Pneumatic catapult rack and multi-connected launcher for unmanned aerial vehicle

Abstract

The utility model relates to a pneumatic catapulting rack and a multi-connected catapulting rack for an unmanned aerial vehicle. In one embodiment, the pneumatic ejection rack comprises a retainer, two ejection air cylinders parallel to each other, an air connecting pipe, an air storage tank, an air valve and two guide parts. The holder comprises two mutually parallel holding rods extending from a first transverse end to a second transverse end, and a first connecting rod connecting the first transverse ends of the two holding rods. The two ejection air cylinders are supported above the two holding rods correspondingly so that the two unmanned aerial vehicle air cylinders of the unmanned aerial vehicle can be arranged on the two ejection air cylinders in a sleeving mode correspondingly. The first transverse ends of the two ejection air cylinders are communicated through the air connecting pipe. The gas storage tank is used for storing compressed gas and connected with the gas connecting pipe through the gas valve. The two guide parts are arranged at the second transverse ends of the two holding rods correspondingly and used for supporting two unmanned aerial vehicle inflators, arranged on the two ejection inflators in a sleeving mode, of the unmanned aerial vehicle correspondingly so as to prevent each unmanned aerial vehicle inflator from deflecting in the circumferential direction of the corresponding ejection inflator.

Description

Technical Field

[0001] The embodiments of the utility model relate to the field of aircraft, and more specifically to a pneumatic ejection rack and a multi-launching rack for unmanned aerial vehicles. Background Art

[0002] UAVs are also called unmanned aerial vehicles. At present, there are various pneumatic ejection racks for UAVs as UAV take-off auxiliary equipment. Common pneumatic ejection racks are mainly divided into the following categories: rail-mounted traction type, rail-mounted piston push rod type, and whole machine barrel ejection type. In the rail-mounted traction ejection rack, a trolley sliding on the track is used to carry the UAV, and the trolley is connected to the pneumatic assembly via a pulley through a traction rope so as to receive the traction force of the pneumatic assembly to eject the UAV, for example, as described in the Chinese patent application with publication number CN108190040A. In the rail-mounted piston push rod ejection rack, a trolley sliding on the track is used to carry the UAV, and the trolley receives the thrust of the high-pressure gas source through the push rod and the piston to eject the UAV. In the whole machine barrel ejection ejection rack, the UAV is stored in a folded form in the ejection barrel, and the piston in the ejection barrel receives the thrust of the high-pressure gas source connected to the ejection barrel to eject the UAV. Utility Model Content

[0003] This section is provided to introduce a selection of concepts in a simplified form that are further described below in the Detailed Description. This section is not intended to identify essential features of the claimed subject matter, nor is it intended to limit the scope of the claimed subject matter.

[0004] One of the purposes of the utility model is to provide an improved pneumatic ejection frame for unmanned aerial vehicles. In particular, one of the technical problems to be solved by the utility model is that the existing pneumatic ejection frame for unmanned aerial vehicles uses a single ejection gas cylinder. When the thrust provided by the high-pressure gas source is given, the length of the gas cylinder required to accelerate the unmanned aerial vehicle to the desired launch speed is given, resulting in the inability to shorten the length of the ejection frame including the gas cylinder, and thus further miniaturization cannot be achieved. Another technical problem to be solved by the utility model is that in the existing pneumatic ejection frame for unmanned aerial vehicles, the piston is a precision part that is used multiple times, and the size is required to be precise, resulting in increased manufacturing difficulty and cost, and increased difficulty in use. Another technical problem to be solved by the utility model is that in the existing ejection frame using a piston push rod propulsion system, in each ejection process, the piston and the push rod are ejected into the air following the launch of the unmanned aerial vehicle and then fall in front of the ejection frame, and the resulting landing impact is likely to damage the piston and the push rod, thereby reducing the service life or even directly making it impossible to use again. Another technical problem to be solved by the utility model is that some existing ejection racks must be equipped with ejection tracks and trolleys to maintain the posture of the UAV during ejection. In particular, some ejection racks must also be equipped with a deceleration system to decelerate the aircraft-carrying trolley to a stop after ejection, which results in a complex structure of the ejection rack and a large number of parts.

