A MICROPROCESSOR CONTROLLED PARACHUTE DEPLOYMENT SYSTEM

Abstract

In the design and development of parachutes for recovery systems (missile, test vehicle, drone, etc.) there is a need for accurate controls and measurements during testing. Relations between air speed, air density, opening forces, and drag can only be determined in a dynamic environment. Through the use of microprocessors and programming flexibility, parachute design parameters can evaluated. Improved signal to noise characteristics are obtained through error analysis and compensation techniques. The incorporation of microprocessors has become a key element in the accurate control and measurement of parachute design parameters for recovery systems.