A folding wing of an aircraft

Abstract

A folding wing for an aircraft includes two symmetrical side wings and a connector. The front ends of the two side wings are respectively hinged to the connector. In the folded state, the tail ends of the two side wings are close together, and in the open state, the tail ends of the two side wings are far apart. The front ends of the two side wings are symmetrically connected to the connector via a connecting shaft and a rocker arm structure. The rocker arm structure includes a rocker arm and a cam. The center of the cam is fixed to the connecting shaft, and a limiting step is provided on the side edge of the cam. The rocker arm extends radially about the center of the cam.

Description

Technical Field

[0001] This invention is applicable to the field of aircraft design, and in particular to a folding wing structure for an airborne launch vehicle. Background Technology

[0002] Folding wings reduce the lateral dimensions of aircraft and the size of packaging boxes, facilitating storage, transportation, and launch, thus greatly increasing their applicability. Aircraft employing folding technology have their wings folded before launch and can quickly unfold after launch, ensuring stable flight and playing an immeasurable role in improving aircraft maneuverability, combat effectiveness, and wartime survivability.

[0003] The wing folding and unfolding mechanism is used to ensure the smooth folding and unfolding of the wings, and its performance directly affects the speed, stability, and reliability of wing unfolding. During wing unfolding, the unfolding mechanism needs to transfer loads and meet specified motion function requirements. Its ability to quickly unfold and lock the wings is the key to folding wing design, directly affecting whether the aircraft can fly normally and successfully perform its mission. Summary of the Invention

[0004] The purpose of this invention is to provide a folding wing for an aircraft that can be quickly unfolded and locked after the aircraft is launched, enabling the aircraft to fly stably.

[0005] A folding wing for an aircraft, characterized in that the folding wing includes two symmetrical side wings and a connector, the front ends of the two side wings are respectively hinged to the connector, the tail ends of the two side wings are close together in the folded state, and the tail ends of the two side wings are far apart in the open state, the front ends of the two side wings are symmetrically connected to the connector through a connecting shaft and a rocker arm structure, the rocker arm structure includes a rocker arm and a cam, the center of the cam is fixed to the connecting shaft, a limiting step is provided on the side edge of the cam, and the rocker arm extends radially with respect to the center of the cam.

[0006] The folding wing of the aircraft is characterized in that the connector body is a plate-shaped structure, and the two side wings are symmetrically hinged to the lower surface of the connector body by pins. The rocker arm structure is located on the upper surface of the connector. The connector is provided with a drive mechanism and a limiting mechanism for the side wings. The drive mechanism drives the side wings to open through the rocker arm structure, and the limiting mechanism limits the rotation direction and rotation angle of the rocker arm structure.

[0007] The folding wing of the aircraft is characterized in that the drive mechanism includes an explosive actuator and a push rod. The explosive actuator drives the rocker arm of the rocker arm structure through the push rod. The explosive actuator and the push rod are located on the axis of symmetry of the two rocker arms. The push rod is movably embedded in the guide hole of the support. The push rod has a stroke slot. A limiting rod is provided in the guide hole of the support. The limiting rod limits the movement stroke of the push rod through the stroke slot.

[0008] The folding wing of the aircraft is characterized in that the limiting structure includes a limiting hook, two horizontal limiting pins, and four vertical limiting pins. The limiting hook is embedded in the body of the connector. In the folded state, the front ends of the rocker arms of the two side wing rocker arm structures face each other and are closest to each other. The rocker arm states of the two side wing rocker arm structures are limited by the limiting hook. The two horizontal limiting pins and four vertical limiting pins are respectively set near the two rocker arm structures. Each rocker arm structure corresponds to one horizontal limiting pin and two vertical limiting pins. The horizontal limiting pins restrict the rocker arm structure from rotating inward through the limiting step to prevent the side wings from folding back after unfolding. The two vertical limiting pins limit the folding and unfolding angles of the rocker arm structure through the rocker arm to prevent the side wings from being over-folded or over-unfolded.

[0009] The folding wing of the aircraft is characterized in that the limiting hook is a cantilever hook, the rear end of the limiting hook is hinged to the groove of the connecting seat by a torsion spring, the front end of the limiting hook is a groove hook, the front groove wall is used to limit the rocker arm, so that the side wing is in a folded state, and the rear groove wall has an inclined surface that matches the front end of the push rod. When the push rod moves forward, the push rod presses against the top of the rear groove wall through the inclined surface, releasing the limitation of the rocker arm by the front groove wall, thereby pushing the rocker arm to drive the side wing to unfold.