[0005] According to the first aspect of the utility model, a pneumatic ejection frame for a drone is provided. The pneumatic ejection frame includes a retaining frame, two ejection gas cylinders parallel to each other, an air connecting pipe, an air storage tank, an air valve, and two guiding components. The retaining frame includes: two retaining rods parallel to each other, each retaining rod extending from a first lateral end toward a second lateral end opposite to the first lateral end; and a first connecting rod connecting the first lateral ends of the two retaining rods. The two ejection gas cylinders are respectively supported above the two retaining rods, so that the two drone gas cylinders of the drone can be respectively sleeved on the two ejection gas cylinders. The air connecting pipe connects the first lateral ends of the two ejection gas cylinders. The air storage tank is used to store compressed gas and is connected to the air connecting pipe through an air valve. The two guiding components are respectively arranged at the second lateral ends of the two retaining rods, and are used to respectively support the two drone gas cylinders of the drone sleeved on the two ejection gas cylinders, so as to prevent each drone gas cylinder from deflecting along the circumference of the corresponding ejection gas cylinder.

[0006] According to the first aspect, due to the use of two mutually parallel ejection cylinders, not only can the thrust of the compressed gas from the gas tank be doubled, thereby shortening the overall length of the ejection frame, reducing the weight, and facilitating transportation and storage, but also the double ejection cylinders themselves can provide a stable posture when the UAV is launched, thereby eliminating the redundant running tracks and trolleys and the corresponding deceleration mechanism, reducing the complexity of the ejection frame, reducing the number of parts, simplifying the launch process, improving the launch efficiency, and eliminating the maintenance and repair problems caused by the deceleration system. Since the two UAV cylinders of the UAV can be respectively mounted on the two ejection cylinders of the ejection frame to receive the thrust from the compressed air, precision parts such as pistons can be omitted, thereby reducing the manufacturing difficulty and cost, and reducing the difficulty of use. Furthermore, the piston push rod component can also be omitted, eliminating the risk of damage to parts due to repeated use. Since two guide components are used to support the two UAV cylinders, the strength and rigidity required for the two ejection cylinders to support the two UAV cylinders can be reduced, thereby reducing the weight and manufacturing difficulty of the two ejection cylinders, and the differential deformation between the ejection cylinder and the UAV cylinder can be reduced, thereby reducing friction. With the cooperation of the two guide components and the two ejection cylinders, the drone can be restrained from rolling in three dimensions, so that the drone can only perform accelerated motion along the axis of the ejection cylinders.

[0007] In one embodiment of the utility model, the retaining frame also includes: two support rods, which extend from the second lateral ends of the two retaining rods to the bottom of the two retaining rods, respectively, so that when the pneumatic ejection frame is placed on the supporting surface, the two ejection cylinders are parallel to the target ejection direction of the drone.

[0008] In an embodiment of the present invention, the two support rods are detachably connected to the second transverse ends of the two retaining rods respectively.

[0009] In one embodiment of the present invention, the retaining frame further comprises: a second connecting rod, which connects the ends of the two supporting rods for contacting the supporting surface.

[0010] In one embodiment of the present invention, the length of the support rod is adjustable.

[0011] In one embodiment of the present invention, each guide component comprises: a support member arranged around the corresponding ejection gas cylinder; and three or more pivotable guide wheels installed on the support member at intervals from each other along the circumference of the ejection gas cylinder.

[0012] In one embodiment of the utility model, the support member is a U-shaped groove. A first guide wheel and a second guide wheel are respectively installed at the ends of two vertical walls of the U-shaped groove. A recessed portion that is recessed downward is provided at the bottom center of the U-shaped groove. A third guide wheel is installed in the recessed portion.

[0013] In one embodiment of the present invention, the gas storage tank is connected to the center position of the gas connecting pipe through the gas valve.

