Semi-physical simulation test IMU (inertial measurement unit) simulation method for carrier rocket

A semi-physical simulation and launch vehicle technology, applied in the field of semi-physical simulation of launch vehicle control systems, can solve the problems of increasing test costs

Active Publication Date: 2017-08-11
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

At present, the dynamic characteristic test completely relies on prof...

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  • Semi-physical simulation test IMU (inertial measurement unit) simulation method for carrier rocket
  • Semi-physical simulation test IMU (inertial measurement unit) simulation method for carrier rocket
  • Semi-physical simulation test IMU (inertial measurement unit) simulation method for carrier rocket

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Embodiment Construction

[0099] Below in conjunction with accompanying drawing and specific embodiment the present invention is described in further detail:

[0100] Such as figure 1 Shown is the schematic diagram of the inertial group simulator measuring dynamic characteristics of the present invention, figure 2 It is the principle diagram of the main functions of the inertial group simulator of the present invention, and the inertial group simulation method for the semi-physical simulation test of the launch vehicle of the present invention specifically includes the following steps:

[0101] Step (1), configure the parameters of the inertial group simulator according to the actual parameters of the simulated or measured inertial group, and the parameter configuration includes the installation matrix E g ,E a , the scaling factor K g 、K a , zero bias D g 、D a .

[0102] Step (2), collect externally sent attitude, speed and position information in each time period, and input the attitude, spee...

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Abstract

The invention relates to a semi-physical simulation test IMU (inertial measurement unit) simulation method for a carrier rocket. The method can be used for replacing a real IMU and a rotating table for a simulation test at the stages of semi-physical simulation debugging, testing and formal testing. In addition, there is a function of testing the real rotating table and IMU dynamic features. According to the invention, the posture, speed and position signals of a dynamical model are received, and the IMU spinning top and meter measurement signals are obtained through resolving. The main functions of the IMU and the rotating table are simulated, and the open-loop and closed-loop semi-physical simulation tests in a normal mode and a fault mode are achieved. The dynamic features of the combination of the rotating table and the IMU are measured. Moreover, the method can achieve the testing and simulation of the dynamic features of a conventional rotating table and a conventional IMU. During testing, an IMU simulator can simulate the main functions of the rotating table and IMU, and generates the meter and spinning top measurement information through the posture, speed and position. The method can replace a real equipment for testing, remarkably reduces the cost, reduces the testing complexity, and simplifies the flow.

Description

technical field [0001] The invention relates to the field of semi-physical simulation of a launch vehicle control system, in particular to an inertial group simulation method for a semi-physical simulation test of a launch vehicle. Background technique [0002] In order to ensure the reliability and value of the hardware-in-the-loop simulation test of the launch vehicle control system, the inertial set is widely used for high-precision measurement of flight and test, and dual inertial set redundancy is usually configured. At the same time, the closed-loop test also needs to configure a large-scale high-precision turntable drive inertial group, which greatly increases the test cost. [0003] The dynamic characteristics of the inertial group and the turntable have a great influence on the hardware-in-the-loop simulation test with high real-time requirements. At present, the dynamic characteristic test completely relies on professional dynamic analysis instruments, which great...

Claims

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Application Information

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IPC IPC(8): G05B17/02G01C25/00
CPCG01C25/005G05B17/02
Inventor 王迪于亚男陈海朋余薛浩范崇盛周嘉炜刘思
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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