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A method for simulating the flight process of an aircraft

A simulation method and technology of the flight process, applied to instruments, navigation through speed/acceleration measurement, navigation, etc., can solve the problems of not considering inertial group information, unable to assess the influence of errors, etc., to achieve simple calculation, real and reliable ground test, high efficiency effect

Active Publication Date: 2019-07-12
BEIJING AEROSPACE AUTOMATIC CONTROL RES INST +1
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Problems solved by technology

[0002] The carrier needs to verify the various technologies and stand-alone products used during the flight before the flight. Therefore, it is necessary to use the simulated flight test to comprehensively assess the flight process, guidance and control process and hardware system of the carrier. Some flight simulation methods often mainly use software calculation and simulation, without considering the real inertial group information, and cannot assess the error influence of the real inertial group in the deviation state

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  • A method for simulating the flight process of an aircraft
  • A method for simulating the flight process of an aircraft
  • A method for simulating the flight process of an aircraft

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Embodiment Construction

[0042] The flight process simulated by the present invention includes two parts, combining figure 2 , is the flight process of the launch vehicle, the first part is from 0 to time t, this part is the inertial navigation simulation section, which uses the combined output data of inertial measurement to simulate the flight process; the second part is from time t to the end of the flight, this part is the thrust Curve simulation section, which calculates the thrust and attitude changes of the aircraft according to the orbital parameters, without using the information output by the inertial set.

[0043] The body coordinate system mentioned in the present invention is specifically as follows:

[0044] The coordinate origin O is the center of mass of the carrier, the OXb axis points to the head along the longitudinal axis of the carrier, OYb is in the longitudinal symmetry plane of the carrier, and is perpendicular to the longitudinal axis (pointing to the third quadrant line of t...

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Abstract

The invention relates to a simulating method for a flying process of an air craft. The simulating method comprises the following steps: obtaining initial parameters of a secondary starting moment t of a standard orbiting aircraft; performing navigation computation to obtain inertial navigation parameters of the moment t; calculating propelling force curve compensation parameters of the moment t; performing inertial navigation computation by utilizing gyroscope data of the inertial navigation equipment and data output by an accelerometer in real time, and simulating orbital data from 0 to moment t; obtaining the parameters of the moment t, performing compensation and taking the parameters as initial parameters of a propelling force curve section, performing inertial navigation computation until flying is ended, and obtaining the orbital data from the moment t to the flying ending section, thereby completing flying simulation after a propelling force curve is accessed. According to the simulating method, true inertial group data is adopted to perform inertial navigation simulation before the secondary starting moment, and propelling force curve stimulation is adopted after the secondary starting moment, so that the true rail can be stimulated, true inertial unit characteristics are reflected, error conditions in practical flying is closer, and therefore, ground test is more true and reliable.

Description

technical field [0001] The invention relates to an aircraft flight process simulation method, which belongs to the field of aircraft ground tests. Background technique [0002] The carrier needs to verify the various technologies and stand-alone products used during the flight before the flight. Therefore, it is necessary to use the simulated flight test to comprehensively assess the flight process, guidance and control process and hardware system of the carrier. Some flight simulation methods often mainly use software calculation and simulation, without considering the real inertial group information, and cannot assess the error influence of the real inertial group in the deviation state. How to realize the track simulation closer to the actual flight state in the ground test is a technical problem to be solved urgently in this field. Contents of the invention [0003] The purpose of the present invention is to overcome the deficiencies of the prior art, provide a kind o...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C21/16
CPCG01C21/165
Inventor 徐帆尚腾李学锋曹洁王辉张宇王会霞吴骁
Owner BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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