[0010] The folding wing of the aircraft is characterized in that the horizontal limiting pin is an elastic limiting pin, which is horizontally embedded in the shaft cavity of the support by a compression spring. The front end of the horizontal limiting pin is pressed against the cam of the rocker arm structure. When the push rod pushes the rocker arm to rotate the side wing to the predetermined unfolding position, the front end of the horizontal limiting pin is just stopped at the step of the cam. The horizontal limiting pin restricts the rocker arm structure from rotating inward and prevents the side wing from folding back after unfolding.

[0011] The folding wing of the aircraft is characterized in that the two vertical limiting pins corresponding to each rocker arm structure are two vertical pin shafts fixed on both sides of the rocker arm respectively, which limit the inward folding angle and the outward unfolding angle of the rocker arm.

[0012] The advantages of this invention are that the wing folding and unfolding mechanism is simple, enabling rapid unfolding and locking of the wing, and also securing the wing during folding. The entire mechanism boasts high reliability, good manufacturability, and interchangeability. 1) The explosion of the electric combustion tube in the explosive actuator generates an impact force, driving the rocker arm to rotate and achieving rapid wing unfolding, providing timely lift and maintaining flight stability. 2) The combined action of the horizontal and vertical limiting pins locks the folded wing after it has unfolded to a set angle. The structure is simple and reliable, reducing the size of the wing while also reducing the aircraft's weight. 3) The limiting hook constrains the rocker arm, locking the wing after folding and effectively ensuring the aircraft's fixed state after folding. 4) This mechanism is simple, easy to implement, and saves space and weight. It can achieve wing folding, unfolding, and locking functions, is suitable for various types of aircraft, and solves the technical difficulties of achieving wing folding, unfolding, and locking functions under conditions of small space and volume. Attached Figure Description

[0013] Figure 1 Schematic diagram of folded wings

[0014] Figure 2 Schematic diagram of wing deployment

[0015] Figure 3 A schematic diagram of the relationship between the horizontal limit pin and the rocker arm structure in the folded and locked state of the wing (AA view).

[0016] Figure 4 BB view schematic diagram of the relationship between the wing folding and locking drive mechanism and the limit hook.

[0017] Figure 5 BB view schematic diagram of the relationship between the drive mechanism and the limit hook in the wing deployment state.

[0018] Figure 6 Schematic diagram of the limiting hook structure

[0019] The numbers in the diagram are explained as follows: 1. Side wing, 2. Connector, 3. First vertical limit pin, 4. Rocker arm structure, 5. Connecting shaft, 6. Horizontal limit pin, 7. Push rod, 8. Explosion actuator, 9. Limit rod, 10. Second vertical limit pin, 11. Limit hook, 12. Compression spring, 13. Torsion spring, 14. Inclined surface. Detailed Implementation

[0020] See the attached diagram, such as Figure 1 , Figure 2As shown, the folding wing of this application mainly consists of side wings 1, connector 2, rocker arm structure 4, connecting shaft 5, horizontal limiting pin 6, push rod 7, first vertical limiting pin 3, second vertical limiting pin 10, limiting hook 11, and explosive actuator 8. In the folded state, the tail ends of the two side wings 1 are close together; in the open state, the tail ends of the two side wings 1 are far apart. In practice, the side wings 1 are installed outside the aircraft, and the connector 2 is installed inside the aircraft using countersunk bolts. The connector 2 body is a plate-like structure. The two side wings 1 are symmetrically hinged to the lower surface of the connector 2 via connecting shaft 5. The rocker arm structure 4 is located on the upper surface of the connector 2. The connector 2 is equipped with a drive mechanism and a limiting mechanism for the side wings 1. The drive mechanism drives the side wings 1 to open via the rocker arm structure 4, and the limiting mechanism limits the rotation direction and rotation angle of the rocker arm structure 4.

[0021] The rocker arm structure 4 includes a rocker arm and a cam. The center of the cam is fixed to the connecting shaft 5. A limiting step is provided on the side edge of the cam. The rocker arm extends radially from the center of the cam.

[0022] The drive mechanism includes an explosive actuator 8 and a push rod 7. The explosive actuator 8 drives the rocker arm of the rocker arm structure 4 through the push rod 7. The explosive actuator 8 and the push rod 7 are located on the axis of symmetry of the two rocker arms. The push rod 7 is movably embedded in the guide hole of the connector 2. The push rod 7 has a stroke slot. The guide hole of the connector 2 is provided with a limiting rod 9. The limiting rod 9 limits the movement stroke of the push rod 7 through the stroke slot to prevent the push rod 7 from flying out under the impact of the explosive actuator 8.