[0014] In one embodiment of the present invention, the gas storage tank is located above the gas connecting pipe.

[0015] According to the second aspect of the utility model, a multiple launcher for a drone is provided. The multiple launcher comprises: a base; four pillars fixed to the base, the projections of the four pillars on the plane where the base is located constitute the four vertices of a rectangle; and a plurality of pneumatic ejection frames according to the first aspect above mounted on the four pillars. The plurality of pneumatic ejection frames are spaced apart from each other in the up-down direction. The two ejection cylinders of each pneumatic ejection frame are perpendicular to the four pillars, or form a predetermined acute angle with the horizontal plane.

[0016] According to the above-mentioned second aspect, since the multi-launch frame uses the pneumatic ejection frame according to the above-mentioned first aspect, the structure of the multi-launch frame can be simplified and the manufacturing cost can be reduced, and more drones can be loaded in the same accommodation space, realizing the transportation and / or cluster launch of more drones.

[0017] In one embodiment of the present invention, the plurality of pneumatic ejection racks are detachably mounted on the four pillars. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solution of the utility model, the drawings of the embodiments are briefly introduced below. Obviously, the structural schematic diagrams in the following drawings are not necessarily drawn to scale, but present various features in a simplified form. Moreover, the following drawings only relate to some embodiments of the utility model, and do not limit the utility model.

[0019] Figure 1 is a perspective view showing a pneumatic ejection rack for a drone according to an exemplary embodiment of the present invention;

[0020] Figure 2 It is shown Figure 1 A partial enlarged view of a guide component included in a pneumatic ejection frame;

[0021] Figure 3A and Figure 3B The drone is shown mounted on Figure 1 A structural view of the state of the pneumatic ejection rack;

[0022] Figure 4 is a perspective view showing a multiple launch rack for a drone according to an exemplary embodiment of the present utility model; and

[0023] Figure 5 It shows that multiple drones are installed Figure 4 A perspective view of the status of the multiple launcher. DETAILED DESCRIPTION

[0024] For purposes of explanation, certain details are set forth in the following description in order to provide a thorough understanding of the disclosed embodiments. However, it is apparent to one skilled in the art that the embodiments may be practiced without these specific details or with an equivalent configuration.

[0025] As mentioned above, the existing pneumatic ejection racks are mainly divided into the following categories: rail-mounted traction type, rail-mounted piston push rod type, and whole-machine barrel-launched type. Regarding the existing pneumatic ejection racks, the inventors of the utility model realize that the existing pneumatic ejection racks use a single ejection gas cylinder. When the thrust provided by the high-pressure gas source is given, the length of the gas cylinder required to accelerate the drone to the desired launch speed is given, which results in the length dimension of the ejection rack containing the gas cylinder being unable to be shortened, and thus unable to achieve further miniaturization. As another technical problem, the inventors of the utility model also realize that in the existing pneumatic ejection racks for drones, the piston is a precision part used multiple times, requiring precise dimensions, resulting in increased manufacturing difficulty and cost, and increased difficulty in use. As another technical problem, the inventors of the utility model also realize that in the existing ejection racks using a piston push rod propulsion system, in each ejection process, the piston and the push rod follow the launch of the drone and are ejected into the air and then fall in front of the ejection rack, causing a high probability of damage to the piston and the push rod caused by the landing impact, thereby reducing the service life or even directly making it impossible to use again. As another technical problem, the inventor of the utility model also realized that some existing ejection racks must be equipped with ejection tracks and carts to maintain the posture of the UAV during launch. In particular, some ejection racks must also be equipped with a deceleration system to decelerate the aircraft carrier cart to stop after launch, which leads to a complex structure of the ejection rack and a large number of parts.

[0026] The utility model provides an improved pneumatic ejection rack and a multi-link launch rack for a UAV. In the following, embodiments of the utility model will be described in detail with reference to the accompanying drawings.

