Indoor model airplane angle adjusting device
By designing the adhesion mechanism and support arm mechanism on the rear wing of the aircraft model, the problem of inconvenient adjustment of the rear wing of the aircraft model model is solved, and more refined angle adjustment and observation are achieved, which is suitable for small aircraft models.
Patent Information
- Application Number
- CN202421020175.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-05-11
- Publication Date
- 2025-04-25
- Estimated Expiration
- 2034-05-11
AI Technical Summary
The existing aircraft model tail wing lacks effective connectors when adjusting the angle, which leads to inconvenient angle adjustment and makes it difficult to observe the matching degree.
An indoor model aircraft angle adjustment device is designed, and the positioning mechanism is adhered to the surface of the model aircraft tail plate through an adhesion mechanism, the tail angle is adjusted using the hinge shaft of the support arm mechanism, and a more detailed angle adjustment is achieved through the bolted connecting seat and magnetic suction block.
Convenient angle adjustment and observation of the connector-free tail wing is achieved, the difficulty of the small model when adjusting the appropriate angle is improved, and the angle deflection is clarified through the indicator needle and degree scale bar.
Smart Images
Figure CN222788444U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of tail angle adjustment of model airplanes, and more specifically, to an angle adjustment device for indoor model airplanes. Background Art
[0002] Model aircraft usually refers to aviation models, which are small models that simulate real aircraft and are usually made and operated by aviation enthusiasts. There are various types of model aircraft, including airplane models, helicopter models, drone models, etc.
[0003] Some aircraft models have movable tails, which need to be pre-shaped before assembly to test the matching degree of the tail. However, tails without connectors can usually only be glued together, which is not conducive to adjusting the tail angle and observing the matching degree. Utility Model Content
[0004] In order to overcome the above-mentioned defects of the prior art, an embodiment of the utility model provides an indoor model aircraft angle adjustment device, in which a positioning mechanism is positioned on the surface of model aircraft tail wing panel one and model aircraft tail wing panel two through an adhesion mechanism, and the axis centers of the hinge axes of the two support arm mechanisms correspond to the angle deflection points of model aircraft tail wing panel one and model aircraft tail wing panel two, so that the tail wing without a connecting part can be adjusted in angle more conveniently, thereby solving the problems raised in the above-mentioned background technology.
[0005] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: an indoor model aircraft angle adjustment device, comprising a model aircraft tail wing panel one and a model aircraft tail wing panel two, at least one group of positioning mechanisms are installed on the surface of the model aircraft tail wing panel one and the positioning mechanism, and the number of positioning mechanisms in each group is set to two, and the positioning mechanisms are installed on the surface of the model aircraft tail wing panel one and the model aircraft tail wing panel two through an adhesion structure, and a support arm mechanism is installed on one side of the positioning mechanism, and the ends of the two support arm mechanisms are hinged.
[0006] In a preferred embodiment, it further comprises an adhesion mechanism, wherein the adhesion mechanism comprises adhesive or a suction cup, and the adhesion mechanism is installed on the surface of the positioning mechanism.
[0007] In a preferred embodiment, the positioning mechanism includes a positioning piece, a U-shaped slot is formed through the side of the positioning piece close to the support arm mechanism, a slide slot is formed in the middle of the slot, a slider 1 and a slider 2 are inserted into the inner cavity of the slide slot, and the slider 1 and the slider 2 are fixedly connected;
[0008] The width of the slider 1 is larger than the empty slot, and the width of the slider 2 is smaller than the empty slot;
[0009] A spherical clamping block is installed on one side of the sliding block 2, and a group of spherical clamping grooves are respectively opened on both sides of the inner cavity of the sliding groove, and the number of the spherical clamping grooves in each group is set to two. The spherical clamping block is clamped in the inner cavity of the spherical clamping groove, and the interior of the positioning plate is opened with internal thread grooves, and the internal thread grooves are connected with the spherical clamping grooves. The number of the internal thread grooves and the spherical clamping grooves is set to be consistent, and the inner cavity of the internal thread groove is threadedly connected with an external threaded rod for extruding and positioning the spherical clamping block.