[0023] The limiting structure includes a limiting hook 11, two horizontal limiting pins 6, two first vertical limiting pins 3, and two second vertical limiting pins 10. The limiting hook 11 is embedded in the body of the connector 2. In the folded state of the wings, the front ends of the rocker arms of the two side wing rocker arm structures 4 face each other and are closest to each other. The rocker arm states of the two side wing rocker arm structures are limited by the limiting hook 11. The two horizontal limiting pins 6 and four vertical limiting pins are respectively set near the two rocker arm structures. Each rocker arm structure 4 corresponds to one horizontal limiting pin 6, one first vertical limiting pin, and one second vertical limiting pin. The horizontal limiting pin 6 restricts the rocker arm structure 4 from rotating inward through the limiting step on the cam to prevent the side wing 1 from unfolding and then folding back. The first vertical limiting pins 3 and the second vertical limiting pins 10 are fixed on both sides of the rocker arm structure 4 and are two vertical pins. The outside of the pins is provided with a rubber sleeve. The rocker arms limit the folding and unfolding angles of the rocker arm structure 4 respectively to prevent the side wing 1 from being over-folded and over-unfolded.

[0024] The limiting hook 11 is a cantilever hook. The limiting hook 11 is screwed into the slot of the connector 2. The rear end of the limiting hook 11 is ensured by the torsion spring 13 that the front end of the limiting hook 11 protrudes from the upper surface of the connector slot. The front end of the limiting hook 11 is a slotted hook. The front slot wall is used to limit the rocker arm, so that the side wing 1 is in a folded state. The rear slot wall has an inclined surface 14 that matches the front end of the push rod 7. When the push rod 7 moves forward, the push rod 7 presses against the top of the rear slot wall through the inclined surface, releasing the limitation of the rocker arm by the front slot wall, thereby pushing the rocker arm structure to drive the side wing 1 to unfold.

[0025] like Figure 3 As shown, 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 presses against the cam of the rocker arm structure 4. When the push rod 7 pushes the rocker arm to rotate the side wing 1 to the predetermined unfolding position, the front end of the horizontal limiting pin 6 is just limited at the step of the cam. The horizontal limiting pin 6 restricts the rocker arm structure 4 from rotating inward and prevents the side wing from folding back after unfolding.

[0026] After the aircraft is launched, the explosion actuator 8 receives a start signal. The electric explosion tube inside the explosion actuator explodes, generating gas pressure. This pressure is converted into an impact force by the piston of the explosion actuator, pushing the push rod 7 forward. When the push rod 7 moves forward, it first contacts the limiting hook 11 in the connector. Because both the push rod 7 and the limiting hook 11 have appropriate bevels 14, as the push rod 7 continues to move forward, it can press the limiting hook 11 into the connector 2, releasing the constraint of the limiting hook 11 on the rocker arm structure 4. Under the impact of the push rod 7, the rocker arm structure 4 drives the side wing 1 to rotate. After the rocker arm structure 4 rotates to a predetermined angle, it stops rotating under the obstruction of the limiting pin, and the side wing is deployed. At the same time, the horizontal limiting pin 6 moves forward under the action of the compression spring 12 to the recess of the cam step of the rocker arm structure 4 to prevent the rocker arm structure 4 from rotating back, thus fixing the side wing 1.

[0027] like Figure 4 , Figure 5 As shown, when the side wing 1 unfolds, the inclined surface 14 at the lower end of the push rod 7 first contacts the inclined surface of the rear groove wall of the limiting hook 11 in the connector 2. When the push rod 7 continues to move forward, it can press the limiting hook 11 into the connector 2, releasing the constraint of the front groove wall of the limiting hook 11 on the rocker arm 4. The rocker arm 4 drives the side wing 1 to rotate under the impact of the push rod 7. When the rocker arm 4 rotates to the predetermined unfolding position, it stops rotating under the obstruction of the first vertical limiting pin 3. The side wing 1 unfolds in place. At the same time, the horizontal limiting pin 6 moves forward to the cam step recess of the rocker arm 4 under the action of the compression spring 12 to prevent the rocker arm 4 from rotating. The side wing 1 is thus fixed.

[0028] When folding the side wing 1, first pull the ring at the end of the horizontal limiting pin 6 from inside the aircraft to pull the horizontal limiting pin 6 out of the recess of the cam step of the rocker arm 4. Then push the side wing 1 from outside the aircraft to rotate the rocker arm 4. When the inclined surface of the lower part of the rocker arm 4 rotates to contact the inclined surface of the front 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. When the rocker arm 4 rotates to the predetermined folding position, it stops rotating under the obstruction of the second vertical limiting pin 10. At the same time, the limiting hook 11 also rises under the action of the torsion spring 15 to prevent the rocker arm 4 from rotating back and fix the side wing 1.

