Strapdown sensors and seeker based guidance filter design

Abstract

Precision guidance filter design for a tactical missile with a strapdown seeker aided by low-cost strapdown sensors has been addressed in this paper. The low-cost strapdown sensors consist of an IMU with 3-axis accelerometers and gyroscopes, two 3-axis magnetometers, and a barometer. Missile's position, velocity, attitude, and bias error of the barometer are considered as state variables. Since the state and measurement equations are highly nonlinear, we adopt UKF(Unscented Kalman Filter). The proposed guidance filter has a function of a navigation filter if target position error is not considered. In the case that the target position error is introduced, the proposed filter can effectively estimate the relative states of the missile to the true target. For specific engagement scenarios, we can observe that observability problems occur. Estimation performance of the proposed filter is affected by the missile's maneuver pattern.

Research on Missile System with Strapdown Guidance Technology

“…If you assume that guided missile are in equilibrium every instantaneous when calculating the ballistic, then it can be calculated the balance lift coefficient in every point of ballistic [9]. This assumption is called "instantaneous balance", it think that it is instantaneous completed when guided missile turned a state of equilibrium to another state of equilibrium.…”

Research on Line-of-Sight Rate Estimation of Strapdown Seeker

“…In view of the aforementioned problems, Low-pass filter was designed to reconstruct the inertial LOS rate [2]. Zhang Yin-chun et al estimate inertial LOS rate using particle filter [3]. Joongsup Yun and Jiao Ying-jie separately using UKF to estimate the inertial LOS rate, based on different state equations and measurement equations [4,5].…”