An integrated guidance and control approach in three-dimensional space for hypersonic missile constrained by impact angles.
A new robust three-dimensional integrated guidance and control (3D-IGC) approach is investigated for sliding-to-turn (STT) hypersonic missile, which encounters high uncertainties and strict impact angle constraints. First, a nonlinear state-space model with more generality is established facing to the design of 3D-IGC law. With regard to the as-built nonlinear system, a robust dynamic inversion control (RDIC) approach is proposed to overcome the robustness deficiency of traditional DIC, and then it is applied to construct the basic 3D-IGC law combining with backstepping method. In order to avoid the problems of "explosion of terms" and high-frequency chattering, an improved 3D-IGC law is further proposed by introducing dynamic surface control and continuous approximation approaches. From the computer simulation on a hypersonic missile, the proposed 3D-IGC law not only guarantees the stable flight, but also presents the precise control on terminal locations and impact angles. Moreover, it possesses smooth control output and strong robustness.
Beijing Aerospace Automatic Control Institute, Beijing 100854, China. Electronic address: k.start@163.com.
Xiaodong
X
Liu
Beijing Aerospace Automatic Control Institute, Beijing 100854, China. Electronic address: wwhuang@163.com.
Wanwei
W
Huang
Beijing Aerospace Automatic Control Institute, Beijing 100854, China. Electronic address: dulifu0328@163.com.
Lifu
L
Du
Dynamic inversion control; Dynamic surface control; Integrated guidance and control; Nonlinear control; Robust control