| 摘要 |
rocketry, applicable in telecontrolled missile systems. SUBSTANCE: at missile guidance an alternating periodic missile control command is formed, a fixed guidance line is used as the reference trajectory of missile guidance. Missile guidance is accomplished with due account made for the alternating periodic command. The linear mismatching between the missile and the guidance reference trajectory, missile velocity and the missile control command relative to the guidance reference trajectory are discretely memorized. Normal acceleration of the missile relative to the guidance reference trajectory is determined, and the value of the available load factor of the missile is determined as the linear regression factor of missile normal acceleration in response to the missile control command. EFFECT: simplified procedure, reduced cost and enhanced level of automation of the testing process. 2 dwg
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