Aircraft release device

Abstract

The present invention provides an aircraft release device, which relates to the field of aircraft. The aircraft release device provided by the present invention includes a frame, wheels and a support frame assembly, the support frame assembly includes a first support frame and a second support frame, the wheels are arranged at the bottom of the frame; the first end of the first support frame is hinged to the front end of the frame; the first support frame has a slide groove, the slide groove includes a first groove section and a second groove section that are interconnected, the first groove section and the second groove section have different extension directions, the first end of the second support frame is hinged to the rear end of the frame, and the second end of the second support frame is slidably connected to the slide groove; when the second end of the second support frame is in the second groove section, the second support frame and the first support frame are locked with each other; when the first support frame releases the aircraft, the second end of the second support frame slides from the second groove section into the first groove section under inertia, so that the second support frame and the first support frame are unlocked and dumped together. The present invention provides an aircraft release device with high safety.

Description

Technical Field

[0001] The present invention relates to the field of aircraft, and in particular to an aircraft releasing device. Background Art

[0002] The research on drone take-off and landing technology has always been a hot topic in the military and civilian fields. Compared with traditional take-off and landing methods, the technology of accelerating drones through an acceleration release device and then releasing them for take-off does not need to rely on dedicated runways. It can participate in emergency and airborne missions more quickly and improves deployment flexibility.

[0003] In the prior art, an acceleration release device is generally connected to a drone, which accelerates the drone to a certain speed and then decelerates. The inertia generated at the moment of deceleration causes the drone to separate from the acceleration release device, thereby enabling the drone to be released and take off.

[0004] However, existing accelerated release devices are prone to interfere with components such as the mount, landing gear, and propeller under the drone fuselage when the drone is released, posing a safety hazard. Summary of the Invention

[0005] In order to solve at least one of the problems mentioned in the background technology, the present invention provides an aircraft release device with high safety.

[0006] In order to achieve the above object, the present invention provides the following technical solutions:

[0007] The present invention provides an aircraft release device, comprising a frame, wheels, and a support frame assembly, wherein the support frame assembly comprises a first support frame and a second support frame, and the wheels are arranged at the bottom of the frame, and are configured to drive the frame to move along an aircraft release track;

[0008] The first end of the first support frame is hinged to the front end of the vehicle frame, and the second end of the first support frame is configured to be hung with the aircraft; the first support frame has a slide groove, which includes a first groove section and a second groove section that are connected to each other, and the first groove section and the second groove section extend in different directions; the first end of the second support frame is hinged to the rear end of the vehicle frame, and the second end of the second support frame is slidably connected to the slide groove; when the second end of the second support frame is in the second groove section, the second support frame and the first support frame are locked with each other, so that the support frame assembly is in a supporting state, wherein the front-to-back direction of the vehicle frame is consistent with the release direction of the aircraft;

[0009] When the first support frame releases the aircraft, the second end of the second support frame slides from the second slot section into the first slot section under the inertia of the second support frame relative to the vehicle frame, so that the second support frame and the first support frame are unlocked and tilted together.

[0010] As an optional embodiment, the first end of the second slot segment is connected to a side of the first slot segment close to the second end of the first support frame, and the second end of the second slot segment extends toward the front end of the vehicle frame.

[0011] As an optional implementation, the connection between the first slot segment and the second slot segment is an arc surface.

[0012] As an optional embodiment, the first support frame includes two first support arms, the first ends of the two first support arms are respectively hinged to opposite sides of the width direction of the frame, and the second ends of the two first support arms have a hanging portion, and the hanging portions on the two first support arms are configured to be hung together with the aircraft, wherein the width direction is perpendicular to the front-rear direction of the frame.

[0013] As an optional embodiment, the second support frame includes two second support arms and a connecting arm connected between the two second support arms, the first ends of the two second support arms are respectively hinged to the opposite sides in the width direction of the frame, and the second ends of the two second support arms are respectively slidably connected to the sliding grooves on the two first support arms.

