A wing quick unfolding locking mechanism applied to a swept wing aircraft

Abstract

This application provides a rapid wing deployment and locking mechanism for swept-wing aircraft. The mechanism includes: a base, a slider, a guide mechanism, a linkage mechanism, a rotating mechanism, and a locking mechanism. The guide mechanism, linkage mechanism, rotating mechanism, and locking mechanism are all mounted on the base. The slider is slidably connected to the guide mechanism and connected to the linkage mechanism. The end of the linkage mechanism away from the slider is connected to the rotating mechanism. The wing is fixedly connected to the rotating mechanism. The locking mechanism is located on the side of the rotating mechanism and is used to lock the rotating mechanism. When the slider is impacted by a pyrotechnic device, the slider moves along the guide mechanism, causing the linkage mechanism to swing. The linkage mechanism drives the rotating mechanism to rotate, which in turn causes the wing to deploy. After the wing is fully deployed, the locking mechanism locks into place with the rotating mechanism. This application eliminates the need for wing reassembly, reduces the need for large packaging space, and allows for rapid wing deployment from under the fuselage. Locking the deployed wing ensures stable flight.

Description

Technical Field

[0001] This application relates to the field of aerospace vehicle structure technology, and in particular to a wing quick deployment locking mechanism for swept-wing aircraft. Background Technology

[0002] During flight, the wings provide most of the lift, but they also increase the aircraft's spanwise dimension on both sides. This is particularly problematic for some aircraft containers, where the presence of the wings makes the container size excessively large. Some aircraft are shipped with wing-body separation, with assembly done before flight. However, this method undoubtedly prolongs assembly time. Therefore, reduced container space, difficulty in facilitating flight, and challenges arise in providing sufficient lift to the aircraft from the wings.

[0003] The urgent technical problem to be solved is how to provide a wing quick deployment and locking mechanism for swept-wing aircraft, so as to solve the problems of long assembly time, slow wing deployment speed, poor wing deployment stability, and poor flight stability caused by wing-body separation in the existing technology. Summary of the Invention

[0004] The purpose of this application is to provide a wing quick deployment and locking mechanism for a swept-wing aircraft. The wing is not separated from the aircraft, eliminating the need for wing reassembly, thus reducing assembly time. The wing is retracted before flight, requiring minimal packaging space. Furthermore, a slider, linkage, and rotating mechanism are used to quickly deploy the wing from under the fuselage. The locking mechanism secures the rotating mechanism to lock the deployed wing, ensuring stable flight of the aircraft.

[0005] To achieve the above objectives, this application provides a wing rapid deployment locking mechanism for swept-wing aircraft. The mechanism includes: a base, a slider, a guide mechanism, a linkage mechanism, a rotating mechanism, and a locking mechanism. The guide mechanism, linkage mechanism, rotating mechanism, and locking mechanism are all mounted on the base. The slider is slidably connected to the guide mechanism and connected to the linkage mechanism. The end of the linkage mechanism away from the slider is connected to the rotating mechanism. The wing is fixedly connected to the rotating mechanism. The locking mechanism is located on the side of the rotating mechanism and is used to lock the rotating mechanism. When the slider is impacted by a pyrotechnic device, the slider moves along the guide mechanism, causing the linkage mechanism to swing. The linkage mechanism drives the rotating mechanism to rotate, and the rotating mechanism causes the wing to deploy. After the wing is fully deployed, the locking mechanism locks into the rotating mechanism.

[0006] The wing rapid deployment locking mechanism for swept-wing aircraft described above includes a guide mechanism comprising a guide seat and a guide shaft; the guide seat is fixedly connected to the base; the guide shaft is disposed on the guide seat; the guide shaft passes through the slider, and the slider is slidably connected to the guide shaft.

[0007] The wing rapid deployment locking mechanism for swept-wing aircraft described above includes two guide shafts arranged in parallel, and the slider is slidably connected to the two guide shafts.

[0008] The wing rapid deployment locking mechanism for swept-wing aircraft described above includes a linkage mechanism comprising a linkage, a first pin, and a second pin; one end of the linkage is connected to the slider via the first pin, and the other end is connected to the rotating mechanism via the second pin.

[0009] The wing rapid deployment locking mechanism for swept-wing aircraft described above includes a rotating mechanism comprising: a rotary joint, a rotating bushing, and a fixed rotating shaft; the fixed rotating shaft is fixedly connected to the base; the rotary joint is rotatably connected to the fixed rotating shaft via the rotating bushing; the rotary joint is connected to a linkage mechanism, which drives the rotary joint to rotate around the fixed rotating shaft; and the rotary joint is fixedly connected to the wing.

