F - Mech Eng,Light,Heat,Weapons – 42 – B
Patent
F - Mech Eng,Light,Heat,Weapons
42
B
354/3
F42B 15/01 (2006.01) F41G 7/00 (2006.01) F41G 7/36 (2006.01) G05D 1/10 (2006.01)
Patent
CA 1287684
Abstract A procedure and an apparatus for the autonomous, onboard determination of an inertial attitude reference (attitude angle T) for a guided projectile is so designed that it can be implemented with the least possible use of sensors and, as far as possible, independently of the instantaneous position of the projectile (12) relative to the apogee (A) of its ballistic trajectory (B). To this end, reference is made to the trimmed-flight behaviour that is available for the control algorithm of an autopilot (13), according to which the satisfaction of the aerodynamic equations for trimmed flight--which is to say the flight state after entry into a stable flight position on the ballistic trajectory (B)--brings about a specific control-surface position (e) as a function of local conditions and this, together with the dynamic pressure (p) as a parameter results in a defined attitude angle (T) in space. In order to take into account the variation of dynamic pressure (p) from the instantaneous flight altitude (h) and, optionally, other local conditions, a defined change in the position (e) of the control surface that is a temporary departure from the stable flight state is initiated, and the resulting change in the pitch attitude (Ts) is integrated by means of the pitch-rate gyro incorporated in the autopilot (13). This relationship is a measure of the altitude (h) and is thus available as a parameter, in order that the inertial attitude angle (T) as a function of the instantaneously measured dynamic pressure (p) at the autopilot (13) can be read out from a characteristic curve memory (19.2) free of any influence exerted by density. (Figure 2)
560549
Diehl Gmbh & Co.
Fetherstonhaugh & Co.
Sundermeyer Peter
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