Abstract: A landing gear for an aircraft includes a landing strut having proximal and distal ends with the proximal end couplable to the fuselage of the aircraft. The landing strut includes a gas chamber, a liquid chamber, a cylinder and a piston that is movable relative to the cylinder between extended and retracted positions. A wheel is coupled to the distal end of the landing strut. A force sensor is disposed between an extend stop surface of the piston and the chamber. Pressurized gas in the gas chamber biases the piston to the extended position such that the force sensor experiences a preload force. The force sensor is configured to detect a reduction in the preload force during a landing maneuver responsive to contact between the wheel and a landing surface.

Abstract: A load sensor includes a compressible body positionable between two surfaces. The compressible body has a plurality of aligned layers including first and second outer shims with a middle shim positioned therebetween and with a resilient material interposed between each adjacent shim. The second outer shim has a gap that exposes an unsupported area of the middle shim. A strain gauge is coupled to the middle shim in the unsupported area. When the compressible body is uncompressed, the resilient material interposed between the first outer shim and the middle shim has a substantially uniform thickness. When the compressible body is compressed between the two surfaces, the resilient material aligned with the unsupported area and interposed between the first outer shim and the middle shim has a nonuniform thickness such that the middle shim deflects away from the first outer shim in the unsupported area, thereby deforming the strain gauge.

Abstract: A landing gear for an aircraft includes a landing strut having proximal and distal ends with the proximal end couplable to the fuselage of the aircraft. The landing strut includes a gas chamber, a liquid chamber, a cylinder and a piston that is movable relative to the cylinder between extended and retracted positions. A wheel is coupled to the distal end of the landing strut. A force sensor is disposed between an extend stop surface of the piston and the chamber. Pressurized gas in the gas chamber biases the piston to the extended position such that the force sensor experiences a preload force. The force sensor is configured to detect a reduction in the preload force during a landing maneuver responsive to contact between the wheel and a landing surface.