[0010] The wing rapid deployment locking mechanism for swept-wing aircraft described above includes a locking pin seat, a locking pin, and a spring. The locking pin is disposed within the locking pin seat. The spring is disposed at the end of the locking pin away from the rotating mechanism, and the spring and the locking pin are aligned in the same straight line. The rotary joint has a groove. When the groove of the rotary joint rotates to the position corresponding to the locking pin, the spring force pushes the locking pin into the groove of the rotary joint, restricting the rotation of the rotary joint.

[0011] As described above, in the wing rapid deployment locking mechanism applied to swept-wing aircraft, when the slider moves along the guide shaft, one end of the connecting rod moves in a direction parallel to the guide shaft, and the other end drives the rotary joint to rotate around the fixed rotating shaft. The rotation of the rotary joint drives the wing to deploy.

[0012] The wing rapid deployment locking mechanism for swept-wing aircraft described above includes a first connecting hole and a second connecting hole at each end of the connecting rod; a first mounting hole for the slider; a second mounting hole for the rotary joint; a first pin inserted into the first connecting hole and the first mounting hole to connect the connecting rod and the slider; and a second pin inserted into the second connecting hole and the second mounting hole to connect the connecting rod and the rotary joint.

[0013] As described above, the wing rapid deployment locking mechanism applied to swept-wing aircraft has a set of linkage mechanisms connected to both ends of the slider, and each set of linkage mechanisms is connected to a set of rotating mechanisms; each set of rotating mechanisms is connected to a wing.

[0014] The wing rapid deployment locking mechanism applied to swept-wing aircraft as described above, wherein the wings include two wings, both of which are located on the side of the rotating mechanism away from the base.

[0015] The beneficial effects achieved by this application are as follows: (1) The wings of this application are not separated from the aircraft, so there is no need to reassemble the wings, reducing assembly time. The wings are folded before flight, so there is no need to occupy a large packing space.

[0016] (2) This application uses a slider, a linkage mechanism and a rotating mechanism to quickly deploy the wings from under the fuselage. The rotating mechanism is locked by a locking mechanism to lock the deployed wings and ensure the stability of the aircraft during flight. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this application. For those skilled in the art, other drawings can be obtained based on these drawings.

[0018] Figure 1 This is a schematic diagram of the structure of a wing quick-deployment locking mechanism for a swept-wing aircraft connected to a wing in the wing-undeployed state, according to an embodiment of this application.

[0019] Figure 2 This is a schematic diagram of a wing quick-deployment locking mechanism for a swept-wing aircraft connected to a wing in the wing-deployed state, according to an embodiment of this application.

[0020] Figure 3 This is a schematic diagram of the rotating mechanism according to an embodiment of this application.

[0021] Figure 4This is a schematic diagram of the locking mechanism and rotating mechanism in an embodiment of this application.

[0022] Figure 5 This is a schematic diagram of the structure of a wing quick-deployment locking mechanism for a swept-wing aircraft connected to two wings in the wing-undeployed state according to an embodiment of this application.

[0023] Reference numerals: 1-connecting rod; 2-slider; 3-guide seat; 4-guide shaft; 5-wing; 6-locking pin seat; 7-rotary joint; 8-base; 9-rotary bushing; 10-fixed shaft; 11-spring; 12-locking pin; 13-connecting rod; 14-second mounting hole; 15-groove. Detailed Implementation

[0024] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application.

[0025] like Figure 1-5 As shown, this application provides a rapid deployment and locking mechanism for a swept-wing aircraft. The mechanism includes: a base 8, a slider 2, a guide mechanism, a linkage mechanism, a rotating mechanism, and a locking mechanism. The guide mechanism, linkage mechanism, rotating mechanism, and locking mechanism are all mounted on the base 8. The slider 2 is slidably connected to the guide mechanism and connected to the linkage mechanism. The end of the linkage mechanism away from the slider 2 is connected to the rotating mechanism. The wing 5 is fixedly connected to the rotating mechanism. The locking mechanism is located on the side of the rotating mechanism and is used to lock the rotating mechanism. When the slider 2 is impacted by a pyrotechnic device, the slider 2 moves along the guide mechanism, causing the linkage mechanism to swing. The linkage mechanism drives the rotating mechanism to rotate, and the rotating mechanism causes the wing 5 to deploy. After the wing 5 is deployed, the locking mechanism locks into the rotating mechanism. This application achieves rapid deployment and locking of the wing 5 through the slider 2, linkage mechanism, rotating mechanism, and locking mechanism.

[0026] like Figure 1 As shown, the guiding mechanism includes a guide seat 3 and a guide shaft 4; the guide seat 3 is fixedly connected to the base 8; the guide shaft 4 is set on the guide seat 3; the guide shaft 4 passes through the slider 2, and the slider 2 is slidably connected to the guide shaft 4, so as to realize the stable connection of the slider 2 and the reliable sliding connection with the guide shaft.