[0014] As an optional embodiment, it also includes an elastic tensioning member, which is connected between the vehicle frame and the second support frame. When the first support frame releases the aircraft, the second end of the second support frame slides down along the first groove section under the tension of the elastic tensioning member, so that the first support frame and the second support frame tilt together in opposite directions.

[0015] As an optional embodiment, the elastic tensioning member includes a spring and a first hanging ear, the first hanging ear is rotatably connected to the connecting arm, the first end of the spring is connected to the first hanging ear, and the second end of the spring is connected to the frame.

[0016] As an optional embodiment, it also includes an adjustment component, which includes a screw rod and a second lug. The screw rod is arranged on the frame, and the screw rod extends along the front and rear direction of the frame. The screw rod is located between the first end of the first support arm and the first end of the second support arm. The second lug is threadedly connected to the screw rod, and the second end of the spring is connected to the second lug to adjust the stretching length of the spring by adjusting the position of the second lug on the screw rod.

[0017] As an optional embodiment, a buffer is further included. The buffer is arranged on the vehicle frame and is used to buffer the second end of the first support frame after it is tilted.

[0018] As an optional embodiment, a counterweight is further included, which is arranged on the first support arm, and the counterweight and the second slot section are arranged opposite to each other along the width direction of the first support arm.

[0019] The aircraft release device provided by the present invention includes a vehicle frame, wheels and a support frame assembly, the support frame assembly including a first support frame and a second support frame, the wheels are arranged at the bottom of the vehicle frame, and the wheels are configured to drive the vehicle frame to move along the aircraft release track; the first end of the first support frame is hinged to the front end of the vehicle frame, and the second end of the first support frame is configured to be hung together with the aircraft; the first support frame has a slide groove, which includes a first groove section and a second groove section that are interconnected, and the first groove section and the second groove section extend in different directions; the first end of the second support frame is hinged to the rear end of the vehicle frame, and the second end of the second support frame is slidably connected to the slide groove; when the second end of the second support frame is in the second groove section, the second support frame and the first support frame are locked with each other, so that the support frame assembly is in a supporting state, wherein the front-to-back direction of the vehicle frame is consistent with the release direction of the aircraft; when the first support frame releases the aircraft, the second end of the second support frame slides from the second groove section into the first groove section under the action of its own inertia relative to the vehicle frame, so that the second support frame and the first support frame are unlocked and tilted together.

[0020] When releasing the aircraft, the aircraft release device provided by the present invention can be first placed on the aircraft release track, and the second end of the second support frame can be slid along the slide groove on the first support frame into the second groove section to lock the relative positions of the second support frame and the first support frame, so that the second end of the first support frame is lifted to the same height as the hanging point on the aircraft, which is convenient for hanging the aircraft and the second end of the first support frame; after the aircraft is hung, a forward force can be applied to the release device to accelerate the release device along the track, and when the release device is accelerated to the required speed, the release device can be pressed When the force applied toward the rear is applied, the release device starts to perform a deceleration movement. At the moment of deceleration, the hanging point of the aircraft will separate from the first support frame under inertia. At the same time, the second end of the second support frame will slide from the second groove section into the first groove section under the action of inertia, so that the first support frame and the second support frame are unlocked. After the second end of the second support frame enters the first groove section, it will slide down along the first groove section, thereby causing the second support frame to tilt to one side. The tilting of the second support frame will drive the first support frame to tilt together, so as to facilitate the aircraft to fly over the releasing device, avoid interference with the support frame assembly when the aircraft is released, and improve the safety of the aircraft when released. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative labor.

[0022] Figure 1A schematic diagram of the overall structure of an aircraft release device provided in an embodiment of the present invention;

[0023] Figure 2 A schematic structural diagram of a first support frame in an aircraft release device provided in an embodiment of the present invention;

[0024] Figure 3 A schematic structural diagram of a second support frame in an aircraft release device provided in an embodiment of the present invention;

[0025] Figure 4 A partially enlarged schematic diagram of an aircraft release device provided by an embodiment of the present invention;

[0026] Figure 5 A schematic diagram of a second support frame in an aircraft release device provided by an embodiment of the present invention when located in a second slot section;

[0027] Figure 6 A schematic diagram of an aircraft release device provided by an embodiment of the present invention being attached to an aircraft.

