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CN-224225285-U - Airfoil locking structure

CN224225285UCN 224225285 UCN224225285 UCN 224225285UCN-224225285-U

Abstract

The utility model discloses an airfoil locking structure which is arranged on an aircraft. The structure comprises a power mechanism and a fixing mechanism, wherein the power mechanism is arranged between a folding wing and a machine body and is used for driving the folding wing to unfold, the fixing mechanism comprises a locating block, an installation block, a limiting pin, a first compression spring, a limiting plate, a contact rod and a second compression spring, wherein one side of the bottom of the installation block is provided with a vertical first installation hole which is matched with the limiting hole of the machine body, the limiting pin is movably installed in the hole and is connected with the first compression spring, the other side of the installation block is transversely provided with a communicated installation groove and a second installation hole, a limiting plate belt is movably installed in the installation groove through the hole, the plate body of the limiting plate belt can block the limiting pin and is used for releasing the limiting pin through the hole, and the contact rod is movably connected in the second installation hole and is fixedly connected with the limiting plate through the second compression spring. The structure realizes a high-reliability unfolding locking process by a pure mechanical design, ensures that the folding wing is stably fixed under pneumatic load, and has reasonable integral structure, small volume and light weight.

Inventors

  • ZENG YI
  • XU HONGZHOU

Assignees

  • 成都诚利腾科技有限公司

Dates

Publication Date
20260512
Application Date
20250619

Claims (10)

  1. 1. The wing surface locking structure is arranged on an aircraft and is characterized by comprising a power mechanism (1) and a fixing mechanism (5), wherein the power mechanism (1) is arranged between a folding wing (2) and a fuselage (3) of the aircraft, the power mechanism (1) is used for driving the folding wing (2) to be unfolded, and the fixing mechanism (5) comprises a locating block (4), a mounting block (9), a limiting pin (17), a first compression spring (7), a limiting plate (19), a contact rod (13) and a second compression spring (14); A first mounting hole (8) is formed in one side of the bottom of the mounting block (9) in the vertical direction, a limiting hole (16) matched with the first mounting hole (8) is formed in the machine body (3), a limiting pin (17) is movably arranged in the mounting hole, two ends of a first compression spring (7) are respectively connected with the limiting pin (17) and the mounting block (9), a mounting groove (18) and a second mounting hole (12) which are mutually communicated are formed in one side of the bottom of the mounting block (9) in the transverse direction, the mounting groove (18) is communicated with the first mounting hole (8), the limiting plate (19) is movably arranged in the mounting groove (18), a through hole (6) is formed in one side of the limiting plate (19), a plate body of the limiting plate (19) is used for blocking the limiting pin (17), the limiting pin (17) is released through the hole (6), one end of the contact rod (13) is fixedly connected in the second mounting hole (12), and two ends of the second compression spring (14) are respectively connected with the contact rod (13) and the mounting block (9).
  2. 2. The airfoil locking structure according to claim 1, wherein the power mechanism (1) comprises a connector (21), a rotating head (20), a fixing column (24), a fixing rod (22) and a coil spring (23), wherein the fixing column (24) is fixedly connected with the machine body (3), the connector (21) is fixedly connected with the folding wing (2), the rotating head (20) is fixedly connected with the connector (21) and the rotating head (20) is further rotatably connected with the fixing column (24), the fixing rod (22) is fixedly connected with the connector (21), one end of the coil spring (23) is fixedly connected with the fixing column (24), and the other end of the coil spring is connected with the fixing rod (22).
  3. 3. An airfoil locking arrangement according to claim 2, characterized in that a bearing (25) is provided between the rotating head (20) and the stationary post (24).
  4. 4. An airfoil locking arrangement according to claim 2, characterized in that the outer side of the bottom of the joint (21) is provided with a ring of extensions.
  5. 5. An airfoil locking arrangement according to claim 1, characterized in that the contact lever (13) is fixedly connected with the mounting part (10), and the second compression spring (14) is connected with the mounting part (10).
  6. 6. An airfoil locking arrangement according to claim 1, characterized in that a limit part (11) is provided on one side in the second mounting hole (12), the limit part (11) being adapted to limit the range of movement of the contact lever (13).
  7. 7. An airfoil locking arrangement according to claim 1, characterized in that the diameter of the top side of the limit pin (17) is smaller than the diameter of the bottom side, the top side of the limit pin (17) being inserted into the first compression spring (7).
  8. 8. An airfoil locking arrangement according to claim 1, characterized in that the end of the contact lever (13) remote from the limiting plate (19) is of a rounded configuration.
  9. 9. An airfoil locking arrangement according to claim 1, characterized in that the diameter of the through hole (6) in the limiting plate (19) is larger than the diameter of the bottom side of the limiting pin (17).
  10. 10. An airfoil locking arrangement according to claim 1, characterized in that the bottom of the limiting aperture (16) is provided with a release aperture (15).

