Patent ID: 6598828
Filing Date: 2003-07-29
Classification: F41G

Abstract:
A method for configuring an instrumentation package to fit within a missile attached'to an aircraft to test said missile during a simulated test flight of said missile comprising the steps of:(a) removing a closed cycle cooling system from an interior of said missile; (b) measuring available space within the interior of said missile after removing said close cycle cooling system from the interior of said missile; (c) designing electronic modules for said instrumentation package to fit within said available space in the interior of said missile; (d) fabricating said electronic modules; (e) packaging said electronic modules to withstand environmental stress applied to said instrumentation package during the simulated test flight of said missile, and to fit within said available space in the interior of said missile, said instrumentation package including: (i) a digital recorder having a flash RAM memory, the flash RAM memory of said digital recorder recording flight data received by said digital recorder for a time period of approximately one hour; (ii) a multiplex data bus connected to said digital recorder; (iii) a digital to analog converter connected to said multiplex data bus; (iv) a plurality of sensors attached to said missile, said plurality of sensors being connected to said multiplex data bus, said plurality of sensors generating digital signals representative of said flight data; (v) said digital to analog converter converting said digital signals to an analog format providing analog signals representative of said flight data; and (vi) said multiplex data bus transferring said digital signals from said digital recorder to said digital to analog converter for conversion to said analog format by said digital to analog converter; and (f) mounting said electronic modules within said available space in the interior of said missile.