[0028] Description of reference numerals:

[0029] 100-Release device;

[0030] 110-frame;

[0031] 120-wheel;

[0032] 130-first support frame;

[0033] 131-chute;

[0034] 1311-first slot section;

[0035] 1312-second slot section;

[0036] 132-hook-up part;

[0037] 140- second support frame;

[0038] 141- second support arm;

[0039] 142-connecting arm;

[0040] 150-elastic tensioning member;

[0041] 151-spring;

[0042] 152-first mounting ear;

[0043] 160-adjustment component;

[0044] 161-screw;

[0045] 162-second mounting ear;

[0046] 170-buffer;

[0047] 180-Counterweight;

[0048] 200-track;

[0049] 300-Aircraft. DETAILED DESCRIPTION

[0050] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0051] In this application, terms such as "upper," "lower," "left," "right," "front," "back," "top," "bottom," "inner," "outer," "vertical," "horizontal," "transverse," and "longitudinal" indicate positions or locations based on the positions or locations shown in the accompanying drawings. These terms are primarily intended to better describe the present invention and its embodiments and are not intended to limit the devices, elements, or components indicated to having a specific orientation, or to being constructed or operated in a specific orientation.

[0052] Furthermore, some of the above terms may be used to express other meanings besides indicating a position or location. For example, the term "on" may also be used to indicate a dependency or connection in certain circumstances. Those skilled in the art will understand the specific meanings of these terms in the present invention based on the specific circumstances.

[0053] Furthermore, the terms "installed," "disposed," "provided with," "connected," and "connected" should be interpreted broadly. For example, they can refer to fixed connections, removable connections, or integral structures; mechanical connections or electrical connections; direct connections or indirect connections through an intermediary; or internal communication between two devices, elements, or components. Those skilled in the art will understand the specific meanings of these terms in the present invention based on specific circumstances.

[0054] Furthermore, the terms "first," "second," and the like are primarily used to distinguish between different devices, elements, or components (which may or may not be of the same type and configuration), and are not intended to indicate or imply the relative importance or quantity of the devices, elements, or components indicated. Unless otherwise specified, "plurality" means two or more.

[0055] In existing technology, drone acceleration release devices are typically connected to the drone. The device accelerates the drone to a certain speed and then decelerates it. The inertia generated during deceleration causes the drone to separate from the device, allowing the drone to be released and launched. However, existing acceleration release devices can easily interfere with components such as the drone's mounts, landing gear, and propellers during release, posing a safety hazard.

[0056] In view of this, the present invention provides an aircraft releasing device, comprising a frame, wheels and a support frame assembly, the support frame assembly comprising a first support frame and a second support frame, the wheels being arranged at the bottom of the frame; the first end of the first support frame is hinged to the front end of the frame; the first support frame has a slide groove, the slide groove comprises a first groove section and a second groove section that are interconnected, the extension directions of the first groove section and the second groove section are different, the first end of the second support frame is hinged to the rear end of the frame, and the second end of the second support frame is slidably connected to the slide groove; when the second end of the second support frame is in the second groove section, the second support frame and the first support frame are locked with each other, so that the support frame assembly is in a supporting state; when the first support frame releases the aircraft, the second end of the second support frame slides from the second groove section into the first groove section under inertia, so that the second support frame and the first support frame are unlocked and dumped together.

[0057] When releasing the aircraft, the aircraft release device provided by the present invention can be first placed on the aircraft release track, and the second end of the second support frame can be slid along the slide groove on the first support frame into the second groove section to lock the relative positions of the second support frame and the first support frame, so that the second end of the first support frame is lifted to the same height as the hanging point on the aircraft, which is convenient for hanging the aircraft and the second end of the first support frame; after the aircraft is hung, a force can be applied to the release device in the forward direction to accelerate the release device along the track. When the release device accelerates to the required speed, A rearward force can be applied to the release device, and the release device starts to perform a deceleration movement. At the moment of deceleration, the hanging point of the aircraft will separate from the first support frame under inertia. At the same time, the second end of the second support frame will slide from the second groove section into the first groove section under the action of inertia, so that the first support frame and the second support frame are unlocked. After the second end of the second support frame enters the first groove section, it will slide down along the first groove section, thereby causing the second support frame to tilt to one side. The tilting of the second support frame will drive the first support frame to tilt together, avoiding interference with the support frame assembly when the aircraft is released, thereby improving the safety of the aircraft when released.

