Search

CN-224225286-U - Folding wing structure of aircraft

CN224225286UCN 224225286 UCN224225286 UCN 224225286UCN-224225286-U

Abstract

The utility model discloses a folding wing structure of an aircraft, which comprises wings and a folding unfolding mechanism, wherein the wings are hinged to two sides of a fuselage of the aircraft, the folding unfolding mechanism comprises a control rod, a guide rod, a compression spring, a connector and a locking piece, the top of the fuselage is provided with a mounting groove, the guide rod is fixedly connected in the mounting groove, the connector is movably connected in the mounting groove and is in sliding connection with the guide rod, two ends of the compression spring are fixedly connected with the fuselage and the connector respectively, two ends of the control rod are respectively hinged to the wings and the connector, a limiting groove is formed in the guide rod along the axial direction, a section of positioning groove is formed in the guide rod along the circumferential direction, the limiting groove is mutually communicated with the positioning groove, the locking piece is connected with the connector, the inner side of the locking piece is in sliding connection with the limiting groove, and the locking piece is used for locking the position of the connector from the limiting groove to the positioning groove. After the aircraft with the structure is launched, wing unfolding can be automatically completed, additional power is not needed, and launching efficiency is improved.

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. A folding wing structure of an aircraft is characterized by comprising wings (5) and a folding and unfolding mechanism, wherein the wings (5) are hinged to two sides of a fuselage (1) of the aircraft, and the folding and unfolding mechanism comprises a control rod (4), a guide rod (7), a compression spring (9), a connector (3) and a locking piece (8); The top of the machine body (1) is provided with a mounting groove (2), a guide rod (7) is fixedly connected in the mounting groove (2), and a connector (3) is movably connected in the mounting groove (2) and is in sliding connection with the guide rod (7), two ends of a compression spring (9) are fixedly connected with the machine body (1) and the connector (3) respectively, and two ends of a control rod (4) are hinged with a wing (5) and the connector (3) respectively; Be provided with spacing groove (14) along axial direction on guide bar (7), be provided with one section on guide bar (7) along circumference direction and arrive in place groove (13), spacing groove (14) communicate each other with arriving in place groove (13), and locking piece (8) are connected with connector (3), and locking piece (8) inboard sliding connection is in spacing groove (14), and locking piece (8) are used for entering into the position of position groove (13) realization locking connector (3) from spacing groove (14).
  2. 2. A folding wing structure of an aircraft according to claim 1, characterized in that one side of the fuselage (1) is connected with a mounting frame (6) by means of screws, the wing (5) is hinged with the mounting frame (6), and the wing (5) is hinged with the fuselage (1) by means of the mounting frame (6).
  3. 3. The folding wing structure of the aircraft according to claim 1, wherein the stabilizing strips (23) are fixedly connected to two sides of the inner wall of the mounting groove (2), the stabilizing grooves (22) are arranged on two sides of the bottom of the connector (3), and the stabilizing strips (23) are in sliding fit with the stabilizing grooves (22).
  4. 4. The folding wing structure of an aircraft according to claim 1, wherein the locking piece (8) comprises a fixed ring (17), a rotating ring (15), a limiting block (12) and a power device, wherein the fixed ring (17) is fixedly connected with the connector (3), the rotating ring (15) is rotationally connected with the fixed ring (17), the limiting block (12) is fixedly connected with the inner side of the rotating ring (15), one side of the limiting block (12) is slidingly connected in the limiting groove (14), the power device is connected with the connector (3), and the power device is used for driving the rotating ring (15) to rotate so that the limiting block (12) enters the position groove (13).
  5. 5. The folding wing structure of an aircraft according to claim 4, wherein a limit ring groove (21) is formed in one side of the fixed ring (17), a limit protrusion (20) is arranged on the inner side of the rotating ring (15), and the limit protrusion (20) is in sliding fit with the limit ring groove (21).
  6. 6. The folding wing structure of an aircraft according to claim 4, wherein the power device comprises a mounting shell (10), a rotating column (19), a coil spring (18), a driving gear (11) and a driven gear ring (16), wherein the mounting shell (10) is fixedly connected with the connector (3), one side of the rotating column (19) is rotationally connected with the mounting shell (10), two ends of the coil spring (18) are fixedly connected with the rotating column (19) and the mounting shell (10) respectively, one side of the rotating column (19) extends out of the mounting shell (10) and is fixedly connected with the driving gear (11), the driven gear ring (16) is fixedly connected with the rotating ring (15), and the driving gear (11) is meshed with the driven gear ring (16).
  7. 7. A folding wing structure of an aircraft according to claim 6, characterized in that the mounting shell (10) is detachably and fixedly connected with the connecting head (3).
  8. 8. A folding wing structure of an aircraft according to claim 1, characterized in that the connection head (3) is of T-shaped construction.
  9. 9. The folding wing structure of an aircraft according to claim 1, characterized in that the compression spring (9) is sleeved outside the guide rod (7).
  10. 10. A folding wing structure of an aircraft according to claim 1, characterized in that the wing (5) is made of carbon fibre material.

