A launch device for an aircraft

Abstract

The utility model provides a kind of launching device of aircraft, including launching barrel and with the launching control component being connected to the launching barrel, the launching barrel one end is exit, the launching barrel is provided with the launching channel leading to the exit, the aircraft is arranged in the launching channel, the launching control component can send the aircraft from the exit.The utility model is by being provided with the launching barrel, and the launching channel is arranged in the launching barrel, the aircraft is arranged in the launching channel, is sent from the launching channel, can make the volume of launching device more compact, can reduce the appearance size of launching device, help to improve its arrangement flexibility, the reuse of the launching device can also be realized, the size of the launching barrel can be designed according to the size requirement of the aircraft, can maximize meet the requirement of lightweight and portable of the launching device, to greatly improve the economy of the launching device.

Description

Technical Field

[0001] This utility model relates to the field of flight equipment technology, specifically to a launch device for an aircraft. Background Technology

[0002] Launch technology for various types of aircraft, such as drones and small carriers, is one of the core supporting technologies in civil aviation, low-altitude economy, and emergency rescue. Its development level determines the deployment efficiency, operational response speed, and application economy of various small aircraft.

[0003] Currently, mainstream small aircraft launchers mainly include fixed catapults, vehicle-mounted mobile launch platforms, and disposable booster launchers. These devices have met the basic launch requirements of small aircraft in specific application scenarios and promoted the initial development of low-altitude operation technology. However, in long-term practice, their technical limitations have gradually been exposed. Among them, the problems of poor economic efficiency caused by the large size of the launcher, structural redundancy, and non-reusability are the most prominent. They are still far from the core development concept of "lightweight, portable, and low-cost" small aircraft, which restricts the large-scale development of the low-altitude economy and the in-depth application of small aircraft in professional fields. There is an urgent need to develop a compact, portable, and reusable small aircraft launcher. Utility Model Content

[0004] In view of this, the purpose of this utility model is to provide a launch device for an aircraft, which solves the problems of poor economy caused by the large size, redundant structure and non-reusability of existing launch devices.

[0005] To solve the above-mentioned technical problems, the technical solution used in this utility model is as follows:

[0006] The present invention discloses a launching device for an aircraft, the aircraft including a main body and winglets connected to the main body, the launching device including a launching tube and a launching control assembly connected to the launching tube, one end of the launching tube being an exit port, the launching tube being provided with a launching channel leading to the exit port, the aircraft being disposed in the launching channel, and the launching control assembly being able to launch the aircraft from the exit port;

[0007] The launch channel includes a main channel and a side channel connected to the main channel. The main body is housed in the main channel, and the winglets are housed in the corresponding side channels. The main body is launched through the main channel, and the winglets are launched through the side channels.

[0008] Preferably, the launch control assembly includes a launch base connected to the launch tube, and the launch base is provided with control buttons.

[0009] More preferably, the launch tube is provided with a first space, and the launch base is connected to the launch tube through a first connecting component. The launch base can be folded and stored in the first space in a stored state through the first connecting component, or it can be unfolded and extended out of the first space in a launch state.

[0010] More preferably, the wing extends radially from the main body in a direction away from the main body, and the launch tube is provided with a first recessed space that is recessed in the direction opposite to the extension direction of the wing, and the first space is located in the first recessed space.

[0011] More preferably, the launching device further includes an aiming assembly fixed to the launching tube.

[0012] More preferably, the launch tube is provided with a second space, and the aiming component is connected to the launch tube through a second connecting component. The aiming component can be folded and stored in the second space through the second connecting component and is in a stored state, or it can be unfolded through the second connecting component and extended out of the second space and is in a launching state.

[0013] More preferably, the launch tube is provided with a second recessed space that is recessed away from the extension direction of the wing, and the second space is located in the second recessed space.

[0014] More preferably, the aiming assembly includes a sight and a support assembly, wherein the sight is connected to the launch tube via the support assembly.

[0015] More preferably, the support assembly includes a connector, a first support, and a second support, the first support and the second support being connected to the launch tube respectively, and the two ends of the connector being connected to the first support and the second support respectively.

