CN116588318A - Folding wing of aircraft - Google Patents
Folding wing of aircraft Download PDFInfo
- Publication number
- CN116588318A CN116588318A CN202310434221.9A CN202310434221A CN116588318A CN 116588318 A CN116588318 A CN 116588318A CN 202310434221 A CN202310434221 A CN 202310434221A CN 116588318 A CN116588318 A CN 116588318A
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- China
- Prior art keywords
- rocker arm
- wing
- folding
- limiting
- push rod
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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- 230000007246 mechanism Effects 0.000 claims description 24
- 125000006850 spacer group Chemical group 0.000 claims description 20
- 238000004880 explosion Methods 0.000 claims description 19
- 230000006835 compression Effects 0.000 claims description 8
- 238000007906 compression Methods 0.000 claims description 8
- 230000009471 action Effects 0.000 description 5
- 230000000903 blocking effect Effects 0.000 description 3
- 241000276425 Xiphophorus maculatus Species 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000004806 packaging method and process Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000000452 restraining effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
Abstract
The utility model provides a folding wing of aircraft, this folding wing contains two symmetrical flank and a connector, and the front end of two flanks articulates respectively on the connector, and under the wing folding state, the tail end of two flanks is close to, and the tail end of two flanks is kept away from under the wing unfolding state, the front end of two flanks pass through connecting axle and rocker arm structure and connector symmetry connection, rocker arm structure contain rocking arm and cam, the center and the connecting axle of cam are fixed, are equipped with spacing step on the side margin of cam, the rocking arm radially extends with the center of cam.
Description
Technical Field
The application is suitable for the field of aircraft design, in particular to a folding wing structure of an airborne launching aircraft.
Background
The folding wings can reduce the transverse dimension of the aircraft, reduce the size of the packaging box, facilitate storage, transportation and emission, and greatly increase the applicability of the aircraft. The aircraft adopting the folding technology has the advantages that the front wing of the aircraft is folded, and the rear wing of the aircraft can be unfolded rapidly, so that the aircraft can fly stably, and the unmanned aircraft has immeasurable effects on improving the maneuverability, fight and fight time survivability of the aircraft.
The wing folding and unfolding mechanism is used for ensuring that the wing is folded and unfolded smoothly, and the performance of the wing folding and unfolding mechanism directly influences the rapidity, stability and reliability of wing unfolding. In the wing unfolding process, the unfolding mechanism needs to transmit load and meet the requirement of a specified movement function, and a method for rapidly unfolding and locking the wing is a key of folding wing design, and directly relates to whether an aircraft can normally fly and whether the aircraft can successfully execute tasks.
Disclosure of Invention
The application aims to provide a folding wing of an aircraft, which can be unfolded and locked rapidly after the aircraft is launched, so that the aircraft can fly stably.
The utility model provides a folding wing of aircraft, its characterized in that, this folding wing contains two symmetrical flank and a connector, and the front end of two flanks articulates respectively on the connector, and under the wing folding state, the tail end of two flanks is close to, and the tail end of two flanks is kept away from under the wing open state, the front end of two flanks pass through connecting axle and rocking arm structure and connector symmetry connection, rocking arm structure contain rocking arm and cam, the center and the connecting axle of cam are fixed, are equipped with spacing step on the side reason of cam, the rocking arm radially extends with the center of cam.
The folding wing of the aircraft is characterized in that the connector body is of a platy structure, two side wings are symmetrically hinged to the lower surface of the connector body through pin shafts respectively, the rocker arm structure is located on the upper surface of the connector, a driving mechanism and a limiting mechanism of the side wings are arranged on the connector, the driving mechanism drives the side wings to open through the rocker arm structure, and the limiting mechanism limits the rotating direction and the rotating angle of the rocker arm structure.
The folding wing of the aircraft is characterized in that the driving mechanism comprises an explosion actuator and a push rod, the explosion actuator drives rocker arms of the rocker arm structure through the push rod, the explosion actuator and the push rod are located on symmetrical axes of the two rocker arms, the push rod is movably embedded in a guide hole of the support, a stroke slot hole is formed in the push rod, a limit rod is arranged in the guide hole of the support, and the limit rod limits the movement stroke of the push rod through the stroke slot hole.
