Aircraft model undercarriage recovery device
By setting up the clamping parts and urge blocks in the aircraft model landing gear recovery device, the problem of tilting and rotating in the landing gear during the taxiing process is solved, and the stable deployment and retraction of the landing gear is achieved to ensure the stable sliding of the aircraft model.
Patent Information
- Application Number
- CN202421527529.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-06-28
- Publication Date
- 2025-07-11
- Estimated Expiration
- 2034-06-28
AI Technical Summary
The existing aircraft model landing gear is not tight enough when deployed and recycled, which leads to the landing gear easily tilting and rotating during the plane of the aircraft model, which has a tendency to recover and affects stability.
An aircraft model landing gear recovery device is designed. By setting a clamping member and a second clamping member in the front and middle recycling grooves, the cooperation of the torsion spring and the urge blocks is used to achieve stable expansion and recovery of the landing gear. The "T"-shaped front-end recycling groove structure and auxiliary block flip mechanism are adopted to ensure the stability of the landing gear.
It improves the expansion and recovery stability of the landing gear, avoids the deformation and recycling trend of the landing gear during taxiing, ensures the stable sliding of the aircraft model, and has a simple, efficient structure, economical and practical.
Smart Images
Figure CN223082256U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the field related to aircraft models, in particular to a retractable landing gear device for aircraft models. Background Art
[0002] Aircraft models are generally divided into two types, dynamic and static: static models are used for collection, display, etc., and cannot fly. They are models that are scaled down in a certain proportion according to the image of an aircraft; while dynamic models can fly and can be controlled by remote control and other means.
[0003] The tightness of the landing gear of existing aircraft models during deployment and retraction is relatively average, and stable positioning cannot be achieved. During the plane taxiing process of the aircraft model, there is a risk that the landing gear tilts and rotates and has a tendency to retract, which is not conducive to the stable use of the landing gear. Content of the Utility Model
[0004] Therefore, in order to solve the above deficiencies, the utility model provides a retractable landing gear device for aircraft models.
[0005] In order to achieve the above purpose, the utility model adopts the following technical solutions: A retractable landing gear device for aircraft models, including a model body, a front-end retraction groove, a retraction plate, an auxiliary block, a clamping member, a landing gear, a force application block, a middle retraction groove, a large retraction plate, a second auxiliary block, a small retraction plate, a second clamping member, a rotating rod, a second landing gear, and a second force application block;
[0006] A front-end retraction groove is provided at the front end of the model body, and a middle retraction groove is provided in the middle thereof;
[0007] The retraction plate is hinged to the model body and is located at the front end of the front-end retraction groove;
[0008] The clamping member is fixed inside the front-end retraction groove, and a landing gear is rotatably connected to the inner side thereof through a torsion spring. A force application block is fixed to the front end of the landing gear;
[0009] The large retraction plate and the small retraction plate are respectively hinged to the model body and are both located at the front end of the middle retraction groove;
[0010] The right end of the second clamping member is fixed to the model body, and a rotating rod is rotatably connected to the left end thereof. The upper end of the second landing gear is fixed to the rotating rod, and a second force application block is fixed to the front end thereof.
[0011] As a further solution of the utility model, the second clamping member includes a support rod, a clamping area, and a clamping plate. The right end of the support rod is fixed to the model body, and a second clamping member is rotatably connected to the left end thereof. A clamping area is provided at the left end of the support rod, and the lower end of the clamping plate is fixed to the second landing gear.
[0012] As a further solution of the utility model, the clamping component includes a support seat and a clamping block. The support seat is fixed inside the front end recovery groove, and the inner side thereof is rotatably connected to the landing gear through a torsion spring. The left end of the clamping block is fixed to the landing gear, and the outer side thereof is clamped to the support seat.
[0013] As a further solution of the utility model, the clamping plate can be clamped with the clamping area after being rotated upward, wherein the rotation intersection of the rotating rod and the support rod is below the center of the support rod, so that when the rotating rod and the second landing gear rotate, the clamping plate rotates about this point, thereby gradually reducing the distance from the clamping area during rotation, and when rotating to obliquely above the clamping area, it is necessary to use a little force to pry the second landing gear so that the clamping plate is clamped into the top of the clamping area to achieve clamping, thereby fixing the deployment of the second landing gear.
