Adapting device for forced landing of aircraft
A technology of aircraft and receiving platform, which is applied in the fields of aircraft forced landing devices and aircraft landing devices, which can solve problems such as unsatisfactory, aircraft landing gear cannot be put down, and achieve good versatility
Active Publication Date: 2014-08-13
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology
The technical problem to be solved is that the forced landing device can effectively protect personnel, equipment and property when the landing gear of the aircraft cannot be put down or the position is not ideal, and the landing system of the recoverable spacecraft is not working properly. Safety
Method used
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Embodiment Construction
[0033] Such as figure 1 As shown, a communicator 1 is arranged at the front end of the forced landing device of the present invention near the landing side of the aircraft. The function of the communicator is to transmit landing information such as the aircraft landing attitude to the control machine 3 through the signal line 2, as shown in FIG. image 3 shown. The controller controls the stiffness of the variable-stiffness adjustment buffer device 4 , the damping in the damper 5 , the peripheral rotation device 6 and the rotation device 12 indirectly by controlling the hybrid power source 11 . The hybrid power source 11 mainly consists of an electric motor, a hydraulic power source, etc., depending on the type of power required by the driving device. Such as image 3 As shown, an electro-hydraulic type can be used in the stiffness adjustment buffer device 4, and similar devices are widely used in the field of structural dynamics. The damper 5 can adopt a hydraulic damper, ...
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The invention discloses an adapting device for forced landing of an aircraft, comprising a track, an adapting platform arranged at the front end of track, a communicator, a circumferential rotation device, a rigidity adjustment and buffer device, a rotating device, a power source and a controller, wherein the communicator is arranged at the front end of the adapting platform and is used for receiving the landing information of the aircraft; the circumferential rotation device is arranged at the lower end of the adapting platform and is used for enabling the adapting platform to rotate in an adapting platform plane; the rigidity adjustment and buffer device is used for adjusting the support rigidity at the lower end of the adapting platform; the rotating device is arranged at the lower end of the adapting platform and is used for enabling the adapting platform to rotate around a spherical hinge; the power source is connected with the circumferential rotation device for centering of the adapting platform; and the controller is used for receiving landing information sent by the communicator, and controls the power source based on the received landing information of the aircraft. The adapting device in the invention can effectively undertake aircrafts with different landing weights and landing postures, and has good popularity.
Description
technical field [0001] The invention relates to the field of aircraft landing gear, in particular to the field of aircraft forced landing devices. Background technique [0002] The tires and pillars of the landing gear generally support the aircraft on the ground. In the air, due to the need to reduce flight resistance, they are stored in the landing gear compartment. Modern aircraft are generally equipped with hydraulic or telex systems to control the retraction process of the landing gear. Before landing, the landing gear should be lowered to the designated position so that the landing gear can well complete the function of cushioning and supporting the aircraft. However, when the landing gear system of the aircraft fails, the landing gear will remain in the retracted position and cannot be lowered. Therefore, the aircraft must adopt an emergency landing method, that is, a belly landing. This landing method will cause a certain degree of damage to airborne equipment and p...
Claims
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IPC IPC(8): B64F1/02
Inventor 聂宏刘向尧魏小辉
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS