Aircraft telescopic wing based on stroke amplifying mechanism

A technology of stroke amplification and aircraft, applied in the direction of wing adjustment, etc., can solve the problems of poor stability, slow deformation of telescopic wings, etc., and achieve the effects of high stability, fast deployment speed, and convenient production and installation

Active Publication Date: 2021-02-26
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] In order to solve the problems of slow deformation speed and poor stability of existing aircraft telescopic wings, the present invention further proposes an aircraft telescopic wing based on a stroke amplification mechanism

Method used

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  • Aircraft telescopic wing based on stroke amplifying mechanism
  • Aircraft telescopic wing based on stroke amplifying mechanism
  • Aircraft telescopic wing based on stroke amplifying mechanism

Examples

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specific Embodiment approach 1

[0024] Specific implementation mode one: combine Figure 1 to Figure 9 Describe this embodiment, the telescopic wings of an aircraft based on the stroke amplification mechanism described in this embodiment include a drive unit and two sets of telescopic wing mechanisms, the two sets of telescopic wing mechanisms are arranged opposite to each other, and each set of telescopic wing mechanisms includes an inner wing cover Plate 1, inner wing 2, main rotary shaft 3, outer wing 4, transmission unit, locking unit and guide unit, inner wing cover plate 1 is installed on the upper end surface of inner wing 2, the front end of main rotary shaft 3 and inner wing The front end of 2 is rotationally connected, the outer wing 4 is arranged on the outside of the main rotary shaft 3, the drive unit controls the extension of the outer wing 4 along the guide unit to the outside of the inner wing 2 through the transmission unit, and the outer wing 4 is locked by the locking unit after unfolding i...

specific Embodiment approach 2

[0025] Specific implementation mode two: combination Figure 2 to Figure 3 Describe this embodiment, the drive unit described in this embodiment includes a support base 5, a fire working cylinder 6, a guide rod 7 and a slider 8, the support base 5 is fixed at the front end of the middle part between the two telescopic wing mechanisms, and the fire work The fixed end of the moving cylinder 6 is arranged on the support base 5, the guide rod 7 is arranged in the middle between the two telescopic wing mechanisms along the length direction, the movable end of the fire working cylinder 6 is slidingly connected with the guide rod 7, The movable end of 6 is connected with slide block 8 and connects. Other compositions and connection methods are the same as those in Embodiment 1.

[0026] In this embodiment, the pyrotechnic cylinder 6 is fixed by the support seat 5, and moves linearly on the guide rod 7, and drives the connected slider 8 to move.

[0027] The telescopic wing designed...

specific Embodiment approach 3

[0028] Specific implementation mode three: combination Figure 2 to Figure 4 Describe this embodiment, the two transmission units of this embodiment are symmetrically arranged on both sides of the slider 8, the transmission unit includes a crank 9, a rocker 10 and a connecting rod 11, one end of the crank 9 is rotationally connected with the slider 8, and the crank The other end of 9 is rotatably connected with the middle part of rocking bar 10, and one end of rocking bar 10 is rotatably connected with the inner side of inner wing 2, and the other end of rocking bar 10 is rotatably connected with one end of connecting rod 11, and the other end of connecting rod 11 is connected with main The middle part of the rotary shaft 3 is rotatably connected. Other compositions and connection methods are the same as those in the second embodiment.

[0029] In this embodiment, the expansion of the telescopic wings is driven by the pyrotechnic cylinder 6, which drives the slider 8 to move ...

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Abstract

The invention discloses an aircraft telescopic wing based on a stroke amplifying mechanism, relates to the technical field of aerospace equipment and equipment, and aims at solving the problems that an existing aircraft telescopic wing is low in deformation speed and low in stability. The aircraft telescopic wing comprises a driving unit and two telescopic wing mechanisms, the two telescopic wingmechanisms are arranged back to back, each telescopic wing mechanism comprises an inner wing cover plate, an inner wing, a main rotating shaft, an outer wing, a transmission unit, a locking unit and aguide unit, the inner wing cover plate covers the upper end face of the inner wing, and the front end of the main rotating shaft is rotationally connected with the front end of the inner wing; the outer wing is arranged in the outer side of the main rotating shaft, the driving unit controls the outer wing to extend towards the outer side of the inner wing along the guide unit through the transmission unit, and the outer wing is locked through the locking unit after being unfolded in place. The aircraft telescopic wing is used for aerospace crafts.

Description

technical field [0001] The invention relates to the technical field of aerospace equipment and equipment, in particular to an aircraft retractable wing based on a stroke amplification mechanism. Background technique [0002] At present, the geometric shape of most aircraft is basically fixed, and its system model does not change much. The limitation is that in the same atmospheric environment, it can only do some specific flights and complete some special tasks. [0003] As the application of aircraft in the military and civilian fields becomes more and more complex, there is an urgent need for a device that can have a larger flight airspace and speed range, can take into account high and low altitudes, high and low speeds, and even take off from the ground and fly through the atmosphere to perform various tasks. Aircraft for complex tasks such as reconnaissance and strike. It is difficult for traditional aircraft to adapt to such a wide range of changes in flight environme...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C3/56
CPCB64C3/56
Inventor 郭宏伟肖洪张健鹏杨广赵冲田志东刘荣强邓宗全
Owner HARBIN INST OF TECH
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