[0027] Figure 1 is a perspective view showing a pneumatic ejection rack for a drone according to an exemplary embodiment of the present utility model. Figure 1As shown, the pneumatic ejection frame includes a retaining frame, two ejection air cylinders 121 and 122 parallel to each other, an air connection pipe 13, an air storage tank 14, an air valve 15, and two guide components 161 and 162. The retaining frame includes two retaining rods 1111 and 1112 parallel to each other, a first connecting rod 112, two supporting rods 1131 and 1132, and a second connecting rod 114.

[0028] The retaining frame can be made of metal or other suitable materials with high rigidity and strength. Figure 1 The right end in the middle) is directed toward a second lateral end (eg, Figure 1 The first connecting rod 112 connects the first lateral ends (e.g. Figure 1 The two support rods 1131 and 1132 are connected to the second lateral ends (e.g. Figure 1 The left end of the pneumatic ejection frame (in the figure) extends downwardly from the two retaining rods 1111 and 1112, so that when the pneumatic ejection frame is placed on a supporting surface (e.g., the ground), the two ejection cylinders 121 and 122 are parallel to the target ejection direction of the UAV. The target ejection direction of the UAV can be a direction tilted upward from the ground to the air. Optionally, the length of each support rod 1131 and 1132 is adjustable so that the ejection direction of the UAV can be adjusted. The second connecting rod 114 connects the ends of the two support rods 1131 and 1132 for contacting the supporting surface.

[0029] Two mutually parallel ejection cylinders 121, 122 are supported above two retaining rods 1111, 1112 respectively, so that the two UAV cylinders of the UAV can be respectively mounted on the two ejection cylinders 121, 122. Figure 1 Each ejection cylinder can be fixed by a fixing ring (see Figure 1 ) or other suitable fixing components are supported above the corresponding retaining rod. Figure 1 Each ejection cylinder can be supported above the corresponding retaining rod by a guide component described later. The sleeve connection between the drone cylinder and the ejection cylinder will be described in detail later with reference to the guide component.

[0030] The gas connection pipe 13 connects the first lateral ends (eg Figure 1The gas tank 14 is used to store compressed gas and is connected to the gas connecting pipe 13 through an air valve 15 (such as a quick release valve). For example, an external air pump (such as an air pump) can be used to fill the gas tank 14 with compressed gas (such as high-pressure air). By operating the air valve 15, the supply of compressed gas from the gas tank 14 to the gas connecting pipe 13 can be opened or closed. The gas tank 14 is located above the gas connecting pipe 13 and is connected to the center position of the gas connecting pipe 13 through the air valve 15. Since the gas tank 14 is connected to the center position of the gas connecting pipe 13, the same thrust can be provided to the two ejection air cylinders 121 and 122 connected to the gas connecting pipe 13.

[0031] The two guide components 161 and 162 are respectively connected to the second lateral ends (eg Figure 1 The left end of the support member is provided to support the two air cylinders of the drone respectively on the two ejection air cylinders 121 and 122, so as to prevent each air cylinder of the drone from deflecting along the circumference of the corresponding ejection air cylinder. Figure 1 The left side in the figure is the front side of the pneumatic ejection frame. Figure 2 FIG. 1 is a front view of one of the two guide components 161 and 162. For simplicity, Figure 2 Only the guide component and the corresponding ejection gas cylinder are shown. Figure 1 and Figure 2 It can be seen that each of the two guide components 161, 162 includes a support member 1614 or 1624 arranged around the corresponding ejection cylinder, and three pivotable guide wheels installed on the support member at intervals from each other along the circumference of the ejection cylinder. Each support member can be fixed to the corresponding retaining rod by welding or other suitable fixing methods. Each support member can be a U-shaped groove. The first guide wheel 1611 or 1621 and the second guide wheel 1612 or 1622 are respectively installed at the ends of the two vertical walls of the U-shaped groove. A downwardly recessed portion is provided at the bottom center of the U-shaped groove, and a third guide wheel 1613 or 1623 is installed in the recessed portion. As shown in FIG. Figure 2 As shown, a gap is provided between the ejection air cylinder and the three guide wheels of the corresponding guide component, so that the two UAV air cylinders of the UAV can be respectively mounted on the two ejection air cylinders of the pneumatic ejection frame.

