GROUND OPERATIONAL RECOVERY TESTS OF THE LW-1 EJECTION SEAT

Abstract

TWO STATIC DEVELOPMENT FIRINGS AND FOUR STATIC DEMONSTRATION FIRINGS WERE CONDUCTED ON THE LW-1 escape system. The development firings were required to define the lateral rocket thrust moment arm and to perfect the separation latch assembly. The demonstration firings proved the system's recovery capabilities under zero attitude, zero speed condtions. Analytical substantiation of recovery at velocities up to 300 knots is presented. Catapult acceleration forces are less than 2 G's with rates of onset of acceleration less than 250 G's/second. Maximum sink rate and angle of dive recovery capabilities are achieved by the immediate allistic deployment of the personnel parachute. Design simplicity minimizes maintenance reqirements. Design simplicity and redundant gas systems optimize reiability.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1962
Accession Number
AD0287479

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aircrafts
  • Airframes
  • Assembly
  • Contracts
  • Ejection
  • Ejection Seats
  • Escape Systems
  • Government Procurement
  • Governments
  • Hydraulic Jacks
  • Moment Of Inertia
  • Parachutes
  • Pressure Transducers
  • Seats
  • Static Tests
  • Trajectories
  • Virginia

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  • Aerospace Engineering
  • Control Systems Engineering.
  • Software Engineering