■ View full text

IEEE Transactions on Aerospace and Electronic Systems, Vol. 49, No. 1,

https://ieeexplore.ieee.org/abstract/document/6404092

■ Researchers

Chang-Hun Lee

Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology (KAIST)

C. H. Lee*, T. H. Kim, M. J. Tahk, and I. H. Whang

■ Abstract

The work presented here investigates proposed impact angle control guidance laws with terminal acceleration constraints for a stationary or slowly moving target. These laws, called time-to-go polynomial guidance (TPG), assume the guidance command as a polynomial function of time-to-go and determine the coefficients of the guidance command to satisfy the specified terminal constraints. The closed-form trajectory solutions of the guidance command and the target look angle for lag-free systems are derived and their characteristics are investigated. Based on the results we propose a systematic method to find the guidance gains that satisfy practical limits, such as the actuator is command limit and the seeker is field-of-view (FOV) limit. A time-to-go estimation method is also discussed for implementing TPG. Nonlinear and adjoint simulations are performed to investigate the performance of TPG.

• Missiles
• Polynomials
• Trajectory
• Kinematics
• Gravity

• [신진연구자] 항공우주시스템의 유도제어 알고리즘 연구