IMPROVED PRESSURE MANAGEMENT DEVICE FOR LANDING GEAR SHOCK ABSORBING STRUTS DEVELOPMENT

MODERN MILITARY AIRCRAFT ARE EXPECTED TO PROTECT THEIR OCCUPANTS IN CRASHES OF UP TO 42-FT./SEC. SINK RATE, WHICH CAUSES VERY RAPID COMPRESSION OF THE LANDING GEAR SHOCK STRUTS. IN THIS CRASH CONDITION, ONE WAY TO PREVENT EXCESSIVE PRESSURE WITHIN A STANDARD AIR/OIL SHOCK STRUT IS TO DISCHARGE FLUID THROUGH A RELIEF VALVE. THE OBJECTIVE OF THIS PROPOSED EFFORT IS TO DEMONSTRATE FEASIBILITY BY DEVELOPING AND TESTING A SUITABLE RELIEF VALVE. THE DESIGN WILL BE REFINED BY A DYNAMIC COMPUTER SIMULATION WHICH WILL TREAT ALL RELEVANT AIRCRAFT AND SHOCK STRUT PARAMETERS, INCLUDING ALL FORCES, MASSES, AND MOTIONS WITHIN THE RELIEF VALVE ITSELF. HARDWARE WILL THEN BE BUILT AND DYNAMICALLY DROP TESTED.