[0029] like Figure 6 As shown, the locking mechanism in the folded state is achieved by a limiting hook 11, which is installed in the slot of connector 2 by screws via a pin and a torsion spring 13. The rear end of the limiting hook 11 is secured by the torsion spring 13, ensuring that the front end of the limiting hook 11 protrudes from the upper surface of the slot of connector 2. When the side wing 1 is folded, the front slot wall of the limiting hook 11 limits and fixes the rocker arm 4; when the side wing 1 is unfolded, the push rod 7 moves forward to press the rear slot wall of the limiting hook 11 into connector 2. The front slot wall of the limiting hook 11 must be lower than the bottom surface of the rocker arm 4 to release the constraint on the rocker arm 4, ensuring that the rocker arm 4 rotates the side wing 1 under the impact of the push rod 7.

Claims

1. A folding wing for an aircraft, characterized in that, The folding wing comprises two symmetrical side wings and a connector. The front ends of the two side wings are hinged to the connector. In the folded state, the rear ends of the two side wings are close together; in the open state, the rear ends of the two side wings are far apart. The front ends of the two side wings are symmetrically connected to the connector via a connecting shaft and a rocker arm structure. The rocker arm structure comprises a rocker arm and a cam. The center of the cam is fixed to the connecting shaft, and a limiting step is provided on the side edge of the cam. The rocker arm extends radially about the center of the cam. The connector is a plate-like structure, and the two side wings are symmetrically hinged to the connector via pins. The lower surface of the connector, the rocker arm structure is located on the upper surface of the connector, the connector is provided with a drive mechanism and a limiting mechanism for the side wings, the drive mechanism drives the side wings to open through the rocker arm structure, the limiting mechanism limits the rotation direction and rotation angle of the rocker arm structure, the drive mechanism includes an explosive actuator and a push rod, the explosive actuator drives the rocker arm of the rocker arm structure through the push rod, the explosive actuator and the push rod are located on the axis of symmetry of the two rocker arms, the push rod is movably embedded in the guide hole of the support, the push rod has a stroke slot hole, the guide hole of the support is provided with a limiting rod, the limiting rod is through The travel slot limits the movement of the push rod. The limiting mechanism includes a limiting hook, two horizontal limiting pins, and four vertical limiting pins. The limiting hook is embedded in the connector body. In the folded wing state, the front ends of the two side wing rocker arm structures face each other and are closest to each other. The rocker arm states of the two side wing rocker arm structures are limited by the limiting hook. The two horizontal limiting pins and four vertical limiting pins are respectively set near the two rocker arm structures. Each rocker arm structure corresponds to one horizontal limiting pin and two vertical limiting pins. The horizontal limiting pins, through the limiting steps, limit the inward rotation of the rocker arm structure. To prevent the side wings from folding back after unfolding, two vertical limiting pins limit the folding and unfolding angles of the rocker arm structure via the rocker arm, preventing the side wings from being over-folded or over-unfolded. The limiting hook is a cantilever hook, with its rear end hinged to the groove of the connecting seat via a torsion spring. The front end of the limiting hook is a groove-shaped hook, with the front groove wall used to limit the rocker arm, keeping the side wings in a folded state. The rear groove wall has an inclined surface that matches the front end of the push rod. When the push rod moves forward, it presses against the top of the rear groove wall through this inclined surface, releasing the limitation of the rocker arm by the front groove wall, thereby pushing the rocker arm to unfold the side wings.

2. The folding wing of the aircraft as described in claim 1, characterized in that, The horizontal limiting pin is an elastic limiting pin. The horizontal limiting pin is horizontally embedded in the shaft cavity of the support by a compression spring. The front end of the horizontal limiting pin presses against the cam of the rocker arm structure. When the push rod pushes the rocker arm to rotate the side wing to the predetermined unfolding position, the front end of the horizontal limiting pin is just stopped at the step of the cam. The horizontal limiting pin restricts the rocker arm structure from rotating inward and prevents the side wing from folding back after unfolding.

3. The folding wing of the aircraft as described in claim 1, characterized in that, Each rocker arm structure has two vertical limiting pins, which are two vertical pin shafts fixed on both sides of the rocker arm respectively, limiting the inward folding angle and the outward unfolding angle of the rocker arm.

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