[0016] More preferably, the launching device further includes a protective component fixed to the launching tube, the protective component being used to form a protective curtain when launching the aircraft.

[0017] More preferably, the protective component includes a foldable curtain and a support frame, the curtain being connected to the launch tube via the support frame.

[0018] More preferably, the launch tube is provided with a third space, and the support frame is connected to the launch tube through a third connecting component. The support frame can be folded and stored in the third space through the third connecting component to be in a stored state, or it can be unfolded and extended out of the third space to be in a protected state.

[0019] More preferably, the launch tube is provided with a third recessed space that is recessed away from the extension direction of the wing, and the third space is located in the third recessed space;

[0020] And / or, the supporting frame includes a main frame and a sub-frame, the two sides of the curtain are respectively connected to the main frame and the sub-frame, the first end of the main frame is connected to the launch tube, one end of the sub-frame is rotatably connected to the first end of the main frame, and the second end of the main frame extends in a radiating manner away from the launch tube;

[0021] And / or, when the support frame is in the protected state, the curtain is located at the end of the launching tube near the emission port, and the curtain can be deployed around the emission port through the support frame.

[0022] More preferably, the launching device further includes a protective cover, the protective cover being provided with a receiving cavity, in which the launching tube can be housed.

[0023] Compared with the prior art, the advantages of the aircraft launching device described in this utility model are mainly reflected in:

[0024] This utility model provides a launching device for launching an aircraft. By setting up a launching tube and a launching channel within the launching tube, and placing the aircraft in the launching channel for launch, the launching device can be made more compact. This not only reduces the overall size of the launching device and improves its layout flexibility, but also enables the reuse of the launching device. Furthermore, the size of the launching tube can be designed according to the size requirements of the aircraft, maximizing the requirements for lightweight and portability of the launching device, thereby significantly improving its economic efficiency. Attached Figure Description

[0025] The above and other objects, features, and advantages of this invention will become clearer through a more detailed description of the preferred embodiments shown in the accompanying drawings. The same reference numerals indicate the same parts throughout the drawings, and the drawings are not intentionally drawn to scale with actual dimensions; the focus is on illustrating the gist of this invention.

[0026] Figure 1 A three-dimensional structural diagram of a launch device for an aircraft provided in an embodiment of this utility model. Figure 1 ;

[0027] Figure 2 A three-dimensional structural diagram of a launch device for an aircraft provided in an embodiment of this utility model. Figure 2 ;

[0028] Figure 3 for Figure 2 View A in the middle;

[0029] Figure 4 A three-dimensional structural diagram of a launch device for an aircraft stored in the protective cover, as provided in an embodiment of this utility model;

[0030] Figure label:

[0031] Launch tube 100, launch port 110, launch channel 120, main channel 121, side channel 122;

[0032] Aircraft 200;

[0033] Launch control assembly 300, launch base 310, control button 320;

[0034] Aiming component 400, connector 410, first support 420, second support component 430;

[0035] Protective component 500, main frame 510, secondary frame 520, first secondary frame 521, second secondary frame 522, arc segment 5221, straight segment 5222;

[0036] First connecting component 1, second connecting component 2, first recessed space 3, second recessed space 4, third recessed space 5, protective cover 6, third connecting component 7. Detailed Implementation

[0037] The technical solution of this utility model will be further described in detail below with reference to the accompanying drawings and specific embodiments, so that those skilled in the art can better understand this utility model and implement it. However, the embodiments are not intended to limit this utility model. In this embodiment, it should be understood that the terms "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting this utility model.

[0038] It should be noted that when one element is considered to be "connected" to another element, it can be directly connected to and integrated with the other element, or there may be an intervening element present. The terms "mounted," "one end," "the other end," and similar expressions used in this invention are for illustrative purposes only.

