CN-121980670-A - Atmospheric parameter inversion method and system for high-speed orbiter

CN121980670ACN 121980670 ACN121980670 ACN 121980670ACN-121980670-A

Abstract

The application provides an atmospheric parameter inversion method and system for a high-speed orbit device, wherein the method comprises the steps of obtaining pressure data of a plurality of measuring points arranged on the surface of the high-speed orbit device; and inputting the pressure data into a pre-established mapping relation model to obtain and output corresponding atmospheric parameters, wherein the mapping relation model is a nonlinear model obtained by training by adopting a neural network fused with extended Kalman filtering according to the corresponding relation between the pressure data of the measuring point of the high-speed orbit device in the flight envelope and the atmospheric parameters. The application provides a design method for inverting the atmospheric data based on surface pressure reverse modeling based on a theoretical basis of a one-to-one correspondence single-value mapping relation between the surface pressure data and the corresponding atmospheric data, solves the technical problem that the traditional design method cannot acquire the surrounding environment parameters of a high-speed orbit device in real time, solves the attack angle and sideslip angle of the orbit device, solves the technical problem of acquiring the high-precision attitude angle of the high-speed aircraft, and has strong applicability and high resolving precision.

Inventors

WANG PENG
LI JUNHONG
HUANG FEI
Wei Haogong
LI QI
CHENG XIAOLI
KANG GUOJIAN

Assignees

中国航天空气动力技术研究院

Dates

Publication Date: 20260505
Application Date: 20251215

Claims (10)

1. An atmospheric parameter inversion method for a high-speed orbiter, comprising: acquiring pressure data of a plurality of measuring points arranged on the surface of the high-speed rail device; Inputting the pressure data into a pre-established mapping relation model to obtain and output corresponding atmospheric parameters; the mapping relation model is a nonlinear model obtained by training a neural network fused with extended Kalman filtering according to the corresponding relation between the measuring point pressure data of the high-speed orbit in the flight envelope and the atmospheric parameters.
2. The method of claim 1, wherein the plurality of stations comprises at least two first stations disposed on a leading surface of the high speed rail, and at least one second station disposed on an upper surface, a lower surface, a left surface, and a right surface of the high speed rail, respectively.
3. The method according to claim 1, wherein the method further comprises: before the pressure data are input into the mapping relation model, calculating the combination amount of the pressure data according to the pressure data of each measuring point; And taking the pressure data combination amount as an input of the mapping relation model.
4. A method according to claim 3, wherein the expression for calculating the combined amount of pressure data is: equation 1; Wherein, the The combined amount of the pressure data is represented, Corresponding to the front edge, the upper surface, the lower surface, the left surface and the right surface of the rail device respectively, The number of pressure measuring holes on the front edge, the upper surface, the lower surface, the left surface and the right surface of the rail device are respectively shown, The pressure value collected for the ith measurement point on the jth surface.
5. The method according to claim 1, wherein the step of establishing the mapping relation model specifically comprises: Acquiring pressure data and corresponding atmospheric parameters of the high-speed orbiter at a plurality of measuring points in various states in the flight envelope through numerical simulation or ground test, and constructing a training data set; And inputting the training data set into the neural network fused with the extended Kalman filter for training to obtain the nonlinear model.
6. The method of claim 5, wherein the expression of the mapping model is: equation 2; wherein Y represents an atmospheric data state parameter matrix, X represents an input pressure matrix, B represents a coefficient matrix, and F () represents a nonlinear function established based on a neural network fused with an extended kalman filter.
7. The method of claim 1, wherein the atmospheric parameters include at least one of angle of attack, sideslip angle, free-flowing hydrostatic and hydrodynamic pressure; the flight envelope is collectively defined by a range of Mach numbers, angles of attack, sideslip angles, and altitudes.
8. An atmospheric parameter inversion system for a high-speed orbiter, comprising: the data acquisition module is used for acquiring pressure data of a plurality of measuring points arranged on the surface of the high-speed rail device; The parameter inversion module is used for inputting the pressure data into a pre-established mapping relation model to obtain and output corresponding atmospheric parameters; the mapping relation model is a nonlinear model obtained by training a neural network fused with extended Kalman filtering according to the corresponding relation between the measuring point pressure data of the high-speed orbit in the flight envelope and the atmospheric parameters.
9. An electronic device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, which when executed by the processor performs the steps of the atmospheric parameter inversion method for a high speed rail machine according to any one of claims 1-7.
10. A computer-readable storage medium, in which a program implementing information transfer is stored, which program, when being executed by a processor, implements the steps of the atmospheric parameter inversion method for a high-speed orbiter according to any one of claims 1-7.

