Method for distinguishing aircraft motion mode
A technology of motion mode identification and motion mode, applied in simulators, instruments, adaptive control, etc., can solve problems such as complex mathematical models of aircraft systems and difficulty in making correct evaluations of aircraft performance
Inactive Publication Date: 2015-12-30
JIANGXI HONGDU AVIATION IND GRP
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Problems solved by technology
However, due to the application of active control technology, the mathematical model of the aircraft system becomes very complicated, and it is difficult to make a correct evaluation of the various performances of the aircraft
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[0066] Given the flight test data of a certain type of aircraft (H=3km, M=0.3, T=0.05), the algorithm introduced in this paper is used to solve the identification parameters.
[0067] The aircraft longitudinal short-period motion mode usually uses the following equivalent mathematical model:
[0068]
[0069] In the formula is the pitch rate (rad / s), F p is the longitudinal bar force (lb), is the equivalent gain (rad / sec / lb), is the short-period mode equivalent natural frequency (rad / sec), is the reciprocal of the short-period mode equivalent time constant (1 / sec), and τ is the equivalent time delay (sec).
[0070] Here, the first-order Bode approximation is used,
[0071]
[0072] The above formula is transformed into a continuous linear differential equation through pull-type inverse transformation:
[0073] d 3 θ · ( ...
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The invention provides a method for distinguishing an aircraft motion mode. The method is characterized by comprising the steps that a response, input by a driver, of an aircraft which is represented by an aircraft motion mode and flying quality characteristic high-order system and provided with a complex control augmentation stability system is similar to a response of a non-augmentation aircraft, and the driver can recognize the response of the aircraft through a low-order system familiar to the driver; the system is described through a continuous domain equivalent low-order system transfer function, as for a linear time invariant system, a continuous type transfer function is converted into a discrete type pulse transfer function through a bilinear transformation formula, a distinguished discrete model coefficient is converted into a continuous model coefficient, and then the continuous model coefficient is converted into an aircraft motion mode and flying quality parameter; step change and pulse responding are carried out on a two-level equivalent system with a distinguished aircraft longitudinal short-period motion mode, and it can be seen that the two-level equivalent system obtained after distinguishing is stable in response under different inputs through a simulation result.
Description
technical field [0001] The invention relates to an aircraft motion mode identification method, which belongs to the technical field of aircraft monitoring and testing. Background technique [0002] With the rapid development of modern control theory, statistical mathematics and electronic computers, the identification of aircraft aerodynamic parameters has achieved rapid development in the analysis of flight test data. At present, there are mature algorithms for parameter identification of linear aerodynamic models. Flight test centers and aircraft manufacturing companies in developed countries have a set of linear aerodynamic parameter identification programs and have accumulated rich experience. [0003] Aircraft system identification is the process of obtaining the mathematical model of the system (including the form and order of the model) and the parameters in the model according to the input and output response time histories of the aircraft system. The identification...
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Inventor 李彬王敏立赵明明胡圆圆史阳王晖叶锡涛傅侨
Owner JIANGXI HONGDU AVIATION IND GRP