The folding wing of the aircraft is characterized in that the limiting structure comprises a limiting hook, two horizontal limiting pins and four vertical limiting pins, wherein the limiting hook is embedded on a connector body, and in a wing folding state, the front ends of rocker arms of two side wing rocker arm structures are opposite and closest to each other, and the rocker arm states of the two side wing rocker arm structures are limited by the limiting hook; two horizontal spacer pins and four vertical spacer pins correspond to each other and set up in the vicinity of two rocker arm structures respectively, and every rocker arm structure corresponds a horizontal spacer pin and two vertical spacer pins, and the horizontal spacer pin leads to spacing step restriction rocker arm structure to inboard rotation, prevents that the flank from expanding the back and turning back, and two vertical spacer pins limit the folding and the expansion angle of rocker arm structure respectively through the rocking arm, prevent that the flank from excessively folding and excessively expanding.
The folding wing of the aircraft is characterized in that the limiting hook is a cantilever-shaped hook, the rear end of the limiting hook is hinged in a groove cavity of the connecting seat through a torsion spring, the front end of the limiting hook is a groove-shaped hook, the front groove wall is used for limiting the rocker arm, the side wing is in a folding state, an inclined plane matched with the front end of the push rod is arranged on the rear groove wall, when the push rod advances, the push rod is crimped at the top end of the rear groove wall through the inclined plane, the limit of the front groove wall to the rocker arm is released, and the rocker arm is pushed to drive the side wing to expand.
The folding wing of the aircraft is characterized in that the horizontal limiting pin is an elastic limiting pin, the horizontal limiting pin is horizontally inlaid in the shaft cavity of the support through a compression spring, the front end of the horizontal limiting pin is in compression joint with the cam of the rocker arm structure, when the push rod pushes the rocker arm to drive the side wing to rotate to a preset unfolding position, the front end of the horizontal limiting pin is just limited at a step of the cam, and the horizontal limiting pin limits the rocker arm structure to rotate inwards to prevent the side wing from folding back after being unfolded.
The folding wing of the aircraft is characterized in that two vertical limiting pins corresponding to each rocker arm structure are two vertical pin shafts respectively fixed on two sides of the rocker arm and respectively limit the inward folding angle and the outward unfolding angle of the rocker arm.
The folding and unfolding mechanism for the side wings has the advantages that the folding and unfolding mechanism for the side wings is simple, the side wings can be unfolded, positioned and locked quickly, the side wings can be fixed when the side wings are folded, and the reliability of the whole mechanism is high and the manufacturability and interchangeability are good. 1) The electric explosion tube in the explosion actuator generates impact force to push the rocker arm to rotate so as to realize the rapid unfolding action of the aircraft wing, thereby being capable of providing lift force for the aircraft in time and keeping stable flight. 2) Through the characteristics of the combined action of the horizontal limiting pin and the vertical limiting pin, the locking of the folding wing span after being unfolded to a set angle is realized, the structure is simple and reliable, the folding wing is folded to reduce the size, and meanwhile, the weight of the aircraft is reduced. 3) The limiting hooks are used for restraining the rocker arms, so that the wing is locked after being folded, and the folded state of the aircraft is effectively ensured to be fixed. 4) The mechanism has the advantages of simple structure, easy realization, space and weight saving, capability of realizing the functions of folding, unfolding and locking the wing surface, suitability for various aircrafts and capability of solving the technical difficulties of realizing the functions of folding, unfolding and locking the wing under the conditions of small space and small volume.
Drawings
FIG. 1 is a schematic view of a wing fold condition
FIG. 2 is a schematic view of an extended wing
Fig. 3A-A are schematic views of the structural relationship between the horizontal stop pin and the rocker arm in the wing fold locking state.
Fig. 4B-B are schematic diagrams of wing fold locking state drive mechanism and limit hook relationship.
Fig. 5B-B are schematic diagrams of wing deployment state drive mechanism and limit hook relationship.
FIG. 6 is a schematic view of a limiting hook structure
The numbering in the figures illustrates: 1. the hydraulic pressure type hydraulic pressure control device comprises a side wing, a connector, a first vertical limiting pin, a rocker arm structure, a connecting shaft, a horizontal limiting pin, a push rod, an explosion actuator, a limiting rod, a second vertical limiting pin, a limiting hook, a compression spring, a torsion spring and an inclined plane, wherein the side wing, the connector, the first vertical limiting pin, the rocker arm structure, the connecting shaft, the horizontal limiting pin, the push rod, the explosion actuator, the limiting rod, the second vertical limiting pin, the limiting hook, the compression spring, the torsion spring and the inclined plane.