[0058] Figure 1 A schematic diagram of the overall structure of an aircraft release device provided in an embodiment of the present invention; Figure 2 A schematic structural diagram of a first support frame in an aircraft release device provided in an embodiment of the present invention; Figure 3A schematic structural diagram of a second support frame in an aircraft release device provided in an embodiment of the present invention;

[0059] Figure 4 A partially enlarged schematic diagram of an aircraft release device provided by an embodiment of the present invention; Figure 5 A schematic diagram of a second support frame in an aircraft release device provided by an embodiment of the present invention when located in a second slot section; Figure 6 A schematic diagram of an aircraft release device provided by an embodiment of the present invention being attached to an aircraft.

[0060] You can refer to Figures 1 to 6 The embodiment of the present invention provides an aircraft release device 100, including a frame 110, wheels 120 and a support frame assembly, the support frame assembly including a first support frame 130 and a second support frame 140, the wheels 120 are arranged at the bottom of the frame 110, and the wheels 120 are configured to drive the frame 110 to move along the release track 200 of the aircraft 300; the first end of the first support frame 130 is hinged to the front end of the frame 110, and the second end of the first support frame 130 is configured to be hung together with the aircraft 300; the first support frame 130 has a slide 131, and the slide 131 includes a first groove section 1311 and a second groove section 1312 that are connected to each other, and the extension direction of the first groove section 1311 and the second groove section 1312 is In different directions, the first end of the second support frame 140 is hinged to the rear end of the vehicle frame 110, and the second end of the second support frame 140 is slidably connected to the slide groove 131; when the second end of the second support frame 140 is in the second groove section 1312, the second support frame 140 and the first support frame 130 are locked with each other, so that the support frame assembly is in a supporting state, wherein the front and rear direction of the vehicle frame 110 is consistent with the release direction of the aircraft 300; when the first support frame 130 releases the aircraft 300, the second end of the second support frame 140 slides from the second groove section 1312 into the first groove section 1311 under the action of its own inertia relative to the vehicle frame 110, so that the second support frame 140 and the first support frame 130 are unlocked and tilted together.

[0061] When releasing the aircraft 300, the aircraft release device 100 provided in the embodiment of the present invention can be first placed on the release track 200 of the aircraft 300, and the second end of the second support frame 140 can be slid along the slide groove 131 on the first support frame 130 into the second groove section 1312 to lock the relative positions of the second support frame 140 and the first support frame 130, so that the second end of the first support frame 130 is lifted to the same height as the hanging point on the aircraft 300, which is convenient for hanging the aircraft 300 and the second end of the first support frame 130; after the aircraft 300 is hung, a forward force can be applied to the release device 100 to accelerate the release device 100 along the track 200. When the release device 100 is accelerated to the required speed, the release device 100 can be released. 00 applies a force toward the rear, and the release device 100 starts to decelerate. At the moment of deceleration, the hanging point of the aircraft 300 will separate from the first support frame 130 under inertia. At the same time, the second end of the second support frame 140 will slide from the second groove section 1312 into the first groove section 1311 under the action of inertia, so that the first support frame 130 and the second support frame 140 are unlocked. After the second end of the second support frame 140 enters the first groove section 1311, it will slide down along the first groove section 1311, thereby causing the second support frame 140 to tilt to one side. The tilting of the second support frame 140 will drive the first support frame 130 to tilt together, so as to facilitate the aircraft 300 to fly over the release device 100, avoid interference between the aircraft 300 and the support frame assembly when being released, and improve the safety of the aircraft 300 when being released.

