Hypersonic boost–glide vehicle strapdown inertial navigation system / global positioning system algorithm in a launch-centered earth-fixed frame

Simulation Platform for SINS/GPS Integrated Navigation System of Hypersonic Vehicles Based on Flight Mechanics

“…In the simulation verification of the integrated navigation algorithm, the gyroscope constant drift [ 34 ] is , the gyroscope random error is , the gyroscope scale factor error is , the accelerometer constant bias is ; the accelerometer random error is , the accelerometer scale factor error is ; the initial roll angle, yaw, pitch errors are , the initial velocity error is 0.05 m/s, the initial position is 5 m [ 18 , 33 ].…”

“…Moreover, the position and velocity of a satellite as well as the pseudo-range and pseudo-range rate of a hypersonic vehicle are obtained from the 6DoF model and GPS satellite broadcast ephemeris. The simulation data can be used for the verification of the loose and tight coupling integrated SINS/GPS navigation algorithms, and it is applied in reference [ 18 ]. Compared with the two traditional trajectory generators, the trajectory generator based on flight mechanics introduced in this paper has been rarely studied in the existing literature, especially in combination with the semi-physical simulation of hypersonic aircraft.…”

“…Compared with the two traditional trajectory generators, the trajectory generator based on flight mechanics introduced in this paper has been rarely studied in the existing literature, especially in combination with the semi-physical simulation of hypersonic aircraft. In addition, the trajectory generator has been actually applied in hypersonic vehicle experimental projects, and we have introduced the results of the semi-physical simulation of the hypersonic vehicle in reference [ 18 ].…”

Comparison of geomagnetic aided navigation algorithms for hypersonic vehicles

“…In the navigation simulation of the near space hypersonic vehicles during the equilibrium gliding phase, the 0-420 s stage is pure inertial navigation, and the 420-790 s stage is inertial/geomagnetic integrated navigation. The sampling interval of magnetometers was 1 s; the sampling interval of accelerometers and gyroscopes was 10 ms; the period of Kalman filtering in integrated navigation was 1 s. Table 1 shows the parameters for the SINS (Chen et al, 2020).…”

“…The magnetometer may be quite accurate after calibration (this process is also significant), but due to the time-varying characteristic of the geomagnetic field and the interpolation/model error of the geomagnetic reference map, it is unlikely that the geomagnetic measurement value will coincide exactly with the value of the geomagnetic reference map at Note: g 0 represents standard acceleration of gravity. Reprinted from (Chen et al, 2020), Copyright 2020, with permission from Elsevier the same position. The focus of this study was the applicability of the three algorithms in hypersonic vehicle navigation.…”