Detailed Description
Referring to the drawings, as shown in fig. 1 and 2, the folding wing of the application mainly comprises a side wing 1, a connector 2, a rocker arm structure 4, a connecting shaft 5, a horizontal limiting pin 6, a push rod 7, a first vertical limiting pin 3, a second vertical limiting pin 10, a limiting hook 11, an explosion actuator 8 and the like. In the wing folded state, the tail ends of the two side wings 1 are close, and in the wing unfolded state, the tail ends of the two side wings 1 are far away. In practice, the side wings 1 are mounted on the outside of the aircraft and the connectors 2 are mounted in the aircraft by countersunk bolts. The connector 2 body is a platy structure, two side wings 1 are symmetrically hinged to the lower surface of the connector 2 through connecting shafts 5 respectively, the rocker arm structure 4 is located on the upper surface of the connector 2, a driving mechanism and a limiting mechanism of the side wings 1 are arranged on the connector 2, the driving mechanism drives the side wings 1 to open through the rocker arm structure 4, and the limiting mechanism limits the rotating direction and the rotating angle of the rocker arm structure 4.
The rocker arm structure 4 comprises a rocker arm and a cam, the center of the cam is fixed with the connecting shaft 5, a limiting step is arranged on the side edge of the cam, and the rocker arm radially extends from the center of the cam.
The driving mechanism comprises an explosion actuator 8 and a push rod 7, the explosion actuator 8 drives the rocker arms of the rocker arm structure 4 through the push rod 7, the explosion actuator 8 and the push rod 7 are positioned on the symmetrical axes of the two rocker arms, the push rod 7 is movably embedded in a guide hole of the connector 2, a travel slot hole is formed in the push rod 7, a limit rod 9 is arranged in the guide hole of the connector 2, the limit rod 9 limits the movement travel of the push rod 7 through the travel slot hole, and the push rod 7 is prevented from flying out under the impact of the explosion actuator 8.
The limiting structure comprises a limiting hook 11, two horizontal limiting pins 6, two first vertical limiting pins 3 and two second vertical limiting pins 10, wherein the limiting hook 11 is embedded on the body of the connector 2, and in the wing folding state, the front ends of the rocker arms of the rocker arm structures 4 of the two side wings 1 are opposite and are nearest to each other, and the rocker arm states of the two side wing rocker arm structures are limited by the limiting hook 11; two horizontal spacer pins 6 and four vertical spacer pins correspond to each other and set up in the vicinity of two rocker arm structures respectively, every rocker arm structure 4 corresponds a horizontal spacer pin 6 and a first vertical spacer pin, a second vertical spacer pin, horizontal spacer pin 6 passes through spacing step restriction rocker arm structure 4 on the cam and rotates inwards, prevent to turn back again after flank 1 expandes, first vertical spacer pin 3 and second vertical spacer pin 10 are fixed in the both sides of rocker arm structure 4, be two vertical round pins, the outside of round pin axle is equipped with the rubber sleeve, through the folding and expansion angle of rocking arm restriction rocker arm structure 4 respectively, prevent that flank 1 from excessively folding and excessively expanding.
The limiting hook 11 is a cantilever-shaped hook, the limiting hook 11 is connected in the groove cavity of the connector 2 through a screw in a threaded manner, the rear end of the limiting hook 11 protrudes out of the upper surface of the groove cavity of the connector through a torsion spring 13, the front end of the limiting hook 11 is a groove-shaped hook, the front groove wall is used for limiting a rocker arm, a side wing 1 is in a folded state, an inclined surface 14 matched with the front end of the push rod 7 is arranged on the groove wall on the rear side, when the push rod 7 advances, the push rod 7 is crimped on the top end of the groove wall on the rear side through the inclined surface, the limit of the groove wall on the rocker arm on the front side is relieved, and the rocker arm structure is pushed to drive the side wing 1 to be unfolded.
As shown in fig. 3, the horizontal limiting pin 6 is an elastic limiting pin, the horizontal limiting pin 6 is horizontally embedded in the shaft cavity of the connector through a compression spring 12, the front end of the horizontal limiting pin 6 is in compression joint with the cam of the rocker arm structure 4, when the push rod 7 pushes the rocker arm to drive the side wing 1 to rotate to a preset unfolding position, the front end of the horizontal limiting pin 6 is just limited at the step of the cam, and the horizontal limiting pin 6 limits the rocker arm structure 4 to rotate inwards to prevent the side wing from folding back after being unfolded.