Description

Atmospheric parameter inversion method and system for high-speed orbiter Technical Field The invention relates to the technical field of spacecraft measurement and control, in particular to an atmospheric parameter inversion method and system for a high-speed orbit. Background Deep space exploration is one of technical hot spots in the future aerospace field, and comprises Mars exploration, asteroid exploration and the like which are carried out in various countries. Deep space probes that perform sampling return tasks typically include orbiters, landers, risers, returners, and the like. The orbiter is used as a flight relay platform, and the atmospheric data of the surrounding environment is crucial to the maneuvering performance. Because deep space probe trackers are at large altitudes, typically in excess of 100km, and at high speeds, mach numbers are greater than 10.0, conventional atmospheric data probe approaches fail. Disclosure of Invention The invention aims to provide an atmospheric parameter inversion method and system for a high-speed orbit device, and aims to solve the problems in the prior art. The embodiment of the invention provides an atmospheric parameter inversion method for a high-speed orbit device, which comprises the following steps: acquiring pressure data of a plurality of measuring points arranged on the surface of the high-speed rail device; Inputting the pressure data into a pre-established mapping relation model to obtain and output corresponding atmospheric parameters; the mapping relation model is a nonlinear model obtained by training a neural network fused with extended Kalman filtering according to the corresponding relation between the measuring point pressure data of the high-speed orbit in the flight envelope and the atmospheric parameters. The embodiment of the invention provides an atmospheric parameter inversion system for a high-speed orbit device, which comprises the following components: the data acquisition module is used for acquiring pressure data of a plurality of measuring points arranged on the surface of the high-speed rail device; The parameter inversion module is used for inputting the pressure data into a pre-established mapping relation model to obtain and output corresponding atmospheric parameters; the mapping relation model is a nonlinear model obtained by training a neural network fused with extended Kalman filtering according to the corresponding relation between the measuring point pressure data of the high-speed orbit in the flight envelope and the atmospheric parameters. The embodiment of the invention also provides electronic equipment, which comprises a memory, a processor and a computer program stored on the memory and capable of running on the processor, wherein the computer program realizes the steps of the atmospheric parameter inversion method for the high-speed orbiter when being executed by the processor. The embodiment of the invention also provides a computer readable storage medium, wherein the computer readable storage medium stores an information transmission implementation program, and the program is executed by a processor to implement the steps of the atmospheric parameter inversion method for the high-speed rail device. The embodiment of the invention has the beneficial effects that in order to solve the measurement and control requirements of the deep-space high-speed orbit device on the environmental parameters, the invention provides an atmosphere data system based on the inverse modeling inversion of the surface pressure based on the theoretical basis of the one-to-one corresponding single-value mapping relation between the surface pressure data and the corresponding atmosphere data, and simultaneously provides a design method for inverting the atmosphere data based on the inverse modeling inversion of the surface pressure based on the sensing of the pressure measuring holes arranged on the surface of the high-speed orbit device, thereby solving the technical problem that the traditional design method can not acquire the environmental parameters around the high-speed orbit device in real time, solving the technical problem that the attack angle and sideslip angle of the orbit device can be solved, and having strong engineering applicability and high resolving precision. Drawings For a clearer description of one or more embodiments of the present description or of the solutions of the prior art, the drawings that are necessary for the description of the embodiments or of the prior art will be briefly described, it being apparent that the drawings in the description that follow are only some of the embodiments described in the description, from which, for a person skilled in the art, other drawings can be obtained without inventive faculty. FIG. 1 is a flow chart of an atmospheric parameter inversion method for a high-speed orbiter in accordance with an embodiment of the present invention; FIG. 2 is a flow chart of a design me