[0014] As a further solution of the utility model, an auxiliary block is provided at the upper end of the recovery plate, so that the recovery plate can be turned over by the auxiliary block, thereby unfolding the landing gear placed inside, and the auxiliary block plays a role in facilitating the application of force.
[0015] As a further solution of the utility model, the cross-section of the front recovery groove is "convex" shaped, which is convenient for adapting to the "T" shape after the landing gear is placed, and the size of the front recovery groove is streamlined to control the overall structure of the front recovery groove, making it simple and efficient.
[0016] As a further solution of the utility model, a second auxiliary block is fixed to the upper end of the large recovery plate, so that the large recovery plate can be flipped up by the second auxiliary block to expose the internal middle recovery groove, thereby providing a force point for flipping the small recovery plate.
[0017] As a further solution of the utility model, the placement and deployment of the landing gear is achieved by rotating the landing gear left and right, wherein when the landing gear rotates, the clamping block and the support seat are slightly staggered and clamped, so that when the clamping block is rotated to the left or right, it will be clamped with the support seat so that the landing gear needs to be pried with a little force to be stably deployed or retracted, thereby achieving stability of the landing gear after deployment.
[0018] As a further solution of the utility model, the placement and deployment of the second landing gear is achieved by rotating the second landing gear and the second clamping member up and down, wherein, when the second landing gear rotates, since the center point of its rotation deviates from the center point of the support rod, when the second landing gear rotates, the distance between the second landing gear, the clamping plate and the support rod gradually decreases, which facilitates the clamping of the clamping plate and the clamping area, thereby achieving stability of the second landing gear after deployment.
[0019] Compared with the prior art, the utility model provides an aircraft model landing gear recovery device, which has the following beneficial effects:
[0020] In the present utility model, by arranging a clamping member and a second clamping member inside the front-end recovery groove and the middle recovery groove, the stability after the landing gear and the second landing gear are deployed is enhanced, facilitating the stable sliding of the aircraft model, and avoiding the deformation of the landing gear and the second landing gear during the sliding process, which may generate a recovery tendency and affect the use of the aircraft model. The landing gear has the functions of opening forward and retracting and positioning, and the second landing gear has the functions of opening outward and retracting and positioning. This structure is simple, efficient, economical and practical. BRIEF DESCRIPTION OF THE DRAWINGS
[0021] Figure 1 is a schematic structural view of one side of the form of the present utility model;
[0022] Figure 2 is a schematic structural view of the second side of the form of the present utility model;
[0023] Figure 3 is a schematic structural view of part A of the present utility model;
[0024] Figure 4 is a schematic view of the detailed structure of the clamping block of the present utility model;
[0025] Figure 5 is a schematic structural view of part B of the present utility model;
[0026] Figure 6 is an enlarged schematic view of the detailed structure of the second clamping member of the present utility model;
[0027] Figure 7 is a schematic side view of the second clamping member of the present utility model.
[0028] Wherein: model body - 1, front-end recovery groove - 2, recovery plate - 3, auxiliary block - 4, clamping member - 5, landing gear - 6, force-applying block - 7, middle recovery groove - 8, large recovery plate - 9, second auxiliary block - 10, small recovery plate - 11, second clamping member - 12, rotating rod - 13, second landing gear - 14, second force-applying block - 15, support rod - 121, clamping area - 122, clamping plate - 123, support seat - 51, clamping block - 52. DETAILED DESCRIPTION OF THE EMBODIMENTS
[0029] In order to further explain the technical solution of the present utility model, it will be elaborated in detail below through specific embodiments.
[0030] Please refer to Figures 1-7 In the embodiments of the present utility model:
[0031] A landing gear recovery device for an airplane model comprises a model body 1, a front end recovery slot 2, a recovery plate 3, an auxiliary block 4, a clamping piece 5, a landing gear 6, a force application block 7, a middle recovery slot 8, a large recovery plate 9, a second auxiliary block 10, a small recovery plate 11, a second clamping piece 12, a rotating rod 13, a second landing gear 14, and a second force application block 15; a front end recovery slot 2 is provided at the front end of the model body 1, and a middle recovery slot 8 is provided in the middle thereof; the recovery plate 3 is hinged to the model body 1, and the recovery plate 3 is located at the front end The front end of the recovery groove 2; the clamping member 5 is fixed to the inside of the front end recovery groove 2, and the inner side thereof is rotatably connected to the landing gear 6 through a torsion spring, and a force block 7 is fixed to the front end of the landing gear 6; the large recovery plate 9 and the small recovery plate 11 are respectively hinged to the model body 1, and they are both located at the front end of the middle recovery groove 8; the right end of the second clamping member 12 is fixed to the model body 1, and the left end thereof is rotatably connected to the rotating rod 13, the upper end of the second landing gear 14 is fixed to the rotating rod 13, and a second force block 15 is fixed to the front end thereof.