[0039] This embodiment provides a launching device for an aircraft, such as... Figures 1 to 4As shown, it includes a launch tube 100 and a launch control assembly 300 connected to the launch tube 100. One end of the launch tube 100 is a launch port 110. The launch tube 100 is provided with a launch channel 120 leading to the launch port 110. The aircraft 200 is disposed in the launch channel 120. The launch control assembly 300 can launch the aircraft 200 from the launch port 110. The aircraft 200 includes a main body and winglets connected to the main body.

[0040] This utility model provides a launching device for launching an aircraft 200. By setting a launching tube 100 and a launching channel 120 in the launching tube 100, the aircraft 200 is placed in the launching channel 120 and can be launched from the launching channel 120. This makes the launching device more compact, which not only reduces the size of the launching device and helps to improve its layout flexibility, but also enables the reuse of the launching device. In addition, the size of the launching tube 100 can be designed according to the size requirements of the aircraft 200, which can maximize the requirements of lightweight and portability of the launching device, thereby greatly improving the economy of the launching device.

[0041] In a preferred embodiment, the launch channel 120 includes a main channel 121 and a side channel 122 communicating with the main channel 121. The main body is housed in the main channel 121, and the winglets are housed in the corresponding side channels 122. The main body is launched through the main channel 121, and the winglets are launched through the side channels 122. In this embodiment, the main channel 121 is columnar, and the side channels 122 extend radially along the main channel 121 in a radiating manner.

[0042] In a preferred embodiment, the launch control assembly 300 includes a launch base 310 connected to the launch tube 100, and a control button 320 is provided on the launch base 310. Pressing the control button 320 controls the aircraft 200 to start launching.

[0043] Furthermore, the launch tube 100 is provided with a first space, and the launch base 310 is connected to the launch tube 100 via a first connecting component 1. The launch base 310 can be folded and stored in the first space in a stored state via the first connecting component 1, or it can be unfolded and extended out of the first space in a launching state, thereby reducing the overall size and volume of the launching device in the stored state. The first connecting component 1 can be any connecting structure that enables the foldable movement of the launch base 310, including hinged connections. This is a readily achievable action effect in the prior art, and will not be listed here.

[0044] Furthermore, the wing extends radially from the main body in a direction away from the main body, and the launch tube 100 is provided with a first recessed space 3 that is recessed in the direction of extension of the wing, and the first space is located in the first recessed space 3.

[0045] In another preferred embodiment, the launching device further includes an aiming component 400, which is fixed to the launching tube 100 and is used to assist in aiming at the target object of the aircraft 200.

[0046] In a preferred embodiment, the launch tube 100 is provided with a second space. The aiming component 400 is connected to the launch tube 100 via a second connecting component 2. The aiming component 400 can be folded and stored in the second space in a stored state via the second connecting component 2, or it can be unfolded and extended out of the second space in a launching state, thereby reducing the overall size and volume of the launching device in the stored state. The second connecting component 2 can be various connection structures, including those enabling hinged connections; this is a readily achievable action effect in the prior art, and its specific structure will not be detailed here. Preferably, the aiming component 400 includes a sight (not shown in the figure) and a support component, with the sight connected to the launch tube 100 via the support component.

[0047] The support assembly includes a connector 410, a first support 420, and a second support 430. The first support 420 and the second support 430 are rotatably connected to the launch tube 100, and both ends of the connector 410 are rotatably connected to the first support 420 and the second support 430, respectively. The aiming device can be fixed on the connector 410.

[0048] In a further preferred embodiment, the launch tube 100 is provided with a second recessed space 4 that is recessed away from the extension direction of the wing, and the second space is located in the second recessed space 4.

[0049] In another preferred embodiment, the launching device further includes a protective component 500, which is fixed to the launching tube 100. The protective component 500 is used to form a protective curtain when launching the aircraft 200 to protect the launch operator from foreign objects such as flares and falling objects.

[0050] In a further preferred embodiment, the protective component 500 includes a foldable curtain (not shown) and a supporting frame. The curtain is connected to the launch tube 100 via the supporting frame, and the foldable curtain can be folded and unfolded via the supporting frame. The curtain is foldable and unfolds and / or folds via the supporting frame. Preferably, the curtain is made of a transparent material so that it does not obstruct the operator's view when unfolded. In this embodiment, the curtain, via the supporting frame, can form a partition curtain around the launch port 110, separating the area in front of and behind the launch end of the launch tube 100, thus protecting the operator in the launch area behind the launch end of the launch tube 100.