[0027] In a preferred embodiment of the present invention, the guide shaft 4 includes two guide shafts 4 arranged in parallel. The slider 2 is slidably connected to the two guide shafts 4. When the slider 2 is impacted by the pyrotechnic device, the slider 2 moves along the two guide shafts 4, thereby improving the smoothness and reliability of the slider 2's movement.

[0028] like Figure 1 and 2 As shown, the linkage mechanism includes: a connecting rod 1, a first pin, and a second pin; one end of the connecting rod 1 is connected to the slider 2 via the first pin, and the other end is connected to the rotating mechanism via the second pin. The connecting rod 1 swings under the drive of the slider 2 without interfering with other components, ensuring reliable movement.

[0029] like Figure 1-4 As shown, the rotating mechanism includes: a rotary joint 7, a rotary bushing 9, and a fixed rotating shaft 10; the fixed rotating shaft 10 is fixedly connected to the base 8; the rotary joint 7 is rotatably connected to the fixed rotating shaft 10 through the rotary bushing 9; the rotary joint 7 is connected to a linkage mechanism, and the linkage mechanism drives the rotary joint 7 to rotate around the fixed rotating shaft 10; the rotary joint 7 is fixedly connected to the wing 5, and the rotation of the rotary joint 7 drives the wing 5 to unfold.

[0030] like Figure 1 , 2 As shown in Figure 4, the locking mechanism includes a locking pin seat 6, a locking pin 12, and a spring 11. The locking pin seat 6 is used to install the locking pin 12 and the spring 11. The locking pin 12 is disposed within the locking pin seat 6; the spring 11 is disposed at the end of the locking pin 12 away from the rotating mechanism, and the spring 11 and the locking pin 12 are arranged in the same straight line direction. The rotary joint 7 has a groove 15. When the groove 15 of the rotary joint 7 rotates to the position corresponding to the locking pin 12, the elastic force of the spring 11 pushes the locking pin 12 into the groove 15 of the rotary joint 7, restricting the rotation of the rotary joint 7. It can be understood that one end of the locking pin 12 is installed in the locking pin seat through the spring 11, and the other end rests on the rotary joint 7. When the rotary joint 7 rotates to the corresponding position, the locking pin 12 is inserted into the groove 15 of the rotary joint 7 under the action of the spring 11, so as to keep the wing 5 stable after it is deployed. The wing 5 rotates around the fixed hinge axis to deploy / retract.

[0031] As a specific embodiment of the present invention, when the slider 2 moves along the guide shaft 4, one end of the connecting rod 1 moves in a direction parallel to the guide shaft 4, and the other end drives the rotary joint 7 to rotate around the fixed rotating shaft 10. The rotation of the rotary joint 7 drives the wing 5 to unfold.

[0032] like Figure 1-4As shown, the two ends of the connecting rod 1 have a first connecting hole and a second connecting hole, respectively; the slider 2 has a first mounting hole; the rotary joint 7 has a second mounting hole 14; the first pin is inserted into the first connecting hole and the first mounting hole to connect the connecting rod 1 and the slider 2; the second pin is inserted into the second connecting hole and the second mounting hole 14 to connect the connecting rod 1 and the rotary joint 7.

[0033] As a specific embodiment of the present invention, the linkage mechanism includes two sets, the rotating mechanism includes two sets, the locking mechanism includes two sets, and the two ends of the slider 2 are respectively connected to a linkage mechanism. Each linkage mechanism is connected to a rotating mechanism. Each rotating mechanism is connected to a wing 5. A locking mechanism is provided on the side of each rotating mechanism. The locking mechanism is used to lock the rotating mechanism on the side.

[0034] like Figure 5 As shown, the wing 5 includes two wings, which are respectively connected to a set of rotating mechanisms. After the slider 2 moves, it drives the two sets of linkage mechanisms to swing synchronously, the two sets of rotating mechanisms to rotate synchronously, and the two wings 5 ​​to unfold synchronously.

[0035] like Figure 1 and 2 As shown, there are two wings 5, both of which are located on the side of the rotating mechanism away from the base 8. This arrangement is simple and reliable, and it is convenient to control the deployment of the wings 5 ​​without causing interference.

[0036] The beneficial effects achieved by this application are as follows: (1) The wings of this application are not separated from the aircraft, so there is no need to reassemble the wings, reducing assembly time. The wings are folded before flight, so there is no need to occupy a large packing space.

[0037] (2) This application uses a slider, a linkage mechanism and a rotating mechanism to quickly deploy the wings from under the fuselage. The rotating mechanism is locked by a locking mechanism to lock the deployed wings and ensure the stability of the aircraft during flight.

