A Prediction Method of Unsteady Aerodynamic Parameters
An unsteady aerodynamic and prediction method technology, applied in the field of aircraft modeling, can solve the problems of low modeling accuracy and poor versatility, and achieve the effects of high prediction accuracy, strong versatility and large sample size.
Active Publication Date: 2019-07-19
NORTHWESTERN POLYTECHNICAL UNIV
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[0003] For the modeling of unsteady aerodynamic forces, commonly used methods include step function model, algebraic polynomial model, Fourier function analysis model, state space model, difference equation model and fuzzy logic model, etc. Steady aerodynamic modeling problem, but its modeling accuracy is not high, and its versatility is poor
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[0073] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.
[0074] refer to figure 1 , an embodiment of the present invention provides a method for predicting unsteady aerodynamic parameters, the method comprising:
[0075] Obtain large-scale oscillation wind tunnel test data, including triaxial force coefficient, triaxial moment coefficient, pitch angle, turntable rotation angle and tail support strut roll angle;
[0076] Obtain relevant parameters during aerodynamic modeling, such as angle of attack and sideslip ang...
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The invention discloses an unsteady aerodynamic model parameter prediction method, and relates to the technical field of aircraft modeling. Unsteady aerodynamic force is modeled and predicted through an ELM method on the basis of a large amount of wind tunnel test data, therefore, the advantages of being large in processing sample size, globally convergent, high in universality and prediction precision and the like are achieved, and unsteady aerodynamic force prediction under single-axle oscillation is achieved. Compared with other existing unsteady aerodynamic force prediction methods, the method has the advantages that the model precision is high, an accurate aerodynamic model is achieved under the condition of the large incidence angle and the great maneuver of an advanced fighter, great maneuver control can be better achieved, and therefore the favorable position is achieved in dogfight of future fighters.
Description
technical field [0001] The invention relates to the technical field of aviation vehicle modeling, in particular to a method for predicting unsteady aerodynamic parameters. Background technique [0002] Close-range combat is a symbol of the super maneuverability of advanced fighter jets, which requires fighter jets to still be able to achieve controllable command tactical maneuvers at low speeds and high angles of attack—post-stall maneuvers. Typical post-stall maneuvers include cobra maneuvers, Herbster maneuvers, vector rollers, etc. During post-stall maneuvers, the gas on the wing surface changes from a single attachment flow to a vortex flow, and the vortex breaks until it develops into a separation flow, and the gas flow lags behind. The mutual interference with the vortex system of each component is relatively serious, which leads to the nonlinearity, multi-axis coupling and hysteresis of the aerodynamic force and aerodynamic moment during the large maneuvering of the a...
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IPC IPC(8): G06F17/50
CPCG06F30/20Y02T90/00
Inventor 吕永玺章卫国史静平屈晓波李广文刘小雄张一玮
Owner NORTHWESTERN POLYTECHNICAL UNIV