| 摘要 |
FIELD: control of two-stage missiles. SUBSTANCE: missile tracking is being accomplished according to the coordinates of flame after launch up to time movement t determined by relation $$$, where $$$-values of temperature of the upper and lower levels of use, C; T - running value of the cruise engine charge temperature, C; C - advance of transition to inertia regime, whose value is taken up to 0.5 s, after which missile tracking is conducted according to the model up to measurement of optical responder. EFFECT: enhanced reliability of tracking owing to transition to inertia regime of missile tracking before staging and up to arrival of signal from optical responder.
|