[0032] Figure 3A and Figure 3B The drone is shown mounted on Figure 1 A structural view of the state of the pneumatic ejection frame, where Figure 3A It is a perspective view. Figure 3B is the front view. Figure 3AAs shown, the drone cylinder 321 or 322 is connected to the corresponding ejection cylinder 121 or 122 over substantially the entire length thereof, so that the drone can be stably supported to provide a stable posture for the drone when launched. Figure 3B As shown, when the drone cylinder is sleeved on the ejection cylinder, each drone cylinder is in contact with the three guide wheels of the corresponding guide component. Figure 2 By comparison, it can be seen that the radius of each drone air cylinder is slightly larger than the radius of the corresponding ejection air cylinder, so that the drone air cylinder can be slidably mounted on the corresponding ejection air cylinder along the outer surface of the corresponding ejection air cylinder.

[0033] In use Figure 1 When the pneumatic ejection frame shown is used to eject the drone, the compressed gas (e.g., high-pressure air) in the gas tank can be released by operating the air valve. The compressed gas is released to the two ejection cylinders through the air connecting pipe, thereby ejecting the compressed gas outward. Since the drone cylinder (which belongs to the drone structure) with a closed front end of the drone is sleeved on the ejection cylinder to form a closed cavity, the compressed gas can expand the relatively closed cavity and push the drone to eject and take off. When performing a single launch, there is no need to carry an air pump (e.g., an air pump), and it is only necessary to store compressed gas in the gas tank. When multiple launches are required, an air pump can be carried to replenish the compressed gas in the gas tank.

[0034] for Figure 1 The pneumatic ejection frame shown in the figure uses two ejection cylinders parallel to each other, which can not only double the thrust of the compressed gas from the gas tank, thereby shortening the overall length of the ejection frame, reducing the weight, and facilitating transportation and storage, but also the double ejection cylinders themselves can provide a stable posture when the UAV is launched, thereby eliminating redundant running tracks and trolleys and corresponding deceleration mechanisms, reducing the complexity of the ejection frame, reducing the number of parts, simplifying the launch process, improving the launch efficiency, and eliminating the maintenance problems caused by the deceleration system. Since the two UAV cylinders of the UAV can be respectively mounted on the two ejection cylinders of the ejection frame to receive the thrust from the compressed air, precision parts such as pistons can be omitted, thereby reducing the difficulty and cost of manufacturing and reducing the difficulty of use. Furthermore, the piston push rod component can also be omitted, eliminating the risk of damage to parts due to repeated use. Since two guide components are used to support the two drone cylinders, the strength and rigidity required for the two ejection cylinders to support the two drone cylinders can be reduced, thereby reducing the weight and manufacturing difficulty of the two ejection cylinders, and reducing the differential deformation between the ejection cylinder and the drone cylinder, thereby reducing friction. With the cooperation of the two guide components and the two ejection cylinders, the drone can be constrained from rolling in three dimensions, so that the drone can only perform accelerated motion along the axial direction of the ejection cylinder.

[0035] It should be noted that the present invention is not limited to the examples described above. As another example, the two support rods 1131, 1132 can be detachably connected to the second lateral ends (e.g. Figure 1 In this way, when multiple ejection racks are transported and / or drone clusters are launched, the two support rods 1131, 1132 of each ejection rack can be removed and the remaining parts can be installed on the bracket to form a multi-link launch rack, as described in detail later. As another example, the retaining frame of the pneumatic ejection rack may only include two retaining rods 1111, 1112 parallel to each other, a first connecting rod 112, and two support rods 1131, 1132. That is, the second connecting rod 114 can be omitted as an optional component. As another example, the retaining frame of the pneumatic ejection rack may only include two retaining rods 1111, 1112 parallel to each other, and a first connecting rod 112. That is, the two support rods 1131, 1132 and the second connecting rod 114 can be omitted as optional components. In this way, the pneumatic ejection rack can be used as a component of the multi-link launch rack described in detail later.

