A low-speed wind tunnel virtual flight experiment model attitude measurement system and its application method

Abstract

The invention discloses a low-speed wind tunnel virtual flying experimental model attitude measuring system. The system comprises an airborne power supply, an embedded attitude measuring computer, a heading attitude reference system, an inertial measuring unit and a system calibration computer; the airborne power supply, the embedded attitude measuring computer, the heading attitude reference system and the inertial measuring unit are arranged inside an aircraft model; measuring information of the heading attitude reference system and measuring information of the inertial measuring unit enter the embedded attitude measuring computer through a serial bus; a computing result of the embedded attitude measuring computer is sent to the system calibration computer through the Ethernet in a wireless mode; the system calibration computer is arranged outside a wind tunnel experimental section. According to the low-speed wind tunnel virtual flying experimental model attitude measuring system, the angular velocity and attitude angle of the model are directly measured through pure inertial measuring elements, an air flow angle is indirectly calculated and obtained by utilizing a transformational relation of the attitude angle peculiar to a virtual flying experiment and the air flow angle, and therefore attitude measuring information of the virtual flying experimental model is obtained.

Description

technical field [0001] The invention belongs to the technical field of wind tunnel experiment devices, in particular to a low-speed wind tunnel virtual flight experiment model attitude measurement system. Background technique [0002] The low-speed wind tunnel virtual flight experiment requires real-time acquisition of airflow angle, angular rate, and attitude angle information of the aircraft model, which is used for flight control system feedback or flight history parameter records. [0003] The existing measuring system can be divided into three categories according to the working principle of the sensor: [0004] (1) The combined flow field and inertial measurement system uses the wind vane sensor and the inertial measurement sensor to measure the airflow angle and attitude angle respectively; this method has the following disadvantages: First, the wind vane sensor must be installed on the outer surface of the model, which destroys the Geometric similarity, especially t...

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Problems solved by technology

[0004] (1) The combined flow field and inertial measurement system uses the wind vane sensor and the inertial measurement sensor to measure the airflow angle and attitude angle respectively; this method has the following disadvantages: First, the wind vane sensor must be installed on the outer surface of the model, which destroys the Geometric similarity, especially the key aerodynamic characteristics of sensitive parts such as the nose and wings, has a greater impact; second, the measurement range of the wind vane sensor is limited and the bandwidth is low, which cannot meet the requirements of virtual flight experiments with high angle of attack and high maneuverability; The third is that the airflow angle, angular rate, and attitude angle information come from two sensors, and each has a certain measurement error. The consistency and correlation of the data is not good, which is not conducive to the analysis of the results of the virtual flight experiment.

[0005] (2) Optical measurement system, which installs marking points on the model, uses optical measuring elements to capture the spatial coordinates of the marking points in real time, and obtains the attitude information of the model through calculation; this method has the following disadvantages: first, the system is complex and expensive; second, the system is calibrated 1. The calibration and use process is cumbersome and the stability is poor; the third is to arrange mark points on the model, which greatly increases the difficulty of model design and processing

[0006] (3) The indirect measurement system installs an encoder sensor at the rotating joint of the model support device, and obtains the attitude of the model through indirect calculation through the kinematic transfer relationship between the support device and the aircraft model; this method has the following disadvantages: First, the scope of application is narrow , it is often encountered that the encoder sensor cannot be installed on the rotating joint of the device; the second is that the kinematics calculation relationship is complicated, errors accumulate, and the measurement accuracy is not high

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