SINS/BDS Integrated Navigation for Hypersonic Boost-Glide Vehicles in the Launch-Centered Inertial Frame

Kai Chen,Jun Zhou,Xiaofeng Wu,Fuqiang Shen,Yongmin Zhong

doi:10.1155/2020/7503272

Abstract

According to the trajectory specialty of hypersonic boost-glide vehicles, a strapdown inertial navigation system/BeiDou navigation satellite system (SINS/BDS) algorithm based on the launch-centered inertial (LCI) frame for hypersonic vehicles is proposed. First, the related frame system, especially the launch earth-centered inertial (LECI) frame, and the SINS mechanization in the LCI frame are introduced. Second, SINS discrete updating algorithms in the LCI frame for the compensation of coning, sculling, and scrolling effects are deduced in the attitude, velocity, and position updating algorithms, respectively. Subsequently, the Kalman filter of the SINS/BDS integrated navigation in the LCI frame is obtained. The method of converting BDS receiver position and velocity from the Earth-centered Earth-fixed (ECEF) frame to the LCI frame is deduced through the LECI frame. Finally, taking the typical hypersonic boost-glide vehicles as the object, the SINS/BDS algorithm vehicle field test and hardware-in-the-loop simulation are performed.

Highlights

A hypersonic vehicle is an aircraft that has the ability to fly and cruise for a long time at more than five times the speed of sound in near space; it is called a “near-space hypersonic vehicle” [1]. e near space is the atmospheric space 20–100 km from the ground, and it is located below the low-orbit satellite operation area and above the traditional aircraft flight area
If the local horizontal frame is used as the navigation coordinate system of the hypersonic boost-glide vehicle, the attitude angle will be singular during the navigation calculation process. erefore, the launch-centered inertial (LCI) frame is often used as the navigation coordinate system of the launch vehicle, which will not cause the attitude angle to be singular, making the LCI frame more advantageous over the local horizontal frame [4, 12, 13]
In the present study, based on the high-dynamic characteristics of hypersonic vehicles, we propose updating algorithms for the attitude, velocity, and position of strapdown inertial navigation as well as a SINS/BDS integrated navigation system in the LCI frame

Summary

Introduction

A hypersonic vehicle is an aircraft that has the ability to fly and cruise for a long time at more than five times the speed of sound in near space; it is called a “near-space hypersonic vehicle” [1]. e near space is the atmospheric space 20–100 km from the ground, and it is located below the low-orbit satellite operation area and above the traditional aircraft flight area. If the local horizontal frame is used as the navigation coordinate system of the hypersonic boost-glide vehicle, the attitude angle will be singular during the navigation calculation process. According to the navigation solutions in the LCI frame, scholars from all over the world have designed some hypersonic vehicle flight control algorithms. Our group proposed an algorithm of SINS in the LCI frame for hypersonic boost-glide vehicles and presented a solution in the local horizontal frame from the LCI frame. In the present study, based on the high-dynamic characteristics of hypersonic vehicles, we propose updating algorithms for the attitude, velocity, and position of strapdown inertial navigation as well as a SINS/BDS integrated navigation system in the LCI frame. We conduct a test on the SINS/BDS integrated navigation vehicle and hardware-in-the-loop (HWIL) simulation of the LCI frame

SINS Mechanization in Launch-Centered Inertial Frame

Relationship between Frame Systems

Initial Value of Launch Time

SINS Error Equation in the Launch-Centered Inertial Frame

Conclusions