Aircraft launching device and protective assembly therefor

Abstract

The utility model provides a kind of aircraft launching device and its protection assembly, the launching device is provided with exit, the aircraft is sent from the exit, the protection assembly is arranged around the exit, the protection assembly is used to form partition curtain around the exit when launching the aircraft. The utility model is by being provided with the protection assembly in the exit, the protection assembly can form partition curtain around the exit, so as to be able to form effective barrier and protection to operator located in launching area when launching the aircraft, avoid that foreign matter such as smoke, particle causes harm to operator, reduce the operation safety hidden danger of operator, improve the overall safety of aircraft launching device.

Description

Technical Field

[0001] This utility model relates to the field of flight equipment technology, specifically to an aircraft launching device and its protective components. Background Technology

[0002] In recent years, with the widespread application of small aircraft, launch operations have gradually expanded from professionals to ordinary users, making the safety protection needs of operators increasingly urgent. Related data shows that approximately 35% of personal injuries in small aircraft operation accidents occur during the launch phase, with over 80% of these directly related to the lack of protective measures in the launch device. While some large aircraft launch systems are equipped with comprehensive safety protection devices, these devices are bulky, costly, and their design concepts for large aircraft cannot be directly adapted to the lightweight and portable requirements of small aircraft launch devices. Therefore, there is an urgent need for a launcher protection technology solution that can adapt to small aircraft launch scenarios, balancing protective effectiveness with device practicality, to address the safety hazards of existing launch devices and improve the overall safety of small aircraft operations. Utility Model Content

[0003] In view of this, the purpose of this utility model is to provide an aircraft launching device and its protective components to solve the safety hazards caused by the lack of protective measures for operators in existing launching devices.

[0004] To solve the above-mentioned technical problems, the technical solution used in this utility model is as follows:

[0005] On one hand, the present invention provides a protective component for an aircraft launching device, wherein the launching device is provided with an exit port, the aircraft is launched from the exit port, and the protective component is disposed around the exit port, the protective component being used to form a partition curtain around the exit port when the aircraft is launched.

[0006] Preferably, the protective component includes a curtain and a supporting frame, the transmitting device includes a transmitting tube, the emission port is disposed at the emission end of the transmitting tube, and the curtain is connected to the transmitting tube through the supporting frame.

[0007] More preferably, the curtain is foldable, and the curtain is unfolded and / or folded by the supporting frame.

[0008] 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.

[0009] More preferably, the aircraft includes a main body and a wing connected to the main body, the wing extending radially from the main body in a direction away from the main body, and the launch tube is provided with a third recessed space recessed in the direction opposite to the extension direction of the wing, the third space being located in the third recessed space;

[0010] And / or, when the support frame is in the protected state, the curtain is located at the emission end of the emission tube, and the curtain can be unfolded around the emission port through the support frame.

[0011] More preferably, the supporting frame includes a main frame and a secondary frame, with both sides of the curtain connected to the main frame and the secondary frame respectively. The first end of the main frame is connected to the launch tube, and the second end of the main frame extends radially away from the launch tube. One end of the secondary frame is rotatably connected to the first end of the main frame.

[0012] More preferably, the sub-frame includes a first sub-frame and a second sub-frame, one end of the first sub-frame being rotatably connected to the main frame for rotating counterclockwise to a first position; one end of the second sub-frame being rotatably connected to the main frame for rotating clockwise to a second position, the first position and the second position being located on both sides of the main frame.

[0013] More preferably, the second subframe includes an arc-shaped segment and a straight segment, one end of the arc-shaped segment being rotatably connected to the main frame, and the other end of the arc-shaped segment being connected to one end of the straight segment.

[0014] More preferably, the curtain is made of a transparent material.

[0015] On the other hand, this utility model provides an aircraft launching device, including the aforementioned protective component of an aircraft launching device.

[0016] Compared with the prior art, the beneficial effects of the protective component for an aircraft launch device described in this utility model are mainly reflected in:

[0017] This invention provides a protective component at the launch port, which forms a barrier curtain around the launch port. This effectively isolates and protects operators within the launch area during the launch of the aircraft, preventing smoke, particles, and other foreign objects from harming the operators, reducing operational safety hazards, and improving the overall safety of the aircraft launch device. Attached Figure Description

[0018] 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.

[0019] Figure 1 A three-dimensional structural diagram of an aircraft launching device provided for an embodiment of this utility model. Figure 1 ;

[0020] Figure 2 A three-dimensional structural diagram of an aircraft launching device provided for an embodiment of this utility model. Figure 2 ;

[0021] Figure 3 for Figure 2 View A in the middle;

[0022] Figure 4 A three-dimensional structural diagram of an aircraft launch device stored in the protective cover, as provided in an embodiment of this utility model;

[0023] Figure label:

[0024] Launch tube 100, launch port 110, launch channel 120, main channel 121, side channel 122;

[0025] Aircraft 200;

[0026] Launch control assembly 300, launch base 310, control button 320;

[0027] Aiming component 400, connector 410, first support 420, second support component 430;

[0028] Protective component 500, main frame 510, secondary frame 520, first secondary frame 521, second secondary frame 522, arc segment 5221, straight segment 5222;

[0029] 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

[0030] 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.

[0031] 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.

[0032] This embodiment provides a protective component 500 for an aircraft launch device, such as... Figures 1 to 4 As shown, the launching device is provided with an exit port 110, from which the aircraft 200 is launched. A protective component 500 is disposed around the exit port 110. The protective component 500 is used to form a partition curtain around the exit port 110 when the aircraft 200 is launched.

