Abstract
In this study, a simulation platform for an integrated navigation algorithm for hypersonic vehicles based on flight mechanics is designed. In addition, the generation method of inertial measurement unit data and satellite receiver data is introduced. First, the interface relationship between a high-precision six-degree-of-freedom (6DoF) model and the simulation platform in the launch-centered Earth-fixed frame is introduced. Three-axis theoretical specific force and angular velocity are output by the 6DoF model. Accelerometer and gyroscope error models are added, and integral processing of the specific force and angular velocity is performed to obtain velocity increment of the accelerometer and the angular increment of the gyroscope. These data are quantified to obtain the accelerometer and gyroscope pulses. The satellite’s pseudo-range and pseudo-range rate as well as its position and velocity are obtained from the theoretical position, velocity, the attitude of the hypersonic vehicle’s 6DoF model output, and the global positioning system (GPS) satellite broadcast ephemeris. The simulation data can be used for the verification of the loose and tight coupling integrated navigation algorithms. The simulation test verifies the accuracy of the designed method.
Highlights
Near space is recognized as the altitude ranging 20–100 km, which is high for airplanes and too low for satellites
The X-51A navigation system is equipped with an inertial measurement unit (IMU) and a global positioning system (GPS) receiver [4]
The Simulink integral module, module, in cycle the 1 period, ms cycle the acceleration/angular velocity information is accumulated in the 1 ms theperiod, acceleration/angular velocity information is accumulated every 1 ms every ms within ms, and the internal high-frequency sampling of the inertial device is within 5 ms, and the internal high-frequency sampling of the inertial device is simulated, sosimulated, that there sono that there is no loss of the acceleration/angular velocity high-frequency
Summary
Near space is recognized as the altitude ranging 20–100 km, which is high for airplanes and too low for satellites. The first and second approaches are limited in that the specific force and the angular velocity can only be derived from the equation of the inertial navigation system on the basis of a set flight profile in the first approach, while those in the second approach are post-processed Both the approaches are suitable for investigating the SINS/GNSS algorithm in digital simulation, they cannot be run in real time; they cannot be integrated with and adapted to the 6DoF flight dynamics model and flight control system in the real-time hardware-in-the-loop (HWIL) simulation. A trajectory generator of the SINS as a real-time closed-loop system is proposed that can be coordinated with the flight control system and the 6DoF model in the HWIL simulation It can generate the real aircraft trajectory based on real aerodynamic and engine data, and reproduce the real flying environment of the aircraft in the sky as realistically as possible. The trajectory generator has been applied in hypersonic vehicle experimental projects, and we have introduced the results of the semi-physical simulation of the hypersonic vehicle in reference [18]
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