[0032] In this embodiment, the second clamping member 12 includes a support rod 121, a clamping area 122, and a clamping plate 123. The right end of the support rod 121 is fixed to the model body 1, and the left end thereof is rotatably connected to the second clamping member 13. The left end of the support rod 121 is provided with a clamping area 122, and the lower end of the clamping plate 123 is fixed to the second landing gear 14.
[0033] In this embodiment, the clamping member 5 includes a support seat 51 and a clamping block 52. The support seat 51 is fixed inside the front end recovery slot 2, and its inner side is rotatably connected to the landing gear 6 through a torsion spring. The left end of the clamping block 52 is fixed to the landing gear 6, and its outer side is clamped to the support seat 51.
[0034] In this embodiment, the clamping plate 123 can be clamped with the clamping area 122 after rotating upward, wherein the rotation intersection of the rotating rod 13 and the support rod 121 is below the center of the support rod 121, so that when the rotating rod 13 and the second landing gear 14 rotate, the clamping plate 123 rotates about this point, thereby gradually reducing the distance from the clamping area 122 during rotation, and when rotating to the oblique upper part of the clamping area 122, it is necessary to use a little force to pry the second landing gear 14 so that the clamping plate 123 is clamped into the upper part of the clamping area 122 to achieve clamping, thereby fixing the deployment of the second landing gear 14.
[0035] In this embodiment, an auxiliary block 4 is provided at the upper end of the recovery plate 3, which is convenient for flipping the recovery plate 3 through the auxiliary block 4, so as to unfold the landing gear 6 placed inside. The auxiliary block 4 plays a role in facilitating the application of force. The cross section of the front end recovery groove 2 is "convex", which is convenient for adapting to the "T" shape after the landing gear 6 is placed, so as to achieve the simplified control of the size of the front end recovery groove 2, so that the overall structure is simple and efficient. A second auxiliary block 10 is fixed to the upper end of the large recovery plate 9, which is convenient for flipping the large recovery plate 9 through the second auxiliary block 10 to expose the internal middle recovery groove 8, thereby providing a force point for the flipping of the small recovery plate 11. The placement and deployment of the landing gear are achieved by rotating the landing gear left and right. When the landing gear rotates, the clamping block 52 and The support seat 51 is slightly staggered and clamped, so that when the clamping block 52 rotates to the left or right, the landing gear 6 needs to be pried with a little force due to the clamping with the support seat 51 to be stably deployed or retracted, thereby achieving the stability of the landing gear 6 after deployment. The placement and deployment of the second landing gear 14 are achieved by the up and down rotation of the second landing gear 14 and the second clamping member 12. When the second landing gear 14 rotates, the center point of its rotation deviates from the center point of the support rod 121, so that when the second landing gear 14 rotates, the distance between the second landing gear 14, the clamping plate 123 and the support rod 121 gradually decreases, which facilitates the clamping of the clamping plate 123 and the clamping area 122, thereby achieving the stability of the second landing gear 14 after deployment.
[0036] refer to Figures 1-4 When the landing gear 6 is deployed, the auxiliary block 4 is used to position and apply force, and the recovery plate 3 is turned outward to expose the internal landing gear 6, and the landing gear 6 is turned over with the help of the force-applying block 7. When turning over, the clamping block 52 and the support seat 51 are slightly staggered and clamped, so that when the clamping block 52 is rotated to the left, it is necessary to use a little force to bend the landing gear to deploy it due to the clamping connection with the support seat 51, and the elastic force of the torsion spring is used to stably deploy the landing gear 6, and the landing gear 6 is not easy to rotate due to the slight clamping, so as to achieve the purpose of positioning and stable deployment;
[0037] When the second landing gear 14 is deployed, the second auxiliary block 10 is used to position and apply force, and the large recovery plate 9 is turned over, and then the small recovery plate 11 is turned over to completely expose the second landing gear 14 inside, and then the second force-applying block 15 is used to rotate the second landing gear 14 and the rotating rod 13. Because the rotation intersection of the rotating rod 13 and the supporting rod 121 is below the center of the supporting rod 121, when the rotating rod 13 and the second landing gear 14 are rotated, the clamping plate 123 rotates about this point, so that the distance from the clamping area 122 is gradually reduced during the rotation, and when the second landing gear 14 is rotated to the oblique upper part of the clamping area 122, it is necessary to slightly force the second landing gear 14 to make the clamping plate 123 clamped to the top of the clamping area 122 to achieve clamping, thereby fixing the deployment of the second landing gear 14;
[0038] When it is necessary to retract the landing gear 6 and the second landing gear 14, first reset the landing gear 6 and the second landing gear 14 inside the front retraction groove 2 and the middle retraction groove 8 respectively, and then flip the retraction plate 3, the large retraction plate 9 and the small retraction plate 11 to achieve complete retraction.
