equivalent flight test model bas...
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IPC IPC(8): G06F30/15G06F119/14
CPCG06F30/15G06F2119/14
Inventor 刘志林苗文中郑权杨海庆贺振玲陶义建
Owner CHENGDU AIRCRAFT INDUSTRY GROUP