When the aircraft is launched, the explosion actuator 8 receives a starting signal, the electric combustion explosion tube in the explosion actuator explodes to generate gas pressure, and the piston of the explosion actuator becomes impact force to push the push rod 7 to move forwards. When the push rod 7 moves forward, the push rod 7 is firstly contacted with the limiting hook 11 in the connector, because the contact part of the push rod 7 and the limiting hook 11 is provided with a proper inclined plane 14, the limiting hook 11 can be pressed into the connector 2 when the push rod 7 moves forward continuously, the restraint of the limiting hook 11 on the rocker arm structure 4 is relieved, the rocker arm structure 4 drives the side wing 1 to rotate under the impact of the push rod 7, the rocker arm structure 4 stops rotating under the blocking of the limiting pin after rotating to a preset angle, the side wing is unfolded in place, meanwhile, the horizontal limiting pin 6 moves forward to the concave part of the cam step of the rocker arm structure 4 under the action of the pressing spring 12 to prevent the rocker arm structure 4 from rotating, and the side wing 1 is fixed.
As shown in fig. 4 and 5, when the side wing 1 is unfolded, the inclined plane 14 at the lower part of the front end of the push rod 7 is firstly contacted with the inclined plane of the groove wall at the rear side of the limit hook 11 in the connector 2, when the push rod 7 moves forwards, the limit hook 11 can be pressed into the connector 2, the restriction of the groove wall at the front side of the limit hook 11 on the rocker arm 4 is released, the rocker arm 4 drives the side wing 1 to rotate under the impact of the push rod 7, the rocker arm 4 stops rotating under the blocking of the first vertical limit pin 3 when rotating to a preset unfolding position, the side wing 1 is unfolded in place, meanwhile, the horizontal limit pin 6 moves forwards to the concave position of the cam step of the rocker arm 4 under the action of the compression spring 12 to prevent the rocker arm 4 from rotating, and the side wing 1 is fixed.
When the side wing 1 is folded, firstly, a pull ring at the end part of the horizontal limiting pin 6 is pulled from the inside of the aircraft, the horizontal limiting pin 6 is pulled out from a cam step recess of the rocker arm 4, then the side wing 1 is pushed outside the aircraft to drive the rocker arm 4 to rotate, when the inclined plane at the lower part of the rocker arm 4 rotates to be in contact with the inclined plane of the front side groove wall of the limiting hook 11 in the connector 2, the rocker arm 4 continues to rotate to press the limiting hook 11 into the connector 2, and when the rocker arm 4 rotates to a preset folding position, the rotation is stopped under the blocking of the second vertical limiting pin 10, meanwhile, the limiting hook 11 also rises under the action of the torsion spring 15, the rocker arm 4 is blocked to rotate, and the side wing 1 is fixed.
As shown in fig. 6, the wing is locked in a folded state by a limit hook 11, and the limit hook 11 is mounted in a groove cavity of the connector 2 by a pin and a torsion spring 13 through a screw. The rear end of the limiting hook 11 is provided with a torsion spring 13 to ensure that the front end of the limiting hook 11 protrudes out of the upper surface of the groove cavity of the connector 2. When the side wing 1 is in a folded state, the front side groove wall limiting rocker arm 4 of the limiting hook 11 is fixed; when the side wings 1 are unfolded, the push rod 7 moves forward to press the rear groove wall of the limit hook 11 into the connector 2, and the restraint on the swing arms 4 can be released only by making the front groove wall of the limit hook 11 lower than the lower bottom surface of the swing arms 4, so that the swing arms 4 are ensured to impact the push rod 7 to drive the side wings 1 to rotate.
Claims (7)
1. The utility model provides a folding wing of aircraft, its characterized in that, this folding wing contains two symmetrical flank and a connector, and the front end of two flanks articulates respectively on the connector, and under the wing folding state, the tail end of two flanks is close to, and the tail end of two flanks is kept away from under the wing open state, the front end of two flanks pass through connecting axle and rocking arm structure and connector symmetry connection, rocking arm structure contain rocking arm and cam, the center and the connecting axle of cam are fixed, are equipped with spacing step on the side reason of cam, the rocking arm radially extends with the center of cam.