[0062] like Figure 5 As shown, it can be understood that when the second end of the second support frame 140 is locked in the second groove section 1312 of the slide groove 131, the first support frame 130 and the second support frame 140 can both be in an inclined state. In this way, when the second end of the second support frame 140 slides into the first groove section 1311, the second end of the second support frame 140 can slide down along the first groove section 1311 under the action of its own gravity, thereby causing the first support frame 130 and the second support frame 140 to fall down at the same time.

[0063] like Figure 2 As shown, in the above embodiment, the first end of the second slot section 1312 can be connected to the side of the first slot section 1311 near the second end of the first support frame 130, and the second end of the second slot section 1312 can extend toward the front end of the vehicle frame 110. It can be understood that when the release device 100 decelerates, the second end of the second support frame 140 can slide from the first end of the second slot section 1312 into the first slot section 1311 under inertia, thereby unlocking the first support frame 130 and the second support frame 140. The first slot section 1311 can be an elongated strip as a whole and extend along the height direction of the first support frame 130.

[0064] In the above embodiment, the connection between the first slot section 1311 and the second slot section 1312 is an arc surface. Setting the connection between the first slot section 1311 and the second slot section 1312 as an arc section makes the transition between the first slot section 1311 and the second slot section 1312 smoother, facilitating the second end of the second support frame 140 to slide from the second slot section 1312 into the first slot section 1311, and avoiding jamming and difficulty when the second end of the second support frame 140 slides from the second slot section 1312 into the first slot section 1311, thereby affecting the tilting action of the first support frame 130 and the second support frame 140.

[0065] In the above embodiment, the first support frame 130 may include two first support arms, wherein the first ends of the two first support arms are hingedly connected to opposite sides of the vehicle frame 110 in the width direction, and the second ends of the two first support arms each have a hooking portion 132. The hooking portions 132 on the two first support arms are configured to be hooked to the aircraft 300, wherein the width direction is perpendicular to the front-to-back direction of the vehicle frame 110. Hooking the aircraft 300 via the two first support arms can, on the one hand, improve the reliability of the hooking between the aircraft 300 and the release device 100, ensuring that the aircraft 300 moves stably under the traction of the release device 100, and on the other hand, simplify the structure of the first support frame 130, reduce the space occupied by the first support frame 130, and further reduce the possibility of interference between the first support frame 130 and the aircraft 300.

[0066] like Figure 3 As shown, in the above embodiment, the second support frame 140 may include two second support arms 141 and a connecting arm 142 connected between the two second support arms 141. The first ends of the two second support arms 141 are respectively hinged to opposite sides of the width direction of the vehicle frame 110, and the second ends of the two second support arms 141 are respectively slidably connected to the slide slots 131 on the two first support arms. This simplifies the structure of the second support frame 140, reduces the space occupied by the second support frame 140, and further reduces the possibility of interference between the second support frame 140 and the aircraft 300.

[0067] The above embodiment may further include an elastic tensioning member 150 connected between the vehicle frame 110 and the second support frame 140. When the first support frame 130 releases the aircraft 300, the second end of the second support frame 140 slides down the first groove section 1311 under the tension of the elastic tensioning member 150, causing the first support frame 130 and the second support frame 140 to fall together in opposite directions. It is understood that when the second end of the second support frame 140 slides from the second groove section 1312 into the first groove section 1311 under the action of inertia, the second support frame 140 can quickly slide down the first groove section 1311 under the tension of the elastic tensioning member 150, thereby increasing the speed at which the second support frame 140 and the first support frame 130 fall, further reducing the possibility of interference between the aircraft 300 and the first support frame 130 and the second support frame 140. Furthermore, the provision of the elastic tensioning member 150 can also restrain the second support frame 140 after it falls, preventing it from rebounding.

[0068] Specifically, one end of the elastic tensioning member 150 may be connected to the connecting arm 142 on the second support frame 140 , so that the force exerted by the elastic tensioning member 150 on the second support frame 140 is more uniform.