[0036] As another example, the position where the gas storage tank is connected to the gas connecting pipe may not be the center position of the gas connecting pipe, as long as the thrust of the compressed gas ultimately delivered to the two ejection gas cylinders is equal (for example, a flow regulating valve may be used in the gas connecting pipe to adjust the gas delivery amount). As another example, the gas storage tank may not be located above the gas connecting pipe, but as long as the gas storage tank is connected to the gas connecting pipe through a gas valve, it will be fine.

[0037] As another example, the support member in the guide component may not be Figure 2 The U-shaped groove shown in the figure may take other suitable shapes. For example, the support member may be in the form of a ring with a notch, and three or more guide wheels may be arranged spaced apart from each other along the ring. As another example, the portion of the guide component that contacts the drone cylinder may not take the form of a guide wheel, but may take the form of a non-pivoting component, as long as it can support the corresponding drone cylinder to prevent the drone cylinder from deflecting along the circumference of the corresponding ejection cylinder.

[0038] Based on the above description, at least one aspect of the utility model provides a pneumatic ejection frame for a drone. The pneumatic ejection frame includes a retaining frame, two ejection gas cylinders parallel to each other, an air connecting pipe, an air storage tank, an air valve, and two guiding components. The retaining frame includes: two retaining rods parallel to each other, each retaining rod extending from a first lateral end toward a second lateral end opposite to the first lateral end; and a first connecting rod connecting the first lateral ends of the two retaining rods. The two ejection gas cylinders are respectively supported above the two retaining rods, so that the two drone gas cylinders of the drone can be respectively sleeved on the two ejection gas cylinders. The air connecting pipe connects the first lateral ends of the two ejection gas cylinders. The air storage tank is used to store compressed gas and is connected to the air connecting pipe through an air valve. The two guiding components are respectively arranged at the second lateral ends of the two retaining rods, and are used to respectively support the two drone gas cylinders of the drone sleeved on the two ejection gas cylinders, so as to prevent each drone gas cylinder from deflecting along the circumference of the corresponding ejection gas cylinder.

[0039] In one embodiment, the retaining frame also includes: two support rods, which extend from the second lateral ends of the two retaining rods to the bottom of the two retaining rods, respectively, so that when the pneumatic ejection frame is placed on the supporting surface, the two ejection cylinders are parallel to the target ejection direction of the drone.

[0040] In one embodiment, the two support rods are detachably connected to the second transverse ends of the two retaining rods, respectively.

[0041] In one embodiment, the retaining frame further includes: a second connecting rod, which connects the ends of the two supporting rods for contacting the supporting surface.

[0042] In one embodiment, the length of the support rod is adjustable.

[0043] In one embodiment, each guide component comprises: a support member arranged around the corresponding ejection cylinder; and three or more pivotable guide wheels installed on the support member at intervals from each other along the circumference of the ejection cylinder. According to this embodiment, due to the use of the guide wheels, the friction between the ejection cylinder and the cylinder of the drone can be further reduced.

[0044] In one embodiment, the support member is a U-shaped groove. A first guide wheel and a second guide wheel are respectively installed at the ends of two vertical walls of the U-shaped groove. A recessed portion that is recessed downward is provided at the bottom center of the U-shaped groove. A third guide wheel is installed in the recessed portion.

[0045] In one embodiment, the gas storage tank is connected to the central position of the gas connection pipe through the gas valve.

[0046] In one embodiment, the gas storage tank is located above the gas connecting pipe.

