Device for the transformation of steering control signals from one coordinate system to another

Claim 1

A system for the generation of an electrical steering command signal for an aerodynamic missile rolling about its longitudinal axis, which signal corresponds to a vector in a polar coordinate system and originates from a steering signal derived from a plane cartesian coordinate system, said system also for generating pulses such that each pulse generated corresponds to a predetermined incremental change in missile roll angle and for generating a start pulse at the beginning of each revolution of the missile, said system comprising: pulse generating means for generating a start pulse synchronized to a missile rolling about its longitudinal axis and for providing a train of pulses corresponding to the incremental change in missile roll angle; a plurality of sine an cosine-programmed, read-only memories having respective sine and cosine outputs; a binary digital counter respective to said start pulse and said train of pulses for counting the pulses of said train of pulses of said pulse generating means, said counter being resettable to zero by said start pulse, said counter supplying electrical signals corresponding to the pulse count to said sine and cosine-programmed read-only memories so that said respective sine and cosine outputs correspond to instantaneous roll angle position; a pair of digital-to-analog converters, each of the digital converters being permanently associated with a different axis of a plane cartesian coordinate system; said respective outputs of said read-only memories being supplied to said digital-to-analog converters; instantaneous steering signals also being supplied to said digital-to-analog converters, said steering signals for being multiplied by the instantaneous voltage value of the associated digital converter; and a summing element, the signals obtained at the outputs of said digital-to-analog converters being summed in said summing element, the output of said summing element being supplied as a steering command for the missile.

Claim 2

A system for the generation of an electrical steering command signal for an aerodynamic missile rolling about its longitudinal axis, which signal corresponds to a vector in a polar coordinate system and originates from a steering signal derived from a plane cartesian coordinate system, said system also for generating pulses such that each pulse generated corresponds to a predetermined incremental change in missile roll angle and for generating a start pulse at the beginning of each revolution of the missile, said system comprising: pulse generating means for generating a start pulse synchronized to a missile rolling about its longitudinal axis and for providing a train of pulses corresponding to the incremental change in missile roll angle; a plurality of sine an cosine-programmed, read-only memories having respective sine and cosine outputs; a binary digital counter respective to said start pulse and said train of pulses for counting the pulses of said train of pulses of said pulse generating means, said counter being resettable to zero by said start pulse, said counter supplying electrical signals corresponding to the pulse count to said sine and cosine-programmed read-only memories so that said respective sine and cosine outputs correspond to instantaneous roll angle position; a pair of digital-to-analog converters, each of the digital converters being permanently associated with a different axis of a plane cartesian coordinate system; said respective outputs of said read-only memories being supplied to said digital-to-analog converters; instantaneous steering signals also being supplied to said digital-to-analog converters, said steering signals for being multiplied by the instantaneous voltage value of the associated digital converter; and a summing element, the signals obtained at the outputs of said digital-to-analog converters being summed in said summing element, the output of said summing element being supplied as a steering command for the missile.

Claim 3

A system for the generation of an electrical steering command signal for an aerodynamic missile rolling about its longitudinal axis, which signal corresponds to a vector in a polar coordinate system and originates from a steering signal derived from a plane cartesian coordinate system, said system also for generating pulses such that each pulse generated corresponds to a predetermined incremental change in missile roll angle and for generating a start pulse at the beginning of each revolution of the missile, said system comprising: pulse generating means for generating a start pulse synchronized to a missile rolling about its longitudinal axis and for providing a train of pulses corresponding to the incremental change in missile roll angle; a plurality of sine and cosine-programmed, read-only memories having respective sine and cosine outputs; a binary digital counter responsive to said start pulse and said train of pulses for counting the pulses of said train of pulses of said pulse generating means, said counter being resettable to zero by said start pulse, said counter supplying electrical signals corresponding to the pulse count to said sine and cosine-programmed read-only memories so that said respective sine and cosine outputs correspond to instantaneous roll angle position; a pair of digital-to-analog converters, each of the digital converters being permanently associated with a different axis of a plane cartesian coordinate system; said respective outputs of said read-only memories being supplied to said digital-to-analog converters; instantaneous steering signals also being supplied to said digital-to-analog converters, said steering signals for being multiplied by the instantaneous voltage value of the associated digital converter; and a summing element, the signals obtained at the outputs of said digital-to-analog converters being summed in said summing element, the output of said summing element being supplied as a steering command for the missile; and also including a second pulse generating means, a second binary digital counter and a digital summing device, said second counter being initiated by a start pulse utilizing the same bit count as said counter associated with missile roll position determination, said second counter summing the pulses generated by the second pulse generating device which is associated with a launch platform, output voltages of said second counter being supplied to the inputs of said digital summing device, the output voltages of said missile roll position counter also being supplied to said digital summing device, said summing device subtracting the output voltages of said second counter from said roll position counter output voltages, the output of said summing device being the difference therebetween and being supplied to the read-only memories.

Claim 4

A system for the generation of an electrical steering command signal for an aerodynamic missile rolling about its longitudinal axis, which signal corresponds to a vector in a polar coordinate system and originates from a steering signal derived from a plane cartesian coordinate system, said system also for generating pulses such that each pulse generated corresponds to a predetermined incremental change in missile roll angle and for generating a start pulse at the beginning of each revolution of the missile, said system comprising: pulse generating means for generating a start pulse synchronized to a missile rolling about its longitudinal axis and for providing a train of pulses corresponding to the incremental change in missile roll angle; a plurality of sine and cosine-programmed, read-only memories having respective sine and cosine outputs; a binary digital counter responsive to said start pulse and said train of pulses for counting the pulses of said train of pulses of said pulse generating means, said counter being resettable to zero by said start pulse, said counter supplying electrical signals corresponding to the pulse count to said sine and cosine-programmed read-only memories so that said respective sine and cosine outputs correspond to instantaneous roll angle position; a pair of digital-to-analog converters, each of the digital converters being permanently associated with a different axis of a plane cartesian coordinate system; said respective outputs of said read-only memories being supplied to said digital-to-analog converters; instantaneous steering signals also being supplied to said digital-to-analog converters, said steering signals for being multiplied by the instantaneous voltage value of the associated digital converter; and a summing element, the signals obtained at the outputs of said digital-to-analog converters being summed in said summing element, the output of said summing element being supplied as a steering command for the missile; and also including a second pulse generating means, a second binary digital counter and a digital summing device, said second counter being initiated by a start pulse utilizing the same bit count as said counter associated with missile roll position determination, said second counter summing the pulses generated by the second pulse generating device which is associated with a launch platform, output voltages of said second counter being supplied to the inputs of said digital summing device, the output voltages of said missile roll position counter also being supplied to said digital summing device, said summing device subtracting the output voltages of said second counter from said roll position counter output voltages, the output of said summing device being the difference therebetween and being supplied to the read-only memories.