[0069] like Figure 4 As shown, in the above embodiment, the elastic tensioning member 150 may include a spring 151 and a first hanging ear 152, the first hanging ear 152 is rotatably connected to the connecting arm 142, the first end of the spring 151 is connected to the first hanging ear 152, and the second end of the spring 151 is connected to the frame 110. It can be understood that when the second support frame 140 falls, the spring 151 will rotate relative to the second support frame 140 to a certain extent. By providing the hanging ear, the spring 151 and the second support frame 140 can be prevented from rotating relative to each other.

[0070] like Figure 4 As shown, the above embodiment may further include an adjustment assembly 160, which includes a screw rod 161 and a second lug 162. The screw rod 161 is disposed on the vehicle frame 110 and extends in the front-to-rear direction of the vehicle frame 110. The screw rod 161 is located between the first end of the first support arm and the first end of the second support arm 141. The second lug 162 is threadedly connected to the screw rod 161, and the second end of the spring 151 is connected to the second lug 162. The tension length of the spring 151 can be adjusted by adjusting the position of the second lug 162 on the screw rod 161. It can be understood that when the second lug 162 moves along the screw rod 161, the length and tension direction of the elastic tension member 150 change accordingly, thereby varying the tension magnitude and tension direction of the elastic tension member 150 within a certain range, making the release device 100 of this embodiment applicable to a wider range of working conditions.

[0071] The above embodiment may further include a buffer member 170, which is disposed on the vehicle frame 110 and is used to cushion the second end of the first support frame 130 after it has fallen. The provision of the buffer member 170 allows the first support frame 130 and the second support frame 140 to act on the surface of the buffer member 170 after they have fallen, thereby quickly absorbing the impact of the first support frame 130 and the second support frame 140 falling. This not only protects the first support frame 130 and the second support frame 140, but also prevents the first support frame 130 and the second support frame 140 from rebounding after they have fallen.

[0072] The above embodiment may further include a counterweight 180, which is disposed on the first support arm and is disposed opposite the second slot section 1312 along the width direction of the first support arm. The provision of the counterweight 180 increases the mass of the first support frame 130, thereby increasing the inertia of the first support frame 130, making it easier for the second end of the second support frame 140 to enter the first slot section 1311 from the second slot section 1312.

[0073] The aircraft release device 100 provided in an embodiment of the present invention includes a frame 110, wheels 120 and a support frame assembly, the support frame assembly includes a first support frame 130 and a second support frame 140, the wheels 120 are arranged at the bottom of the frame 110, and the wheels 120 are configured to drive the frame 110 to move along the release track 200 of the aircraft 300; the first end of the first support frame 130 is hinged to the front end of the frame 110, and the second end of the first support frame 130 is configured to be hung together with the aircraft 300; the first support frame 130 has a slide 131, and the slide 131 includes a first groove section 1311 and a second groove section 1312 that are connected to each other, and the extension direction of the first groove section 1311 and the second groove section 1312 is Differently, the first end of the second support frame 140 is hinged to the rear end of the vehicle frame 110, and the second end of the second support frame 140 is slidably connected to the slide groove 131; when the second end of the second support frame 140 is in the second groove section 1312, the second support frame 140 and the first support frame 130 are locked with each other, so that the support frame assembly is in a supporting state, wherein the front and rear direction of the vehicle frame 110 is consistent with the release direction of the aircraft 300; when the first support frame 130 releases the aircraft 300, the second end of the second support frame 140 slides from the second groove section 1312 into the first groove section 1311 under the action of its own inertia relative to the vehicle frame 110, so that the second support frame 140 and the first support frame 130 are unlocked and tilted together.