[0047] Figure 4 is a perspective view showing a multi-launcher for a drone according to an exemplary embodiment of the present utility model. Figure 4 As shown, the multiple launcher includes four pillars 421, 422, 423, 424, and six pneumatic ejection frames mounted on the four pillars 421, 422, 423, 424. The four pillars can be fixed on a base. Figure 4 For the sake of simplicity, the base is not shown. It should be noted that the base is not limited to a dedicated component, but can also be a placement surface for placing the multiple launcher (for example, the bottom surface of the carrying space (such as a carriage) of a vehicle carrying the multiple launcher). The projections of the four pillars on the plane where the base is located constitute the four vertices of the rectangle. The four pillars can be made of metal or other suitable materials with high rigidity and strength, and can be fixed to the base by welding, by fixing components, or by other suitable fixing methods. The six pneumatic ejection racks are spaced apart from each other in the up and down directions, and the two ejection air cylinders of each pneumatic ejection rack are perpendicular to the four pillars. Each of the six pneumatic ejection racks is Figure 1 The pneumatic ejection frame shown is a portion after removing the two support rods 1131 , 1132 and the second connecting rod 114 . Figure 5 It shows that multiple drones are installed Figure 4 A perspective view of the state of the multi-launcher. Figure 5 As shown, six UAVs are respectively mounted on six pneumatic ejection racks of the multi-link launcher. When performing cluster launch (e.g., vehicle-mounted combined launch), the gas tank of each pneumatic ejection rack can be connected to a large gas tank (e.g., a vehicle-mounted large gas tank). Therefore, for the case of vehicle-mounted combined launch, only a large gas tank and an air pump (e.g., an air pump) are required.

[0048] for Figure 4 The multiple launcher shown uses Figure 1 The part of the pneumatic ejection rack shown can simplify the structure of the multi-launch rack, reduce the manufacturing cost, and can load more UAVs in the same accommodation space, realize the transportation and / or cluster launch of more UAVs.

[0049] It should be noted that the utility model is not limited to the examples described above. As another example, the number of pneumatic ejection frames mounted on the four pillars may also be other suitable numbers, as long as the number is two or more than two. As another example, multiple pneumatic ejection frames can be detachably mounted on four pillars. In this way, when the two support rods 1131, 1132 of each pneumatic ejection frame are detachably connected to the two retaining rods 1111, 1112, the two support rods 1131, 1132 can be removed and the remaining part of the pneumatic ejection frame can be mounted on the four pillars to facilitate the transportation and / or cluster launch of multiple pneumatic ejection frames. As another example, the two ejection air cylinders of each pneumatic ejection frame can be at a predetermined acute angle with the horizontal plane, thereby limiting the ejection direction of multiple drones mounted on the multi-link launcher. For example, each pneumatic ejection frame can be installed by a fixing component so that the two ejection gas cylinders of each pneumatic ejection frame form a predetermined acute angle with the horizontal plane, or the angle formed by the two ejection gas cylinders of each pneumatic ejection frame and the horizontal plane can be adjusted by an additional adjustment mechanism.

[0050] Based on the above description, at least another aspect of the present invention provides a multiple launcher for a drone. The multiple launcher comprises: a base; four pillars fixed to the base, the projections of the four pillars on the plane where the base is located constitute the four vertices of a rectangle; and a plurality of pneumatic ejection frames according to the first aspect above mounted on the four pillars. The plurality of pneumatic ejection frames are spaced apart from each other in the up and down directions. The two ejection air cylinders of each pneumatic ejection frame are perpendicular to the four pillars, or form a predetermined acute angle with the horizontal plane.

[0051] In one embodiment, the plurality of pneumatic ejection racks are detachably mounted to the four pillars.

[0052] References herein to "one embodiment," "an embodiment," etc., indicate that the described embodiment may include a particular feature, structure, or characteristic, but not every embodiment must include the particular feature, structure, or characteristic. Moreover, such phrases do not necessarily refer to the same embodiment. In addition, when a particular feature, structure, or characteristic is described in conjunction with one embodiment, it is within the knowledge of those skilled in the art to implement such feature, structure, or characteristic in conjunction with other embodiments, whether or not explicitly described.

[0053] It should be understood that, although the terms "first", "second" etc. can be used in this article to describe various elements, these elements should not be limited by these terms. These terms are only used to distinguish one element from another element. For example, the first element can be referred to as the second element, and similarly, the second element can be referred to as the first element, without departing from the scope of the present invention. In this article, the term "and / or" includes any one and all combinations of one or more of the associated listed terms. It should also be understood that the terms "include", "have", and / or "comprise" when used in this article refer to the existence of stated features, elements and / or components, and do not exclude the existence or addition of one or more other features, elements, components and / or their combinations. The term "connection" used in this article covers direct and / or indirect connection between two elements.