[0038] In the description of this application, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the stated features. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0039] In the description of this application, the word "for example" is used to mean "used as an example, illustration, or description." Any embodiment described as "for example" in this application is not necessarily to be construed as being more preferred or advantageous than other embodiments. The following description is provided to enable any person skilled in the art to make and use the invention. Details are set forth in the following description for purposes of explanation. It should be understood that those skilled in the art will recognize that the invention can be made without using these specific details. In other instances, well-known structures and processes will not be described in detail to avoid obscuring the description of the invention with unnecessary detail. Therefore, the invention is not intended to be limited to the embodiments shown, but is consistent with the broadest scope of the principles and features disclosed in this application.

[0040] The above description is merely an embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principle of the present invention should be included within the scope of the claims of the present invention.

Claims

1. A wing rapid deployment locking mechanism for swept-wing aircraft, characterized in that, The mechanism includes: a base, a slider, a guide mechanism, a linkage mechanism, a rotating mechanism, and a locking mechanism; The guiding mechanism, the linkage mechanism, the rotating mechanism, and the locking mechanism are all mounted on the base; The slider is slidably connected to the guide mechanism, and the slider is connected to the linkage mechanism; The end of the linkage mechanism furthest from the slider is connected to the rotating mechanism; The wing is fixedly connected to the rotating mechanism; The locking mechanism is disposed on the side of the rotating mechanism and is used to lock the rotating mechanism. When the slider is impacted by the pyrotechnic device, the slider moves along the guide mechanism and drives the linkage mechanism to swing. The linkage mechanism drives the rotating mechanism to rotate, and the rotating mechanism drives the wing to unfold. After the wing unfolds to its position, the locking mechanism locks into the rotating mechanism.

2. The wing rapid deployment locking mechanism for swept-wing aircraft according to claim 1, characterized in that, The guiding mechanism includes a guide seat and a guide shaft; The guide seat is fixedly connected to the base; The guide shaft is mounted on the guide seat; The guide shaft passes through the slider, and the slider is slidably connected to the guide shaft.

3. The wing rapid deployment locking mechanism for swept-wing aircraft according to claim 2, characterized in that, The guide shaft includes two guide shafts, which are arranged in parallel, and the slider is slidably connected to the two guide shafts.

4. The wing rapid deployment locking mechanism for swept-wing aircraft according to claim 2, characterized in that, The linkage mechanism includes: a connecting rod, a first pin, and a second pin; One end of the connecting rod is connected to the slider via the first pin, and the other end is connected to the rotating mechanism via the second pin.

5. The wing rapid deployment locking mechanism for swept-wing aircraft according to claim 4, characterized in that, The rotating mechanism includes: a rotary joint, a rotary bushing, and a fixed rotating shaft; The fixed rotating shaft is fixedly connected to the base; The rotary joint is rotatably connected to the fixed shaft via the rotary bushing; The rotary joint is connected to the linkage mechanism, and the linkage mechanism drives the rotary joint to rotate around the fixed rotating shaft; The rotary joint is fixedly connected to the wing.

6. The wing rapid deployment locking mechanism for swept-wing aircraft according to claim 5, characterized in that, The locking mechanism includes a locking pin seat, a locking pin, and a spring; The locking pin is disposed within the locking pin seat; The spring is disposed at the end of the locking pin away from the rotating mechanism, and the spring and the locking pin are disposed in the same straight line direction; The rotary joint has a groove. When the groove of the rotary joint rotates to the position corresponding to the locking pin, the elastic force of the spring pushes the locking pin into the groove of the rotary joint, thereby restricting the rotation of the rotary joint.

7. The wing rapid deployment locking mechanism for swept-wing aircraft according to claim 5, characterized in that, When the slider moves along the guide shaft, one end of the connecting rod moves in a direction parallel to the guide shaft, and the other end drives the rotary joint to rotate around the fixed rotating shaft. The rotation of the rotary joint drives the wing to unfold.

8. The wing rapid deployment locking mechanism for swept-wing aircraft according to claim 5, characterized in that, The connecting rod has a first connecting hole and a second connecting hole at its two ends, respectively; The slider has a first mounting hole; the rotary joint has a second mounting hole; The first pin is inserted into the first connecting hole and the first mounting hole to connect the connecting rod and the slider; The second pin is inserted into the second connecting hole and the second mounting hole to connect the connecting rod and the rotary joint.

9. The wing rapid deployment locking mechanism for swept-wing aircraft according to claim 1, characterized in that, The slider is connected to a set of linkage mechanisms at both ends, and each set of linkage mechanisms is connected to a set of rotation mechanisms. Each set of the rotating mechanisms is connected to a wing.

10. The wing rapid deployment locking mechanism for swept-wing aircraft according to claim 9, characterized in that, The aircraft includes two wings, both of which are located on the side of the rotating mechanism away from the base.

Images