[0010] In a preferred embodiment, a bolt connection seat 1 is installed on the side of the slider away from the slide slot, and a bolt connection seat 2 is installed on the side of the positioning plate away from the empty slot. The bolt connection seat 1 and the bolt connection seat 2 are used for threaded connection of the support arm mechanism.
[0011] In a preferred embodiment, the support arm mechanism comprises an outer sleeve, a plurality of inner sleeves are sleeved in sequence inside the outer sleeve, and rubber gaskets for preventing slippage and increasing friction are fixedly installed on the inner wall top, outer wall bottom and inner wall top of the inner sleeve;
[0012] A magnetic block is fixedly installed on the top of the inner sleeve near the center, and a bolt connection head is fixedly installed on the bottom of the outer sleeve, and the bolt connection head is used for threaded connection with the first bolt connection seat or the second bolt connection seat;
[0013] A magnetic head is provided in the middle of the second bolt connection seat, and the magnetic block is used for magnetically attracting the magnetic head of the second bolt connection seat, and the number of the support arm mechanisms is set to at least three.
[0014] In a preferred embodiment, the two support arm mechanisms connected by the two positioning mechanisms are respectively connected to a connecting head and a rotating block, a prefabricated groove is opened in the middle of the connecting head, a central axis is fixedly installed in the middle of the prefabricated groove of the connecting head, a circular hole groove is provided in the middle of the rotating block, the rotating block is sleeved on the surface of the central axis through the circular hole groove, and annular gaskets are fixedly installed on both sides of the circular hole groove of the rotating block.
[0015] In a preferred embodiment, angle indicator disks are fixedly mounted on both sides of the connector, degree scale bars are provided on the surface of the angle indicator disks, and indicator needles are fixedly mounted on the top and bottom of the rotating block.
[0016] Technical effects and advantages of the utility model:
[0017] 1. The positioning mechanism is positioned on the surface of the first and second tail wing panels of the model aircraft through the adhesion mechanism. The axis centers of the hinge shafts of the two support arm mechanisms correspond to the angle deflection points of the first and second tail wing panels of the model aircraft, so that the tail without a connecting part can be adjusted more conveniently and its matching degree can be observed;
[0018] 2. Connect the support arm mechanism through the bolt connection seat 2, and pull the support arm mechanism apart and lengthen it. By lengthening the distance, the tail wing panel 1 or tail wing panel 2 of the model aircraft can be adjusted at a small angle better, which improves the problem that small models are difficult to manually adjust to a suitable angle;
[0019] 3. The indicator needle indicates the degree scale bar on the surface of the angle indicator disk, so that after the two support arm mechanisms are deflected, the operator can observe the deflection angle, which is conducive to the angle adjustment of the tail wing panel 1 and the tail wing panel 2 of the model aircraft. BRIEF DESCRIPTION OF THE DRAWINGS
[0020] Figure 1 It is a schematic diagram of assembling a tail wing without a connector according to the utility model.
[0021] Figure 2 It is a partial structural sectional view of the utility model.
[0022] Figure 3 For this utility model Figure 2 A-section structure enlarged view.
[0023] Figure 4 For this utility model Figure 2 Enlarged view of the structure of part B.
[0024] Figure 5 It is a structural sectional view of the support arm mechanism of the utility model.
[0025] The accompanying drawings are marked as: 1 model aircraft tail wing panel 1, 2 model aircraft tail wing panel 2, 3 positioning mechanism, 31 positioning plate, 32 empty groove, 33 sliding groove, 34 slider 1, 35 slider 2, 36 spherical clamping block, 37 spherical clamping groove, 38 internal threaded tooth groove, 39 external threaded rod, 310 bolt connection seat 1, 311 bolt connection seat 2, 4 support arm mechanism, 41 outer sleeve, 42 bolt connection head, 43 inner sleeve, 44 magnetic suction block, 5 connection head, 6 middle axis, 7 rotating block, 8 washer, 9 angle indicator plate, 10 indicator needle. DETAILED DESCRIPTION
[0026] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.
