FLIGHT ALTITUDE AUTOMATIC CONTROL SYSTEM FOR UNMANNED FLYING VEHICLES Russian patent published in 2006 - IPC B64C13/18 G05D1/04 

FIELD: aviation and rocketry; automatic control systems equipped with auto-pilots.

SUBSTANCE: proposed system includes adder, amplifier, servo unit, elevator, feedback, free pitch gyroscope, angular-rate sensor and altimeter with outputs showing altitude and rate of its change. Outputs of free pitch gyroscope and angular-rate sensor are connected with inputs of adder and output of adder is connected with amplifier input whose output is connected to servo unit input whose output is connected with elevator and is connected to adder input through feedback. Proposed system is additionally provided with two units forming the signals of mismatch between true altitude and preset altitude; it is also provided with multiplexer and integrator. Multiplexer has two inputs: first input is connected with altimeter output of altitude magnitude and second input is connected with altimeter output of magnitude of rate of change of altitude; multiplexer has two outputs: output of magnitude of flight altitude is connected with inputs of first and second error signal forming units and output of magnitude of rate of change of altitude is connected with adder input; integrator input is connected to output of second error signal forming unit; outputs of integrator and first error signal forming unit are connected to adder inputs.

EFFECT: enhanced stabilization of flight altitude without re-adjustment after abrupt change in flight altitude.

2 dwg