Description

Airfoil locking structure Technical Field The utility model belongs to the technical field of aircrafts, and particularly relates to an airfoil surface locking structure. Background The technology of unfolding and locking the folding wings of the aircraft is continuously innovated along with the rapid development of the aerospace field in recent years. The early aircraft mostly adopts fixed folding wings, but the structure is stable, but the occupation space is big, and the demand of modern aircraft to warehousing and transportation convenience and launching flexibility is difficult to satisfy. Therefore, the folding wing technology gradually becomes the mainstream, and the folding wings are driven to be unfolded through elastic elements such as springs, torsion springs and the like, and are combined with limiting and locking structures to realize locking. For example, part of the schemes adopt torsion springs to store potential energy to drive the folding wings to rotate, and meanwhile, mechanical locking is completed through wedge-shaped locking parts or spring locking pins, so that the space utilization rate of the aircraft is remarkably improved. However, the traditional design still has the problems of complex structure force transmission, complex debugging and the like, and most schemes are not optimized for key indexes such as folding span opening time, locking precision and the like. Along with the popularization of unmanned aerial vehicles and intelligent aircrafts, a pure mechanical locking scheme with light weight, low power consumption and high reliability becomes an important direction of industry development. Despite the advances made in the art, many technical bottlenecks are faced. On the one hand, the conventional electrically or hydraulically driven locking systems need to be continuously powered, which not only increases the energy burden of the aircraft, but also causes significant increases in volume and weight due to the complex structure, especially in small aircraft. For example, electric drives require high torque motors and high ratio gearboxes, require severe structural strength to the root of the folding wing, and are expensive to maintain. On the other hand, depending on the locking mode of the electric control system, there is a reliability hidden trouble, for example, the locking of the servo mechanism is easily affected by electromagnetic interference or mechanical jamming, and may fail in emergency. In addition, part of mechanical locking schemes simplify the structure, but the manual operation is needed to be unfolded or complex multi-power source cooperation is relied on, so that the automatic combat requirement is difficult to meet. For example, the traditional pin puller requires additional hardware to monitor the unlocked state, and the pin shaft is easy to be blocked with the folding wing when retracted, so that the locking failure is caused. Therefore, how to realize full-process automation of folding wing unfolding and locking without additional energy sources, and simultaneously, to give consideration to aerodynamic load resistance and maintenance convenience becomes a core problem to be broken through in the prior art. Disclosure of utility model The utility model aims to provide an airfoil surface locking structure which is used for solving the following technical problems in the background art: Conventional hydraulic conventional electric or hydraulic driven locking systems require continuous energy supply, increasing the energy burden of the aircraft, and also result in significant increases in volume and weight due to the complex structure. In order to solve the technical problems, the utility model adopts the following technical scheme: The wing surface locking structure is arranged on an aircraft and comprises a power mechanism and a fixing mechanism, wherein the power mechanism is arranged between a folding wing and a fuselage of the aircraft and is used for driving the folding wing to be unfolded, the fixing mechanism comprises a positioning block, a mounting block, a limiting pin, a first compression spring, a limiting plate, a contact rod and a second compression spring, a first mounting hole is formed in the vertical direction of one side of the bottom of the mounting block, a limiting hole matched with the first mounting hole is formed in the fuselage, the limiting pin is movably arranged in the mounting hole, two ends of the first compression spring are respectively connected with the limiting pin and the mounting block, a mounting groove communicated with each other is formed in the transverse direction of one side of the bottom of the mounting block and is communicated with the first mounting hole, the limiting plate is movably arranged in the mounting groove, one side of the limiting plate is provided with a through hole, a plate body of the limiting plate is used for blocking the limiting pin, the contact rod is movably connected in the second moun