[0027] Refer to the instruction manual Figure 1-5An indoor model aircraft angle adjustment device according to an embodiment of the utility model comprises a model aircraft tail wing panel 1 and a model aircraft tail wing panel 2. At least one group of positioning mechanisms 3 are installed on the surface of the model aircraft tail wing panel 1 and the positioning mechanism 3. The number of each group of positioning mechanisms 3 is set to two. The positioning mechanisms 3 are installed on the surface of the model aircraft tail wing panel 1 and the model aircraft tail wing panel 2 through an adhesion structure. A support arm mechanism 4 is installed on one side of the positioning mechanism 3. The ends of the two support arm mechanisms 4 are hinged. The adhesion mechanism comprises glue or a suction cup. The adhesion mechanism is installed on the surface of the positioning mechanism 3.
[0028] The positioning mechanism 3 includes a positioning piece 31, and a U-shaped slot 32 is provided on one side of the positioning piece 31 close to the support arm mechanism 4, and a slide slot 33 is provided in the middle of the slot 32. A slider 1 34 and a slider 2 35 are inserted into the inner cavity of the slide slot 33, and the slider 1 34 and the slider 2 35 are fixedly connected; the width of the slider 1 34 is greater than the slot 32 and is used for sliding connection in the inner cavity of the slide slot 33, and the width of the slider 2 35 is less than the slot 32, and when the spherical clamping block 36 is inserted into the right spherical clamping slot 37, it can be deflected and adjusted;
[0029] A spherical clamping block 36 is installed on one side of the slider 2 35, wherein the round head at the end of the spherical clamping block 36 can be a rubber head for positioning and clamping. Figure 2 , 3 As shown, a group of spherical slots 37 are respectively opened on both sides of the inner cavity of the slide groove 33, and the number of each group of spherical slots 37 is set to two. The spherical block 36 is clamped in the inner cavity of the spherical slot 37. The interior of the positioning piece 31 is opened with an internal thread groove 38, and the internal thread groove 38 is connected to the spherical slot 37. The number of the internal thread groove 38 and the spherical slot 37 is set to be consistent. The inner cavity of the internal thread groove 38 is threadedly connected with an external thread rod 39 for squeezing and positioning the spherical block 36, as shown in FIG. Figure 3 As shown in the figure, there are two spherical grooves 37 and two internal thread grooves 38. When the spherical block 36 is inserted into the left spherical groove 37, because the width of the slider 1 34 is greater than the width of the empty groove 32, the slider 1 34 is limited in the inner cavity of the slide groove 33 and cannot be turned over. When the spherical block 36 is inserted into the inner cavity of the spherical groove 37, the width of the slider 2 35 is less than the width of the empty groove 32. At the same time, the spherical block 36 includes a rod body and a spherical structure. Therefore, in this state, the slider 2 35 and the slider 1 34 can rotate around the spherical clamping block 36 as the center, which is the role of fine-tuning, so that the support arm mechanism 4 can be close to or away from the model aircraft tail wing panel 1 and the model aircraft tail wing panel 2, and finally the spherical clamping block 36 is squeezed and positioned by the external threaded rod 39. The side of the slider 1 34 away from the slide groove 33 is installed with a bolt connection seat 1 310, and the side of the positioning plate 31 away from the empty groove 32 is installed with a bolt connection seat 2 311. The bolt connection seat 1 310 and the bolt connection seat 2 311 are used for threaded connection of the support arm mechanism 4.