2. The folding wing of the aircraft according to claim 1, wherein the connector body is a plate-shaped structure, the two side wings are symmetrically hinged to the lower surface of the connector body through pin shafts respectively, the rocker arm structure is positioned on the upper surface of the connector, the connector is provided with a driving mechanism and a limiting mechanism of the side wings, the driving mechanism drives the side wings to open through the rocker arm structure, and the limiting mechanism limits the rotation direction and the rotation angle of the rocker arm structure.
3. The folding wing of the aircraft according to claim 2, wherein the driving mechanism comprises an explosion actuator and a push rod, the explosion actuator drives the rocker arms of the rocker arm structure through the push rod, the explosion actuator and the push rod are positioned on the symmetry axes of the two rocker arms, the push rod is movably embedded in the guide hole of the support, the push rod is provided with a travel slot hole, and a limit rod is arranged in the guide hole of the support and limits the movement travel of the push rod through the travel slot hole.
4. The folding wing of the aircraft according to claim 2, wherein the limiting structure comprises a limiting hook, two horizontal limiting pins and four vertical limiting pins, the limiting hook is embedded on the body of the connector, in the wing folding state, the front ends of the rocker arms of the two side wing rocker arm structures are opposite and closest to each other, and the rocker arm state of the two side wing rocker arm structures is limited by the limiting hook; two horizontal spacer pins and four vertical spacer pins correspond to each other and set up in the vicinity of two rocker arm structures respectively, and every rocker arm structure corresponds a horizontal spacer pin and two vertical spacer pins, and the horizontal spacer pin leads to spacing step restriction rocker arm structure to inboard rotation, prevents that the flank from expanding the back and turning back, and two vertical spacer pins limit the folding and the expansion angle of rocker arm structure respectively through the rocking arm, prevent that the flank from excessively folding and excessively expanding.
5. The folding wing of the aircraft according to claim 4, wherein the limit hook is a cantilever-shaped hook, the rear end of the limit hook is hinged in the groove cavity of the connecting seat through a torsion spring, the front end of the limit hook is a groove-shaped hook, the front groove wall is used for limiting the rocker arm, the side wing is in a folded state, an inclined plane matched with the front end of the push rod is arranged on the rear groove wall, and when the push rod advances, the push rod is pressed on the top end of the rear groove wall through the inclined plane, the limit of the front groove wall to the rocker arm is released, and the rocker arm is pushed to drive the side wing to unfold.
6. The folding wing of the aircraft according to claim 4, wherein the horizontal limiting pin is an elastic limiting pin, the horizontal limiting pin is horizontally embedded in the shaft cavity of the support through a compression spring, the front end of the horizontal limiting pin is in pressure connection with the cam of the rocker arm structure, when the push rod pushes the rocker arm to drive the side wing to rotate to a preset unfolding position, the front end of the horizontal limiting pin is just limited at the step of the cam, and the horizontal limiting pin limits the rocker arm structure to rotate inwards to prevent the side wing from folding back after unfolding.
7. The folding wing of the aircraft according to claim 4, wherein the two vertical limiting pins corresponding to each rocker arm structure are two vertical pin shafts respectively fixed at two sides of the rocker arm, and respectively limit the inward folding angle and the outward unfolding angle of the rocker arm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310434221.9A CN116588318A (en) | 2023-04-21 | 2023-04-21 | Folding wing of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310434221.9A CN116588318A (en) | 2023-04-21 | 2023-04-21 | Folding wing of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116588318A true CN116588318A (en) | 2023-08-15 |
Family
ID=87605298
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310434221.9A Pending CN116588318A (en) | 2023-04-21 | 2023-04-21 | Folding wing of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116588318A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118025520A (en) * | 2024-04-12 | 2024-05-14 | 成都纵横大鹏无人机科技有限公司 | Wing folding mechanism and unmanned aerial vehicle |
-
2023
- 2023-04-21 CN CN202310434221.9A patent/CN116588318A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118025520A (en) * | 2024-04-12 | 2024-05-14 | 成都纵横大鹏无人机科技有限公司 | Wing folding mechanism and unmanned aerial vehicle |
| CN118025520B (en) * | 2024-04-12 | 2024-07-26 | 成都纵横大鹏无人机科技有限公司 | Wing folding mechanism and unmanned aerial vehicle |
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