[0051] In a further preferred embodiment, the launch tube 100 is provided with a third space, and the support frame is connected to the launch tube 100 through the third connecting component 7. The support frame can be folded and stored in the third space through the third connecting component 7 and is in a stored state, or it can be extended out of the third space through the third connecting component 7 and is in a protected state.

[0052] In a further preferred embodiment, the launch tube 100 is provided with a third recessed space 5 that is recessed away from the extension direction of the wing, and the third space is located in the third recessed space 5; in this embodiment, the support frame can be rotated and unfolded around the launch tube 100 via the third connecting component 7 to unfold the curtain, and can also be rotated on the longitudinal section of the launch tube 100 to be stored in the third recessed space 5.

[0053] The supporting frame includes a main frame 510 and a secondary frame 520. The two sides of the curtain are connected to the main frame 510 and the secondary frame 520 respectively. The first end of the main frame 510 is connected to the launch tube 100. One end of the secondary frame 520 is rotatably connected to the first end of the main frame 510. The second end of the main frame 510 extends in a radiating manner in a direction away from the launch tube 100.

[0054] When the supporting frame is in the protected state, the curtain is located at the end of the launch tube 100 near the outlet 110, and the curtain can be unfolded around the outlet 110 through the supporting frame. For example, the third connecting component 7 includes a hinged pin structure that allows the first end of the main frame 510 to be rotatably connected to the launch tube 100, and a hinged pin structure that allows the first end of the main frame 510 to be rotatably connected to one end of the secondary frame 520. This allows the secondary frame 520 to rotate circumferentially along the launch tube 100 until it is closed with the main frame 510. Then, by rotating the main frame 510 in the longitudinal section of the launch tube 100, the main frame 510 and the secondary frame 520 can be stored together in the third recessed space 5. This is an action effect easily achieved by existing technology, and the specific structure of the third connecting component 7 will not be described in detail here. It should be noted that in this embodiment, the first recessed space 3, the second recessed space 4, and the third recessed space 5 are spaced apart circumferentially along the launch tube 100 to avoid interference. Furthermore, the aircraft 200 is typically provided with multiple winglets, and the first recessed space 3, the second recessed space 4 and the third recessed space 5 are preferably respectively disposed between two circumferentially adjacent winglets.

[0055] More preferably, the sub-frame 520 includes a first sub-frame 521 and a second sub-frame 522. One end of the first sub-frame 521 is rotatably connected to the main frame 510 and is used to rotate counterclockwise to a first position. One end of the second sub-frame 522 is rotatably connected to the main frame 510 and is used to rotate clockwise to a second position. The first and second positions are located on opposite sides of the main frame 510. This embodiment, by respectively arranging the first sub-frame 521 and the second sub-frame 522 on opposite sides of the main frame 510, can expand the angular coverage range of the curtain and increase the protection area of ​​the protective component 500.

[0056] In a further preferred embodiment, the second sub-frame 522 includes an arc-shaped segment 5221 and a straight segment 5222. One end of the arc-shaped segment 5221 is rotatably connected to the main frame 510, and the other end of the arc-shaped segment 5221 is connected to one end of the straight segment 5222. The arc-shaped segment 5221 matches the outer wall surface of the emission end of the launch tube 100, thereby increasing the rotatable angle of the second sub-frame 522 and allowing the curtain to cover a wider angle range.

[0057] In another preferred embodiment, the launching device further includes a protective cover 6, which has a receiving cavity in which the launching tube 100 can be housed. The protective cover 6 protects the launching device from unnecessary impacts. In this embodiment, the protective cover 6 is cylindrical. When the launching control component 300, aiming component 400, protection component 500, etc., are all stored on the launching tube 100, the launching tube 100 can be housed in the protective cover 6. It has a compact and neat shape, making it convenient for transfer or deployment.

