Atmospheric data sensing system flight parameter calculating method and device without total pressure measuring point
A technology of flight parameters and atmospheric data, applied in measurement devices, mapping and navigation, instruments, etc., can solve the problems of lack, no total pressure algorithm accuracy and poor stability, and achieve the effect of intuitive physical meaning
Active Publication Date: 2020-04-24
BEIJING AEROSPACE TECH INST
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Problems solved by technology
Most of the calculation methods of the current atmospheric parameter sensing system are based on the situation that there are total pressure measurement points, and the research on the calculation methods in the case of no total pressure measurement points or the total pressure measurement points is very scarce, and there is no The accuracy and stability of the total pressure algorithm are not ideal
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[0032] In order to enable those skilled in the art to better understand the solutions of the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only It is an embodiment of a part of the present invention, but not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts shall fall within the protection scope of the present invention.
[0033] Those skilled in the art should understand that the embodiments of the present invention may be provided as methods, systems, or computer program products. Accordingly, the present invention can take the form of an entirely hardware embodiment, an entirely software embodiment, or an embodiment combining software and hardware aspe...
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The invention discloses an atmospheric data sensing system flight parameter calculating method and device without a total pressure measuring point. The method comprises the following steps of determining a flight parameter combination search interval at a current moment according to a flight parameter combination at a previous moment and a preset search interval setting parameter; for each flightparameter combination determined from the flight parameter combination search interval, calculating a pressure prediction value of each pressure measurement point corresponding to the flight parametercombination by adopting a shock wave expansion wave method; and comparing a calculated pressure predicted value of each pressure measuring point with a pressure measured value of each pressure measuring point, and determining the flight parameter combination corresponding to the pressure predicted value of each pressure measuring point with a minimum overall deviation with the pressure measured value of each pressure measuring point as the flight parameter combination at the current moment. In the invention, a problem that flight parameters are difficult to calculate due to lack of total pressure data is solved.
Description
technical field [0001] The invention relates to a flight parameter calculation method of an air data sensing system (FADS) without a total pressure measuring point, in particular to a flight parameter calculation method that can be used for an aircraft with a head multi-stage compression surface shape under the condition that the total pressure of the leading edge cannot be measured. Air Data Sensing System (FADS) Flight Parameter Calculation Method. Background technique [0002] Aircraft flying in the atmosphere put forward an urgent demand for the measurement of atmospheric parameters (including hydrostatic pressure, flight Mach number, angle of attack and sideslip angle, etc.). At present, pitot tubes are widely used in various aircrafts to obtain real-time atmospheric parameters. By sensing the pressure values at a group of pressure measuring points arranged on it, the required atmospheric parameter values are back-calculated with the help of specific algorithms or ...
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IPC IPC(8): G01C23/00G01D21/02
CPCG01C23/00G01D21/02
Inventor 黄俊森徐忠达吕侦军马红亮査旭
Owner BEIJING AEROSPACE TECH INST