[0033] This utility model provides a protective component 500 at the launch port 110. The protective component 500 can form a partition curtain around the launch port 110, thereby effectively blocking and protecting the operators in the launch area when the aircraft 200 is launched, preventing smoke, particles and other foreign objects from causing harm to the operators, reducing the safety hazards of the operators, and improving the overall safety of the aircraft 200 launch device.

[0034] In a preferred embodiment, the protective component 500 includes a curtain (not shown) and a supporting frame. The launching device includes a launching tube 100, and a launching port 110 is located at the launching end of the launching tube 100. The curtain is connected to the launching tube 100 via the supporting frame. More preferably, the curtain is foldable, unfolding and / or folding via the supporting frame. The curtain is made of transparent material, so that it does not obstruct the operator's line of sight when unfolded. In this embodiment, the curtain, via the supporting frame, can form a partition curtain around the launching port 110, separating the area in front of and behind the launching end of the launching tube 100, thus protecting the operator in the launching area behind the launching end of the launching tube 100.

[0035] 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.

[0036] In a further preferred embodiment, the aircraft 200 includes a main body and a wing connected to the main body. The wing extends radially from the main body in a direction away from the main body. The launch tube 100 is provided with a third recessed space 5 that is recessed away from the direction of extension of the wing. The third space is located in the third recessed space 5.

[0037] And / or, when the support frame is in a protected state, the curtain is located at the exit end of the launch tube 100, and the curtain can be deployed around the exit port 110 through the support frame.

[0038] In this embodiment, the support frame can be rotated and unfolded circumferentially along the launching tube 100 via the third connecting component 7 to unfold the curtain. It can also be rotated along the longitudinal section of the launching tube 100 to be stored in the third recessed space 5. In addition to unfolding and / or folding the curtain, the support frame can also support the curtain, ensuring its stability after unfolding and its orderly folding.

[0039] In a further preferred embodiment, 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 launching tube 100, and the second end of the main frame 510 extends radially away from the launching tube 100. One end of the secondary frame 520 is rotatably connected to the first end of the main frame 510. As an example, the third connecting component 7 includes a hinge pin structure that allows the first end of the main frame 510 to be rotatably connected to the launching tube 100, and a hinge 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 launching tube 100 until it is closed with the main frame 510. Then, by rotating the main frame 510 in the longitudinal section of the launching tube 100, the main frame 510 and the secondary frame 520 are stored together in the third recessed space 5. This is an action effect that is easily achieved in the prior art, and the specific structure of the third connecting component 7 will not be described in detail here.

[0040] 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.

[0041] 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.

[0042] Based on the above embodiments, another embodiment of an aircraft launcher 200 is provided, including the protective component 500 of the aforementioned aircraft launcher. This embodiment of the aircraft launcher 200 is equipped with the aforementioned protective component 500, possessing the beneficial effects of the aforementioned protective component 500, and offering higher safety in use.

[0043] The aircraft launching device in this embodiment includes a launch tube 100 and a launch control component 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 component 300 can launch the aircraft 200 from the launch port 110. The aircraft 200 includes a main body and wings connected to the main body.

[0044] 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.

[0045] 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.

[0046] 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.

[0047] 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, and is a movement effect easily achievable with existing technology; therefore, it will not be listed here.

[0048] 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.

[0049] 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.

[0050] 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.

[0051] 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.

[0052] 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.

[0053] It should be noted that the first recessed space 3, the second recessed space 4, and the third recessed space 5 are arranged at intervals along the circumference of 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 arranged between two circumferentially adjacent winglets.

[0054] 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.

[0055] 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.

[0056] 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.

[0057] 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 protective assembly for an aircraft launch device, characterized in that: The launching device is provided with a launch port from which the aircraft is launched. The protective component is disposed around the launch port and is used to form a partition curtain around the launch port when the aircraft is launched.

2. The protection component according to claim 1, characterized in that: The protective assembly includes a curtain and a supporting frame, the launching device includes a launching tube, the launching port is located at the launching end of the launching tube, and the curtain is connected to the launching tube through the supporting frame.

3. The protection component according to claim 2, characterized in that: The curtain is foldable, and it unfolds and / or folds through the supporting frame.

4. The protection component according to claim 3, 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.

5. The protection component according to claim 4, characterized in that: The aircraft includes a main body and a wing connected to the main body. The wing extends radially from the main body in a direction away from the main body. The launch tube is provided with a third recessed space that is recessed away from the extension direction of the wing. The third space is located in the third recessed space. And / or, when the support frame is in the protected state, the curtain is located at the emission end of the emission tube, and the curtain can be unfolded around the emission port through the support frame.

6. The protection component according to claim 3, characterized in that: The supporting frame includes a main frame and a secondary frame. The two sides of the curtain are respectively connected to the main frame and the secondary frame. The first end of the main frame is connected to the launch tube, and the second end of the main frame extends in a radiating manner away from the launch tube. One end of the secondary frame is rotatably connected to the first end of the main frame.

7. The protection component according to claim 6, characterized in that: The subframe includes a first subframe and a second subframe. One end of the first subframe is rotatably connected to the main frame and is used to rotate counterclockwise to a first position. One end of the second subframe is rotatably connected to the main frame and is used to rotate clockwise to a second position. The first position and the second position are located on both sides of the main frame.

8. The protection component according to claim 7, characterized in that: The second subframe includes an arc-shaped segment and a straight segment. One end of the arc-shaped segment is rotatably connected to the main frame, and the other end of the arc-shaped segment is connected to one end of the straight segment.

9. The protection component according to claim 2, characterized in that: The curtain is made of transparent material.

10. A spacecraft launching device, characterized in that: A protective component for an aircraft launch device, including any one of claims 1 to 9.

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