[0054] It should be understood that the orientations or positional relationships indicated by terms such as "top", "bottom", "inside" and "outside" are based on the orientations or positional relationships shown in the accompanying drawings, and are merely for the convenience and simplification of the description of the present invention. They do not indicate or imply that the elements, components, or devices referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0055] Embodiments of the present invention include any novel features or feature combinations disclosed herein explicitly or in any generalized form thereof. When read in conjunction with the accompanying drawings, based on the above description, various modifications and adaptations to the above exemplary embodiments of the present invention will become apparent to those skilled in the art. However, any and all modifications and adaptations will still fall within the scope of the non-restrictive and exemplary embodiments of the present invention.

Claims

1. A pneumatic ejection rack for a drone, characterized in that: include: A retaining frame, comprising: two retaining rods parallel to each other, each retaining rod extending from a first transverse end toward a second transverse end opposite to the first transverse end; and a first connecting rod connecting the first transverse ends of the two retaining rods; Two ejection gas cylinders are respectively supported on the two retaining rods and are parallel to each other, so that the two UAV gas cylinders of the UAV can be respectively mounted on the two ejection gas cylinders; An air connection pipe connecting the first lateral ends of the two ejection air cylinders; A gas storage tank for storing compressed gas, which is connected to the gas connection pipe via a gas valve; and The two guide components respectively arranged at the second lateral ends of the two retaining rods are used to respectively support the two drone air cylinders of the drone sleeved on the two ejection air cylinders to prevent each drone air cylinder from deflecting along the circumference of the corresponding ejection air cylinder.

2. The pneumatic ejection frame according to claim 1, wherein: The retainer also includes: Two support rods extend from the second lateral ends of the two retaining rods to the bottom of the two retaining rods, respectively, so that when the pneumatic ejection frame is placed on a supporting surface, the two ejection cylinders are parallel to the target ejection direction of the UAV.

3. The pneumatic ejection frame according to claim 2, wherein: The two support rods are detachably connected to the second transverse ends of the two retaining rods, respectively.

4. The pneumatic ejection frame according to claim 2, wherein: The retainer also includes: A second connecting rod connects the ends of the two supporting rods for contacting the supporting surface.

5. The pneumatic ejection frame according to claim 2, wherein: The length of the support rod is adjustable.

6. The pneumatic ejection frame according to claim 1, wherein: Each guide component includes: A support member disposed around a corresponding ejection gas cylinder; and Three or more guide wheels are pivotably mounted on the support member at intervals from each other along the circumference of the ejection cylinder.

7. The pneumatic ejection frame according to claim 6, wherein: The support member is a U-shaped groove, and a first guide wheel and a second guide wheel are respectively installed at the ends of two vertical walls of the U-shaped groove. A downwardly recessed portion is arranged at the bottom center of the U-shaped groove, and a third guide wheel is installed in the recessed portion.

8. The pneumatic ejection frame according to claim 1, wherein: The gas storage tank is connected to the central position of the gas connecting pipe through the gas valve.

9. The pneumatic ejection frame according to claim 1, wherein: The gas storage tank is located above the gas connecting pipe.

10. A multi-link launcher for an unmanned aerial vehicle, characterized in that: include: Base; Four pillars fixed on the base, wherein projections of the four pillars on the plane where the base is located constitute four vertices of a rectangle; as well as A plurality of pneumatic ejection frames according to claim 1 are mounted on the four pillars, the plurality of pneumatic ejection frames are spaced apart from each other in the up-down direction, and two ejection air cylinders of each pneumatic ejection frame are perpendicular to the four pillars or form a predetermined acute angle with the horizontal plane.

11. The multiple launcher according to claim 10, wherein: The plurality of pneumatic ejection racks are detachably mounted to the four struts.

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