[0039] The control mode of the present utility model is controlled by manually starting and closing the switch. The wiring diagram of the power element and the power supply are common knowledge in the art, and the present utility model is mainly used to protect mechanical devices. Therefore, the control mode and wiring layout of the present utility model will not be explained in detail.
[0040] The control mode of the present utility model is automatically controlled by a controller. The control circuit of the controller can be realized by simple programming by those skilled in the art, and the power supply is also common knowledge in the art. Moreover, the present utility model is mainly used to protect mechanical devices. Therefore, the control mode and circuit connection of the present utility model will not be explained in detail.
[0041] The above are only the preferred examples of the present utility model and are not used to limit the present utility model. Although the present utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions recorded in the foregoing embodiments or perform equivalent replacements on some of the technical features. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present utility model shall be included within the protection scope of the present utility model.
Claims
1. An undercarriage retraction device for an aircraft model, comprising a model body (1), a front retraction groove (2), a retraction plate (3), an auxiliary block (4), a clamping member (5), an undercarriage (6), a force application block (7), a middle retraction groove (8), a large retraction plate (9), a second auxiliary block (10), a small retraction plate (11), a second clamping member (12), a rotating rod (13), a second undercarriage (14), and a second force application block (15); A front retraction groove (2) is formed at the front end of the model body (1), and a middle retraction groove (8) is formed in the middle thereof; The retraction plate (3) is hinged to the model body (1), and the retraction plate (3) is located at the front end of the front retraction groove (2); The clamping member (5) is fixed inside the front retraction groove (2), and an undercarriage (6) is rotatably connected to the inner side thereof through a torsion spring. A force application block (7) is fixed to the front end of the undercarriage (6); The large retraction plate (9) and the small retraction plate (11) are respectively hinged to the model body (1), and both are located at the front end of the middle retraction groove (8); The right end of the second clamping member (12) is fixed to the model body (1), and a rotating rod (13) is rotatably connected to the left end thereof. The upper end of the second undercarriage (14) is fixed to the rotating rod (13), and a second force application block (15) is fixed to the front end thereof.
2. The landing gear retraction device for an aircraft model according to claim 1, characterized in that: The second clamping member (12) includes a support rod (121), a clamping area (122), and a clamping plate (123). The right end of the support rod (121) is fixed to the model body (1), and a second clamping member (13) is rotatably connected to the left end thereof. A clamping area (122) is provided at the left end of the support rod (121). The lower end of the clamping plate (123) is fixed to the second undercarriage (14).
3. The landing gear retraction device for an aircraft model according to claim 1, wherein: The clamping member (5) includes a support seat (51) and a clamping block (52). The support seat (51) is fixed inside the front retraction groove (2), and an undercarriage (6) is rotatably connected to the inner side thereof through a torsion spring. The left end of the clamping block (52) is fixed to the undercarriage (6), and the outer side thereof is clamped with the support seat (51).
4. The aircraft model landing gear retraction device according to claim 2, characterized in that: After the clamping plate (123) rotates upward, it can be clamped with the clamping area (122).
5. The landing gear retraction device of an aircraft model according to claim 1, wherein: An auxiliary block (4) is provided at the upper end of the retraction plate (3).
6. The landing gear retraction device of an aircraft model according to claim 1, characterized in that: A second auxiliary block (10) is fixed to the upper end of the large retraction plate (9).
7. The retractable landing gear device for an aircraft model according to claim 1, wherein: The cross-section of the front retraction groove (2) is in a "convex" shape.