Description

Folding wing structure of aircraft Technical Field The utility model belongs to the technical field of aircrafts, and particularly relates to a folding wing structure of an aircraft. Background With the rapid iteration of the aerospace technology, the aircraft is widely applied to the fields of military reconnaissance, civil aerial photography, logistics transportation and the like, and higher requirements are put on portability, emission efficiency and flight stability. The folded wing structure can effectively reduce the volume of the aircraft before launching, is convenient to load to a launching tube, a transport platform or an unmanned aerial vehicle nest, and becomes a key design for improving the space utilization rate. In the current industry, automatic unfolding and reliable locking of folding wing mechanisms have become the core direction of technical development, and particularly in the scenes of unmanned aircrafts, tactical missiles and the like, rapid unfolding and stable locking of wings after launching are required to be realized so as to ensure the integrity of aerodynamic shapes. Under the background, the folding wing system with stable unfolding process and reliable locking structure without additional power drive gradually becomes an important field of industrial technical innovation. The existing folding wing mechanism still has some obvious technical problems in practical application, part of design depends on additional power sources such as a motor, hydraulic pressure and the like to drive and unfold, so that the weight and energy consumption of the system are increased, unfolding failure is possibly caused by power system faults, particularly in a small aircraft sensitive to weight, the carrying of the additional power device can obviously influence the flight performance, on the other hand, the reliability of the traditional locking structure is deficient, and the wing is easy to cause unlocking due to the problems of deflection, blocking and the like in the unfolding and locking process. The patent with the application number of CN202421737702.3 discloses a folding wing unmanned aerial vehicle for meteorological operation, wherein a front wing is arranged above a head end of a fuselage and is rotationally connected with the fuselage, a vertical tail is arranged on two opposite sides of a tail end of the fuselage and is rotationally connected with the fuselage, an electric regulator is electrically connected with a driving motor and is electrically connected with a battery, and the electric regulator is used for providing driving rotation power for the driving motor. The folding wing unmanned aerial vehicle with the structure completely depends on the motor control system to realize unfolding the folding wing after being launched, so that an additional power source is required to be configured, the weight and the energy consumption of the system are increased, and the unfolding failure can be caused by the failure of the power system. Disclosure of utility model The utility model aims to provide a folding wing structure of an aircraft, which aims to solve the following technical problems in the background art: The existing folding wings of the aircraft depend on additional power sources to realize unfolding, so that the weight and energy consumption of the system are increased, and the unfolding failure is easy to cause due to the failure of the power system. In order to solve the technical problems, the utility model adopts the following technical scheme: The folding wing structure of the aircraft comprises wings and folding unfolding mechanisms, wherein the wings are hinged to two sides of a fuselage of the aircraft, the folding unfolding mechanisms comprise control rods, guide rods, compression springs, connectors and locking pieces, the tops of the fuselage are provided with mounting grooves, the guide rods are fixedly connected in the mounting grooves, the connectors are movably connected in the mounting grooves and are in sliding connection with the guide rods, two ends of each compression spring are fixedly connected with the fuselage and the connectors respectively, two ends of each control rod are hinged to the wings and the connectors respectively, limiting grooves are formed in the guide rods along the axial direction, one section of each guide rod is provided with an in-place groove along the circumferential direction, the limiting grooves are mutually communicated with the in-place grooves, the locking pieces are connected with the connectors, the inner sides of the locking pieces are in sliding connection with the limiting grooves, and the locking pieces are used for entering the position of the corresponding connecting pieces from the limiting grooves to the in-place grooves to achieve locking of the connecting pieces. Further, a mounting frame is connected to one side of the fuselage through screws, the wing is hinged to the mounting frame, and the wing is hinged to