A landing gear assembly is provided. The landing gear assembly includes a shock strut. The shock strut includes a shock strut cylinder and a shock strut piston slidably disposed within the shock strut cylinder. The landing gear assembly further includes a temperature control unit assembly disposed within the shock strut cylinder. The temperature control unit assembly is configured to, responsive to a temperature within the shock strut cylinder falling below a predetermined temperature, heat gas within the shock strut cylinder.
AIRCRAFT LANDING GEAR ENERGY ABSORPTION
17.10.2024
Patent
Elektronische Ressource
Englisch
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