An impact absorber device (10) of a fixed landing skid of an aircraft (1) is described. The device comprises a female element (20), a male element (30) and a core (40) arranged between said female element and said male element, wherein said female element comprises a cavity and said male element comprises a support and pressure surface for supporting said core, wherein said core comprises a body with controlled plastic deformation of a metallic material. In embodiments of the invention, the core comprises an extruded body having a honeycomb structure or a body comprising a spirally wound metallic substrate.

An apparatus comprising a float bag comprising an air bladder configured to inflate when an aircraft lands in the water, a girt coupled to the air bladder and configured to attach the air bladder to the aircraft via at least one airframe fitting, and a load attenuator coupled to the girt and configured to be positioned between the girt and the airframe fitting when the float bag is attached to the aircraft, wherein the plurality of load attenuators are configured to mechanically deform in a progressive failure fashion from a first effective length to a second effective length greater than the first length in response to an applied tensile load on the load attenuators coupled to the plurality of girts and the aircraft airframe, wherein the load attenuators are selected to reduce the force with a total length that minimizes buoyancy depth of the aircraft.

An apparatus comprising a float bag comprising an air bladder configured to inflate when an aircraft lands in the water, a girt coupled to the air bladder and configured to attach the air bladder to the aircraft via at least one airframe fitting, and a load attenuator coupled to the girt and configured to be positioned between the girt and the airframe fitting when the float bag is attached to the aircraft, wherein the plurality of load attenuators are configured to mechanically deform in a progressive failure fashion from a first effective length to a second effective length greater than the first length in response to an applied tensile load on the load attenuators coupled to the plurality of girts and the aircraft airframe, wherein the load attenuators are selected to reduce the force with a total length that minimizes buoyancy depth of the aircraft.

A takeoff and landing control method of a multimodal air-ground amphibious vehicle includes: receiving dynamic parameters of the multimodal air-ground amphibious vehicle; processing the dynamic parameters by a coupled dynamic model of the multimodal air-ground amphibious vehicle to obtain dynamic control parameters of the multimodal air-ground amphibious vehicle, wherein the coupled dynamic model of the multimodal air-ground amphibious vehicle comprises a motion equation of the multimodal air-ground amphibious vehicle in a touchdown state; and the motion equation of the multimodal air-ground amphibious vehicle in a touchdown state is determined by a two-degree-of-freedom suspension dynamic equation and a six-degree-of-freedom motion equation of the multimodal air-ground amphibious vehicle in the touchdown state; and controlling takeoff and landing of the multimodal air-ground amphibious vehicle according to the dynamic control parameters of the multimodal air-ground amphibious vehicle. The method is used for takeoff and landing control of a multimodal air-ground amphibious vehicle.

An aircraft landing gear including: a sprung arm mounted to a main pivot and carrying one or more wheels; leaf springs; a transfer arm attached to each of the leaf springs; and a swinging link with a first end which is pivotally coupled to the sprung arm via a first swinging link pivot and a second end which is pivotally coupled to the transfer arm via a second swinging link pivot. The leaf springs are arranged to provide a resilient biasing force via the transfer arm and the swinging link which opposes rotation of the sprung arm about the main pivot. Each leaf spring only absorbs a portion of the landing loads, so load and stress levels in each individual spring are lower. The swinging link enables the leaf springs to be positioned remotely from the sprung arm, in a suitable position to optimize the use of space and distribute loads efficiently into the airframe.

An aircraft landing gear including: a sprung arm mounted to a main pivot and carrying one or more wheels; leaf springs; a transfer arm attached to each of the leaf springs; and a swinging link with a first end which is pivotally coupled to the sprung arm via a first swinging link pivot and a second end which is pivotally coupled to the transfer arm via a second swinging link pivot. The leaf springs are arranged to provide a resilient biasing force via the transfer arm and the swinging link which opposes rotation of the sprung arm about the main pivot. Each leaf spring only absorbs a portion of the landing loads, so load and stress levels in each individual spring are lower. The swinging link enables the leaf springs to be positioned remotely from the sprung arm, in a suitable position to optimize the use of space and distribute loads efficiently into the airframe.

The invention discloses a hand-launched unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles. The hand-launched unmanned aerial vehicle comprises a body, a tail, at least one power source and a lens bin, wherein the body comprises a middle section, a first side section and a second side section; two sides of the middle section are respectively detachably connected with the first side section and the second side section correspondingly; the tail is fixed to the middle section; the power source is fixed to the middle section; and the lens bin is fixed to the middle section and provided with a flexible cushion. The invention overcomes the technical defects in the prior art that the body maintenance cost of the hand-launched unmanned aerial vehicle is high and the lens bin is very likely to be damaged due to collision between the lens bin of the hand-launched unmanned aerial vehicle and the ground.

The invention discloses a hand-launched unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles. The hand-launched unmanned aerial vehicle comprises a body, a tail, at least one power source and a lens bin, wherein the body comprises a middle section, a first side section and a second side section; two sides of the middle section are respectively detachably connected with the first side section and the second side section correspondingly; the tail is fixed to the middle section; the power source is fixed to the middle section; and the lens bin is fixed to the middle section and provided with a flexible cushion. The invention overcomes the technical defects in the prior art that the body maintenance cost of the hand-launched unmanned aerial vehicle is high and the lens bin is very likely to be damaged due to collision between the lens bin of the hand-launched unmanned aerial vehicle and the ground.

A tail skid shock absorber including an outer shock absorber canister, a crushable indicator cartridge disposed within the outer shock absorber canister, and an indicator rod coupled to the crushable indicator cartridge so as to move with a portion of the crushable indicator cartridge as a unit.

A tail skid shock absorber including an outer shock absorber canister, a crushable indicator cartridge disposed within the outer shock absorber canister, and an indicator rod coupled to the crushable indicator cartridge so as to move with a portion of the crushable indicator cartridge as a unit.