Method for determining pneumatic error on the condition of high altitude and high Mach number
A technology with a high Mach number and a certain method, which is applied in the field of aircraft structure, can solve problems such as inability to give aerodynamic errors and inability to cover flight conditions, and achieve the effect of solving practical engineering problems and improving the probability of successful flight
Active Publication Date: 2016-06-01
BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST +1
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However, under the conditions of high altitude and high Mach number (height greater than 50km, Mach number greater than 15), the existing domestic test capabilities can no longer cover the flight conditions, and wind tunnel tests alone cannot give the prediction results of aerodynamic characteristics under high altitude and high Mach number conditions. aerodynamic error
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[0024] The present invention will be described in detail below in conjunction with specific embodiments.
[0025] The method for determining the aerodynamic error under the condition of high altitude and high Mach number of the present invention is as follows:
[0026] (1) Based on the complete gas NS equation, the six-component aerodynamic characteristic prediction design result C of the aircraft under the actual high-altitude and high Mach number flight conditions is given cp .
[0027] (2) Select the typical flight angle of attack, sideslip angle, and aircraft control rudder deflection state, and carry out the same state wind tunnel in a multi-seat hypersonic wind tunnel with no less than 2 seats, aiming at the upper limit of the wind tunnel test capability of Mach number 8 Test, and repeat the test in the same state in a single wind tunnel for no less than 3 times, and obtain test data from multiple wind tunnels.
[0028] (3) Perform mathematical statistics on the test d...
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The invention belongs to the technical field of aircraft structure and specifically relates to a method for determining a pneumatic error on the condition of high altitude and a high Mach number. The method solves incompetence of ground wind tunnel experiments in view of a pneumatic predictive influence factor, reflects a special physical phenomenon in a flow with a high Mach number and a low Reynolds number, connects an aircraft theoretical profile pneumatic predictive result with an influence of a real processing manufacture horizontal and flight environment, comprehensively synthesizes pneumatic error influence sources, compensates a defect of a conventional method, derives a result with credibility, and may solve engineering practical problems. The method gives a pneumatic coefficient error value of a high-altitude high-Mach-number aircraft beyond a wind tunnel capacity condition, provides a basis for design of an aircraft control system, and increases successful flight probability.
Description
technical field [0001] The invention belongs to the technical field of aircraft structures, and in particular relates to an aerodynamic error determination method under high altitude and high Mach number conditions. Background technique [0002] In order to reasonably predict the aerodynamic characteristics of the aircraft, it is necessary to give the corresponding aerodynamic error, clearly predict the deviation, and guide the use of the aerodynamic characteristic prediction results. The existing public literature introduces few methods for determining the aerodynamic error band. Since the profile of a traditional aircraft can be covered by the ground wind tunnel test capability, the traditional aerodynamic error band is mainly given based on the ground wind tunnel test, which specifically includes two parts: the deviation between the prediction method and the test result and the test measurement deviation. However, under the conditions of high altitude and high Mach numbe...
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Inventor 周禹闵昌万关键刘斌赵晓利苗萌王美利
Owner BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST