Model airplane track ejection device

Abstract

The utility model discloses a model airplane track ejection device which comprises a guide rail sectional material, a guide rail is installed on the surface of the guide rail sectional material, a guide block is connected into the guide rail in a sliding mode, a carrier base is welded to the top face of the guide block, a first installation ring is fixedly connected to the surface of the carrier base, and a second installation ring is welded to the side face of the guide rail sectional material. An elastic rope is tied between the second mounting ring and the first mounting ring, an extension spring is fixedly mounted on the inner wall of the guide rail, the other end of the extension spring is fixedly connected with the surface of one side of a guide block, and a traction rope is tied on the surface of the other side of the guide block. According to the model airplane ejection device, the elastic rope and the extension spring are arranged as two elastic elements, the elastic rope and the extension spring are used in cooperation, the dual-force-storage ejection effect can be achieved, the model airplane ejection speed is higher, the model airplane ejection distance is longer, when the elastic rope is tired, the elastic rope can be unfastened to be replaced, the maintenance difficulty is lower, practicability is high, and the model airplane ejection device is worthy of popularization.

Description

Technical Field

[0001] The utility model relates to the technical field of model airplanes, in particular to a model airplane track ejection device. Background Art

[0002] At present, unpowered model aircraft, as a mold that imitates aircraft, are manually thrown during takeoff. The wings of unpowered model aircraft are in a fixed unfolded state, and the air resistance is large when thrown, resulting in a limited throwing distance and a short gliding time in the air. At the same time, it requires high skills, which seriously affects the fun of model aircraft flying.

[0003] The existing technology has the following problems:

[0004] After extensive searching, it was found that the patent document with application number CN202121793874.9 disclosed a track-ejection model aircraft. The patent uses a single elastic element to eject the model aircraft. The ejection speed of the model aircraft is not fast enough, the distance is not far enough, and it is inconvenient to replace the fatigued elastic element after multiple uses.

[0005] To this end, we proposed a model aircraft track ejection device to solve the above-mentioned drawbacks. Utility Model Content

[0006] The purpose of the utility model is to provide a model aircraft track ejection device in order to solve the shortcomings in the prior art.

[0007] In order to achieve the above-mentioned purpose, the present invention adopts the following technical solutions: a model aircraft track ejection device, comprising a guide rail profile, a guide rail is installed on the surface of the guide rail profile, and a guide block is slidably connected inside the guide rail, a carrier seat is welded on the top surface of the guide block, and a first mounting ring is fixedly connected to the surface of the carrier seat, a second mounting ring is welded on the side of the guide rail profile, and an elastic rope is tied between the second mounting ring and the first mounting ring, a tension spring is fixedly installed on the inner wall of the guide rail, and the other end of the tension spring is fixedly connected to one side surface of the guide block, and a traction rope is tied to the other side surface of the guide block, one end of the inner part of the guide rail is rotatably connected to a winding roller, and a handle is installed at one end of the winding roller, and the other end of the traction rope is fixed on the winding roller, a locking hole is opened on the surface of the guide rail profile, an installation cavity is opened on the bottom surface of the carrier seat, and a limit spring is fixedly installed on the inner top surface of the installation cavity, a slider is installed on the other end of the limit spring, and a locking rod is fixedly installed on the bottom surface of the slider, and the locking rod is plugged into the locking hole.

[0008] Preferably, there are multiple elastic ropes, and the elastic ropes are distributed in pairs on both sides of the aircraft carrier.

[0009] Preferably, the winding roller is I-shaped.

[0010] Preferably, there are two locking holes, and the two locking holes are symmetrically distributed on the surface of the guide rail profile, and the depth of the two locking holes is the same as the thickness of the guide rail profile.

[0011] Preferably, the length of the locking rod is greater than the depth of the locking hole.

[0012] Preferably, the diameter of the tension spring is smaller than the width of the guide rail.

[0013] Compared with the prior art, the beneficial effects of the present invention are:

[0014] 1. In the utility model, an elastic rope and a tension spring are provided as two elastic elements. The elastic rope and the tension spring are used together to play the role of double-force storage ejection. The model aircraft ejection speed is faster and the distance is farther. When the elastic rope is fatigued, the elastic rope can be untied and replaced, which makes maintenance easier, has strong practicality, and is worthy of promotion. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0016] Figure 1 This is a structural diagram of a model aircraft track ejection device proposed by the utility model;

[0017] Figure 2 It is a structural diagram of the carrier base, guide block, mounting cavity, limit spring, slider and locking rod;

[0018] Figure 3 for Figure 1 Bottom view of .

[0019] Legend:

[0020] 1. Guide rail profile; 2. Guide rail; 3. Guide block; 4. Carrier base; 5. First mounting ring; 6. Elastic rope; 7. Second mounting ring; 8. Tension spring; 9. Traction rope; 10. Winding roller; 11. Handle; 12. Locking hole; 13. Mounting cavity; 14. Limit spring; 15. Slider; 16. Locking rod. DETAILED DESCRIPTION

[0021] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0022] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the devices or components referred to must have a specific direction, be constructed and operated in a specific direction, and therefore should not be understood as limiting the present invention; the terms "first", "second", and "third" are only used for descriptive purposes and should not be understood as indicating or implying relative importance; in addition, unless otherwise expressly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or it can be internal communication between two components. For those skilled in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0023] Please refer to Figure 1-3 A model aircraft track ejection device includes a guide rail profile 1, a guide rail 2 is installed on the surface of the guide rail profile 1, and a guide block 3 is slidably connected to the inside of the guide rail 2, a carrier seat 4 is welded to the top surface of the guide block 3, and a first mounting ring 5 is fixed to the surface of the carrier seat 4, a second mounting ring 7 is welded to the side of the guide rail profile 1, and an elastic rope 6 is tied between the second mounting ring 7 and the first mounting ring 5, a tension spring 8 is fixedly installed on the inner wall of the guide rail 2, and the other end of the tension spring 8 is fixed to one side surface of the guide block 3, and the other side of the guide block 3 A traction rope 9 is fastened to the surface, and a winding roller 10 is rotatably connected to one end of the inner part of the guide rail 2, and a handle 11 is installed at one end of the winding roller 10. The other end of the traction rope 9 is fixed on the winding roller 10. A locking hole 12 is provided on the surface of the guide rail profile 1, and an installation cavity 13 is provided on the bottom surface of the carrier seat 4, and a limit spring 14 is fixedly installed on the inner top surface of the installation cavity 13. A slider 15 is installed at the other end of the limit spring 14, and a locking rod 16 is fixedly installed on the bottom surface of the slider 15, and the locking rod 16 is plugged into the locking hole 12.

[0024] When in use, by setting the elastic rope 6 and the tension spring 8 as two elastic elements, the elastic rope 6 and the tension spring 8 can be used together to play the role of double-force ejection, the aircraft model ejection speed is faster and the distance is farther, and when the elastic rope 6 is fatigued, the elastic rope 6 can be untied and replaced, the maintenance difficulty is lower, the practicality is strong, and it is worthy of promotion, wherein the winding roller 10 is driven to rotate by turning the handle 11, and the traction rope 9 is wound on the winding roller 10, at this time the carrier seat 4 is pulled to move to the right (attached Figure 1 As shown in the direction, the elastic rope 6 and the tension spring 8 are stretched and deformed to store energy. During the movement, the locking rod 16 cannot be ejected from the installation cavity 13 under the action of the guide rail profile 1. When the locking rod 16 on the carrier seat 4 moves to the position of the locking hole 12, the limit spring 14 pushes the locking rod 16 out and inserts it into the locking hole 12 to complete the fixation of the carrier seat 4, waiting for the ejection of the model aircraft. When ejecting, the locking rod 16 only needs to be moved out of the locking hole 12 to eject the model aircraft.

[0025] In this embodiment, a plurality of elastic cords 6 are provided, and the plurality of elastic cords 6 are distributed in pairs on both sides of the aircraft carrier 4 .

[0026] Specifically, the arrangement of multiple elastic ropes 6 has a better power storage effect, and the model aircraft can be launched farther.

[0027] In this embodiment, the winding roller 10 is I-shaped.

[0028] Specifically, the traction rope 9 can be wound onto the winding roller 10 to prevent it from being separated.

[0029] In this embodiment, two locking holes 12 are provided, and the two locking holes 12 are symmetrically distributed on the surface of the guide rail profile 1 , and the depth of the two locking holes 12 is the same as the thickness of the guide rail profile 1 .

[0030] Specifically, the locking effect of the aircraft carrier 4 after power storage is better and the stability is stronger.

[0031] In this embodiment, the length of the locking rod 16 is greater than the depth of the locking hole 12 .

[0032] Specifically, the locking rod 16 inserted into the locking hole 12 can be exposed from the locking hole 12 to facilitate firing.

[0033] In this embodiment, the diameter of the tension spring 8 is smaller than the width of the guide rail 2 .

[0034] Specifically, the tension spring 8 can be installed inside the guide rail 2 .

[0035] Working principle: When in use, by setting the elastic rope 6 and the tension spring 8 as two elastic elements, the elastic rope 6 and the tension spring 8 can be used together to play the role of double-force ejection, the aircraft model ejection speed is faster and the distance is farther, and when the elastic rope 6 is fatigued, the elastic rope 6 can be untied and replaced, the maintenance difficulty is lower, the practicality is strong, and it is worthy of promotion. The winding roller 10 is driven to rotate by turning the handle 11, and the traction rope 9 is wound on the winding roller 10. At this time, the carrier seat 4 is pulled to move to the right (attached Figure 1 As shown in the direction, the elastic rope 6 and the tension spring 8 are stretched and deformed to store energy. During the movement, the locking rod 16 cannot be ejected from the installation cavity 13 under the action of the guide rail profile 1. When the locking rod 16 on the carrier seat 4 moves to the position of the locking hole 12, the limit spring 14 pushes the locking rod 16 out and inserts it into the locking hole 12 to complete the fixation of the carrier seat 4, waiting for the ejection of the model aircraft. When ejecting, the locking rod 16 only needs to be moved out of the locking hole 12 to eject the model aircraft.

[0036] The above is only a preferred specific implementation method of the present invention, but the protection scope of the present invention is not limited to this. Any technician familiar with the technical field within the technical scope disclosed by the present invention can make equivalent replacements or changes based on the technical solution and utility model concept of the present invention, which should be covered by the protection scope of the present invention.

Claims

1. A model aircraft track ejection device, comprising a guide rail profile (1), characterized in that: A guide rail (2) is mounted on the surface of the guide rail profile (1), and a guide block (3) is slidably connected to the inside of the guide rail (2), a carrier seat (4) is welded to the top surface of the guide block (3), and a first mounting ring (5) is fixedly connected to the surface of the carrier seat (4), a second mounting ring (7) is welded to the side of the guide rail profile (1), and an elastic rope (6) is tied between the second mounting ring (7) and the first mounting ring (5), a tension spring (8) is fixedly mounted on the inner wall of the guide rail (2), and the other end of the tension spring (8) is fixedly connected to one side surface of the guide block (3), and a traction rope (9) is tied to the other side surface of the guide block (3). One end of the interior of the guide rail (2) is rotatably connected to a winding roller (10), and a handle (11) is installed at one end of the winding roller (10). The other end of the traction rope (9) is fixed on the winding roller (10). A locking hole (12) is provided on the surface of the guide rail profile (1). A mounting cavity (13) is provided on the bottom surface of the carrier seat (4), and a limit spring (14) is fixedly installed on the inner top surface of the mounting cavity (13). A slider (15) is installed at the other end of the limit spring (14), and a locking rod (16) is fixedly installed on the bottom surface of the slider (15), and the locking rod (16) is plugged into the locking hole (12).

2. The aircraft model track ejection device according to claim 1, characterized in that: A plurality of elastic ropes (6) are provided, and the plurality of elastic ropes (6) are distributed in pairs on both sides of the carrier seat (4).

3. The model aircraft track ejection device according to claim 1, characterized in that: The winding roller (10) is in an I-shape.

4. The model aircraft track ejection device according to claim 1, characterized in that: There are two locking holes (12), and the two locking holes (12) are symmetrically distributed on the surface of the guide rail profile (1), and the depth of the two locking holes (12) is the same as the thickness of the guide rail profile (1).

5. The aircraft model track ejection device according to claim 1, characterized in that: The length of the locking rod (16) is greater than the depth of the locking hole (12).

6. The aircraft model track ejection device according to claim 1, characterized in that: The diameter of the tension spring (8) is smaller than the width of the guide rail (2).

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