Method for obtaining design attack angle for reentry flight of suborbital vehicle

Abstract

The invention discloses a method for obtaining a design attack angle for reentry flight of a suborbital vehicle. The method comprises the following steps: dividing suborbital reentry flight into a plurality of time periods, and establishing and utilizing a homomorphic prediction model for suborbital reentry flight so as to obtain time values of the time periods; by virtue of iteration of the homomorphic prediction model, obtaining design attack angle values which enables the normal acceleration for vehicle reentry to be maintained in a preset fluctuation range within the time periods; and maintaining the normal acceleration for reentry flight of the suborbital vehicle to fluctuate in the preset range in a dynamic balancing segment composed of the time periods, thus achieving the purpose of lowering the normal acceleration peak value for suborbital reentry flight.

Description

technical field [0001] The invention relates to the technical field of guidance and control, in particular to a method for obtaining a design angle of attack of a suborbital vehicle reentry flight. Background technique [0002] As the product of the organic combination of aviation and spaceflight, suborbital vehicles have the application advantages of providing regional coverage, emergency delivery and rapid response. Its active area—near space—is not only a threat to spacecraft, but also restricts aviation. It has become a new hotspot in the field of aerospace research and a growth point of strategic high technology. [0003] Aircraft reentry flight refers to the flight process of a spacecraft or aircraft re-entering the earth's atmosphere from the outside or edge of the earth's atmosphere until it lands. [0004] The re-entry flight process of the suborbital vehicle and the re-entry flight of the space shuttle have both similarities and different characteristics. The dif...

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Problems solved by technology

[0012] In the course of the research, the inventors found that in the existing angle of attack design method, the descending slope of the adjustment of the angle of attack is a fixed value, so that the normal overload during the reentry process of the suborbital vehicle with a relatively low speed is characterized by a single peak or a double peak. peak characteristics, and the peak value of the normal overload is relatively large

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