Hardware-in-the-Loop Simulation Test Method for the Inertial Navigation System of a Boost-Glide Rocket

In view of the complex movement of the boost-glide rocket, the navigation system is difficult to carry out large-scale flight tests, a hardware-in-the-loop simulation scheme is designed to test the inertial navigation system. The real flight environment of a small solid propellant boost-glide test rocket is simulated, then the flight dynamic model of the rocket is established in the real-time simulation device, the inertial navigation system is installed on the three-axis turntable. The movement of the three-axis turntable is driven according to the real flight state simulated by the real-time simulation device, and the rotation information is captured by the inertial navigation system to calculate the attitude angle. The calculated results are compared with the standard results of the three-axis turntable. The precision of navigation information and the feasibility of the hardware-in-the-loop simulation scheme are tested. The test results show that the mean deviation and standard deviation of the calculated attitude angle of the inertial navigation system are within 0.5° and 0.3°, respectively. The calculation precision meets the requirements of the flight mission, and the test method is reasonable and feasible.