[0058] In this specification, unless otherwise expressly specified and limited, "above" or "below" the second feature can mean that the first and second features are in direct contact, or that the first and second features are in indirect contact through an intermediate medium. Furthermore, "above," "over," and "on top" of the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0059] In the description of this specification, the references to terms such as "preferred embodiment," "another embodiment," "other embodiment," or "specific example," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in a suitable manner in any one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0060] Although embodiments of this application have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting this application. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of this application.

Claims

1. A launching device for an aircraft, the aircraft comprising a main body and winglets connected to the main body, characterized in that: The launching device includes a launching tube and a launching control component connected to the launching tube. One end of the launching tube is a launch port. The launching tube is provided with a launching channel leading to the launch port. The aircraft is placed in the launching channel. The launching control component can launch the aircraft from the launch port. The launch channel includes a main channel and a side channel connected to the main channel. The main body is housed in the main channel, and the winglets are housed in the corresponding side channels. The main body is launched through the main channel, and the winglets are launched through the side channels.

2. The launching device according to claim 1, characterized in that: The launch control assembly includes a launch base connected to the launch tube, and the launch base is provided with control buttons.

3. The launching device according to claim 2, characterized in that: The launch tube is provided with a first space, and the launch base is connected to the launch tube through a first connecting component. The launch base can be folded and stored in the first space through the first connecting component and is in a stored state, or it can be unfolded through the first connecting component and extended out of the first space to be in a launch state.

4. The launching device according to claim 3, characterized in that: The wing extends radially from the main body in a direction away from the main body, and the launch tube is provided with a first recessed space that is recessed in the direction opposite to the extension of the wing, and the first space is located in the first recessed space.

5. The launching device according to claim 1, characterized in that: The launching device also includes an aiming assembly, which is fixed to the launching tube.

6. The launching device according to claim 5, characterized in that: The launch tube is provided with a second space. The aiming component is connected to the launch tube through a second connecting component. The aiming component can be folded and stored in the second space through the second connecting component and is in a stored state. It can also be unfolded through the second connecting component and extended out of the second space to be in a launching state.

7. The launching device according to claim 6, characterized in that: The launch tube is provided with a second recessed space that is recessed in the opposite direction to the extension direction of the wing, and the second space is located in the second recessed space.

8. The launching device according to claim 5, characterized in that: The aiming assembly includes a sight and a support assembly, wherein the sight is connected to the launch tube via the support assembly.

9. The launching device according to claim 8, characterized in that: The support assembly includes a connector, a first support, and a second support. The first support and the second support are respectively connected to the launch tube, and both ends of the connector are respectively connected to the first support and the second support.

10. The launching device according to claim 1, characterized in that: The launching device also includes a protective component fixed to the launching tube, which is used to form a protective curtain when the aircraft is launched.

11. The launching device according to claim 10, characterized in that: The protective assembly includes a foldable curtain and a support frame, with the curtain connected to the launch tube via the support frame.

12. The launching device according to claim 11, characterized in that: The launch tube is provided with a third space, and the support frame is connected to the launch tube through a third connecting component. The support frame can be folded and stored in the third space through the third connecting component to be in a stored state, or it can be unfolded and extended out of the third space to be in a protected state.

13. The launching device according to claim 12, characterized in that: The launch tube is provided with a third recessed space that is recessed away from the extension direction of the wing, and the third space is located in the third recessed space; And / or, the supporting frame includes a main frame and a sub-frame, the two sides of the curtain are respectively connected to the main frame and the sub-frame, the first end of the main frame is connected to the launch tube, one end of the sub-frame is rotatably connected to the first end of the main frame, and the second end of the main frame extends in a radiating manner away from the launch tube; And / or, when the support frame is in the protected state, the curtain is located at the end of the launching tube near the emission port, and the curtain can be deployed around the emission port through the support frame.

14. A launching device for an aircraft according to any one of claims 1 to 13, characterized in that: The launching device also includes a protective cover, which has a receiving cavity in which the launching tube can be housed.

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