[0074] When releasing the aircraft 300, the aircraft release device 100 provided in the embodiment of the present invention can be first placed on the release track 200 of the aircraft 300, and the second end of the second support frame 140 can be slid along the slide groove 131 on the first support frame 130 into the second groove section 1312 to lock the relative positions of the second support frame 140 and the first support frame 130, so that the second end of the first support frame 130 is lifted to the same height as the hanging point on the aircraft 300, which is convenient for hanging the aircraft 300 and the second end of the first support frame 130; after the aircraft 300 is hung, a forward force can be applied to the release device 100 to accelerate the release device 100 along the track 200. When the release device 100 is accelerated to the required speed, the release device 100 can be released. 00 applies a force toward the rear, and the release device 100 starts to decelerate. At the moment of deceleration, the hanging point of the aircraft 300 will separate from the first support frame 130 under inertia. At the same time, the second end of the second support frame 140 will slide from the second groove section 1312 into the first groove section 1311 under the action of inertia, so that the first support frame 130 and the second support frame 140 are unlocked. After the second end of the second support frame 140 enters the first groove section 1311, it will slide down along the first groove section 1311, thereby causing the second support frame 140 to tilt to one side. The tilting of the second support frame 140 will drive the first support frame 130 to tilt together, so as to facilitate the aircraft 300 to fly over the release device 100, avoid interference between the aircraft 300 and the support frame assembly when being released, and improve the safety of the aircraft 300 when being released.

[0075] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the above embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. An aircraft release device, characterized in that: The vehicle comprises a frame, wheels, a support frame assembly and an elastic tensioning member, wherein the support frame assembly comprises a first support frame and a second support frame, the wheels are arranged at the bottom of the frame, and the wheels are configured to drive the frame to move along the aircraft release track; The first end of the first support frame is hinged to the front end of the vehicle frame, and the second end of the first support frame is configured to be hung together with the aircraft; the first support frame has a slide groove, and the slide groove includes a first groove section and a second groove section that are connected to each other, and the first groove section and the second groove section extend in different directions; the first end of the second support frame is hinged to the rear end of the vehicle frame, and the second end of the second support frame is slidably connected to the slide groove; When the second end of the second support frame is in the second slot section, the second support frame and the first support frame are locked to each other so that the support frame assembly is in a supporting state, wherein the front-to-back direction of the vehicle frame is consistent with the release direction of the aircraft; When the first support frame releases the aircraft, the second end of the second support frame slides from the second groove section into the first groove section under the action of its own inertia relative to the vehicle frame, so that the second support frame and the first support frame are unlocked and tilted together; The first support frame includes two first support arms, the second support frame includes two second support arms and a connecting arm connected between the two second support arms, the first ends of the two second support arms are respectively hinged to opposite sides of the width direction of the frame, and the second ends of the two second support arms are respectively slidably connected to the sliding grooves on the two first support arms; The elastic tensioning member is connected between the vehicle frame and the second support frame. When the first support frame releases the aircraft, the second end of the second support frame slides down along the first groove section under the tension of the elastic tensioning member, so that the first support frame and the second support frame tilt together in opposite directions.

2. The aircraft release device according to claim 1, characterized in that: The first end of the second slot section is communicated with a side of the first slot section close to the second end of the first support frame, and the second end of the second slot section extends toward the front end of the vehicle frame.

3. The aircraft release device according to claim 2, characterized in that: The connection between the first slot section and the second slot section is an arc surface.

4. The aircraft release device according to claim 3, characterized in that: The first ends of the two first support arms are respectively hinged to opposite sides of the frame in the width direction, and the second ends of the two first support arms have a hanging portion, and the hanging portions on the two first support arms are configured to be hung together with the aircraft, wherein the width direction is perpendicular to the front-to-back direction of the frame.

5. The aircraft release device according to claim 4, characterized in that: The elastic tensioning member includes a spring and a first hanging ear, the first hanging ear is rotatably connected to the connecting arm, the first end of the spring is connected to the first hanging ear, and the second end of the spring is connected to the frame.

6. The aircraft release device according to claim 5, characterized in that: The yoke is secured to the chassis and has a pivotal position about the first support arm and the second support arm, and the yoke is secured to the chassis and has a pivotal position about the first support arm. The yoke is secured to the chassis and has a pivotal position about the first support arm. The yoke is secured to the chassis and has a pivotal position about the first support arm.

7. The aircraft release device according to claim 6, characterized in that: It also includes a buffer component, which is arranged on the vehicle frame and is used to buffer the second end of the first support frame after it is tilted.

8. The aircraft release device according to claim 7, characterized in that: It also includes a counterweight, which is arranged on the first support arm, and the counterweight and the second slot section are arranged opposite to each other along the width direction of the first support arm.

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