[0030] The support arm mechanism 4 includes an outer sleeve 41, and a plurality of inner sleeves 43 are sequentially sleeved inside the outer sleeve 41. The inner wall top, the outer wall bottom and the inner wall top of the inner sleeve 43 are fixedly installed with rubber gaskets for preventing slipping and increasing friction. This scheme is used to allow the support arm mechanism 4 to form a telescopic rod state; a magnetic block 44 is fixedly installed on the top of the inner sleeve 43 near the center, and a bolt connecting head 42 is fixedly installed on the bottom of the outer sleeve 41, and the bolt connecting head 42 is used for threaded connection to the bolt connecting seat 1 310 or the bolt connecting seat 2 311; a magnetic head is provided in the middle of the bolt connecting seat 2 311, and the magnetic block 44 is used for magnetically attracting the magnetic head of the bolt connecting seat 2 311. In this scheme, the number of support arm mechanisms 4 is set to at least three, because two of the support arm mechanisms 4 are used to connect Two positioning plates 31, and through the hinge of two support arm mechanisms 4, the model aircraft tail wing panel 1 and the model aircraft tail wing panel 2 can achieve the effect of "suspended" angle adjustment. The other support arm mechanism 4 is used to connect through the bolt connection seat 2 311. The telescopic rod of the support arm mechanism 4 is pulled open and lengthened. By lengthening the distance, the model aircraft tail wing panel 1 or the model aircraft tail wing panel 2 2 can be better adjusted at a small angle. It should be noted that this solution is very useful in small model aircraft, because small models are directly adjusted with tweezers, and it is difficult to adjust to the appropriate angle, either too much or too little. In addition, the magnetic block 44 can also be connected to the magnetic head of the bolt connection seat 2 311 by magnetic attraction. In order to prevent the connection method between the bolt connection head 42 and the bolt connection seat 2 311 from being too cumbersome and not conducive to practical use.
[0031] like Figure 4 As shown, the two support arm mechanisms 4 connected by the two positioning mechanisms 3 are respectively connected with a connecting head 5 and a rotating block 7, a prefabricated groove is provided in the middle of the connecting head 5, a central axis 6 is fixedly installed in the middle of the prefabricated groove of the connecting head 5, a circular hole groove is provided in the middle of the rotating block 7, the rotating block 7 is sleeved on the surface of the central axis 6 through the circular hole groove, and the rotating block 7 is rotatably connected in the prefabricated groove through the central axis 6. Figure 4 It is a structural exploded diagram of the central axis 6 and the rotating block 7. Circular washers 8 are fixedly installed on both sides of the circular hole groove of the rotating block 7. The washers 8 are used to increase the friction with the inner wall of the prefabricated groove, so that after the rotating block 7 is rotated to a certain angle, it is not so easy to change at will, forming a kind of resistance, which is beneficial to the positioning of the model aircraft tail wing panel 1 and the model aircraft tail wing panel 2 after the angle adjustment is completed.
[0032] As a degree indication scheme, angle indicating disks 9 are fixedly installed on both sides of the connecting head 5, and degree scale bars are opened on the surface of the angle indicating disk 9. Indicator needles 10 are fixedly installed on the top and bottom of the rotating block 7. As shown in the support arm mechanism 4, this scheme is used to indicate the degree scale bars on the surface of the angle indicating disk 9 through the indicator needles 10, so that after the two support arm mechanisms 4 are deflected, the operator can observe the deflection angle, which is beneficial to the angle adjustment of the model aircraft tail wing panel 1 and the model aircraft tail wing panel 2.
[0033] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention shall be included in the protection scope of the present invention.
Claims
1. An indoor model aircraft angle adjustment device, comprising a model aircraft tail wing panel 1 (1) and a model aircraft tail wing panel 2 (2), characterized in that: At least one group of positioning mechanisms (3) is installed on the surfaces of the model aircraft tail wing panel one (1) and the positioning mechanism (3), and the number of each group of positioning mechanisms (3) is set to two. The positioning mechanisms (3) are installed on the surfaces of the model aircraft tail wing panel one (1) and the model aircraft tail wing panel two (2) through an adhesive structure, and a support arm mechanism (4) is installed on one side of the positioning mechanism (3), and the ends of the two support arm mechanisms (4) are hinged.
