US 6,186,441 B1Granted

Device and method for determining the impact point of a ballistic missile

AssigneeEurocopter Deutschland GmbH

InventorUlrich Schneidereit

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Abstract

In an aiming or sighting device and an aiming method for determining the impact point of a ballistic flying body such as a rocket or a tube weapon projectile, specific characteristic values of the ballistic flying body are stored in a memory and an evaluating stage produces control signals in response to the specific characteristic values and in response to actual supplied system parameters. The control signals are transmitted to a display and to an adjustment drive. A model of the trajectory of the ballistic flying body is produced on the basis of all respective possible actual system parameters in an evaluating stage, whereby the trajectory is subdivided into at least two phases, each with a respective submodel. The submodel of the first phase is thereby a model with three or six degrees of freedom and the submodel of the second phase is a model with three degrees of freedom. An input unit permits adjusting the mode of operation and the correction of the impact location.

Claims28

Dependent claims

An apparatus for controlling a trajectory of a ballistic flying body, said trajectory extending from a starting point in a firing system to an impact point in a target, said trajectory having at least a first trajectory phase and a second trajectory phase between said starting point and said impact point, said apparatus comprising:

a. at least one memory (1) for storing first parameters representing characteristic values of said ballistic flying body;
b. at least one input unit (5) for entering second parameters representing actual firing system values,
c. a processing and evaluating unit (2) having inputs connected to said memory (1) and to said input unit (5) for receiving said first and second parameters for evaluation to produce a trajectory model including a first submodel corresponding to said first trajectory phase and a second submodel corresponding to said second trajectory phase for generating control signals for controlling said trajectory of said ballistic flying body in said first and second trajectory phases, and wherein a first number of parameters evaluated in said first submodel of said first trajectory phase is larger than or equal to a second number of parameters evaluated in said second submodel of said second trajectory phase for generating said control signals.

Dependencies are inferred from the claim text.