2. The indoor model aircraft angle adjustment device according to claim 1, characterized in that: It also includes an adhesion mechanism, which includes adhesive or a suction cup, and is installed on the surface of the positioning mechanism (3).
3. The indoor model aircraft angle adjustment device according to claim 2, characterized in that: The positioning mechanism (3) comprises a positioning piece (31), a U-shaped slot (32) is provided in a through-shaped manner on one side of the positioning piece (31) close to the supporting arm mechanism (4), a slide slot (33) is provided in the middle of the slot (32), a slide block (34) and a slide block (35) are inserted into the inner cavity of the slide slot (33), and the slide block (34) and the slide block (35) are fixedly connected; The width of the slider 1 (34) is greater than the empty slot (32), and the width of the slider 2 (35) is less than the empty slot (32); A spherical clamping block (36) is installed on one side of the second slide block (35), and a group of spherical clamping grooves (37) are respectively opened on both sides of the inner cavity of the slide groove (33), and the number of each group of spherical clamping grooves (37) is set to two. The spherical clamping block (36) is clamped in the inner cavity of the spherical clamping groove (37), and the interior of the positioning piece (31) is opened with an internal thread groove (38), and the internal thread groove (38) is connected with the spherical clamping groove (37). The number of the internal thread groove (38) and the spherical clamping groove (37) is set to be consistent, and the inner cavity of the internal thread groove (38) is threadedly connected with an external thread rod (39) for squeezing and positioning the spherical clamping block (36).
4. The indoor model aircraft angle adjustment device according to claim 3, characterized in that: A bolt connection seat 1 (310) is installed on the side of the slide block 1 (34) away from the slide groove (33), and a bolt connection seat 2 (311) is installed on the side of the positioning plate (31) away from the empty groove (32). The bolt connection seat 1 (310) and the bolt connection seat 2 (311) are used for threaded connection of the support arm mechanism (4).
5. The indoor model aircraft angle adjustment device according to claim 4, characterized in that: The support arm mechanism (4) comprises an outer sleeve (41), a plurality of inner sleeves (43) are sequentially sleeved inside the outer sleeve (41), and rubber gaskets for preventing slippage and increasing friction are fixedly mounted on the inner wall top, outer wall bottom and inner wall top of the inner sleeve (43); A magnetic block (44) is fixedly installed on the top of the inner sleeve (43) near the center, and a bolt connection head (42) is fixedly installed on the bottom of the outer sleeve (41), and the bolt connection head (42) is used for threaded connection with a bolt connection seat 1 (310) or a bolt connection seat 2 (311); A magnetic head is provided in the middle of the second bolt connection seat (311), and the magnetic block (44) is used to magnetically attract the magnetic head of the second bolt connection seat (311), and the number of the support arm mechanisms (4) is set to at least three.
6. The indoor model aircraft angle adjustment device according to claim 5, characterized in that: The two support arm mechanisms (4) connected by the two positioning mechanisms (3) are respectively connected to a connecting head (5) and a rotating block (7); a prefabricated groove is provided in the middle of the connecting head (5); a central shaft (6) is fixedly installed in the middle of the prefabricated groove of the connecting head (5); a circular hole groove is provided in the middle of the rotating block (7); the rotating block (7) is sleeved on the surface of the central shaft (6) through the circular hole groove; and annular washers (8) are fixedly installed on both sides of the circular hole groove of the rotating block (7).
7. The indoor model aircraft angle adjustment device according to claim 6, characterized in that: Angle indicator disks (9) are fixedly mounted on both sides of the connector (5), and a degree scale bar is provided on the surface of the angle indicator disk (9). Indicator needles (10) are fixedly mounted on the top and bottom of the rotating block (7).