UAV launch fixture

Abstract

The present invention discloses a UAV launching and fixing device, comprising a UAV fixing frame, a support plate, a locking seat, a rotating shaft A, a pin shaft B, a pin shaft and an elastic reset part of the support plate, a pin shaft limiting slot is provided on the locking seat, the UAV fixing frame comprises a left baffle, a right baffle and a bottom plate, a support plate groove is provided on the bottom plate, the lower end of the left baffle and the lower end of the right baffle are fixedly connected to the bottom plate, a rotating shaft limiting slide groove is provided in the middle of the left baffle and the right baffle, the rotating shaft limiting slide groove is a V-shaped groove composed of a recovery positioning groove and a protruding positioning slot, the front end of the support plate is rotatably connected to the rotating shaft A, the middle part is fixedly connected to the pin shaft B, and the rear end is fixedly connected to the pin shaft, the rotating shaft A is connected to the left baffle and the right baffle, the pin shaft B extends out of the rotating shaft limiting slide groove, the pin shaft B is tightly fitted with the protruding positioning slot, and the pin shaft is tightly fitted with the pin shaft limiting slot. The present invention has the advantages of good UAV supporting effect, high launching safety, and the ability to avoid excessive resistance.

Description

Technical Field

[0001] The present invention relates to the technical field of rocket-propelled UAV launch, in particular to a UAV launch fixing device. Background Art

[0002] In drone launches, rocket-assisted launches have the advantages of high efficiency, little damage to the aircraft, no site requirements, and maneuverability, and are widely used.

[0003] In the prior art, a launch frame is usually used to restrain and support UAVs. After searching, CN2019304086096 discloses a launch frame (for UAV rocket propulsion), which supports the UAV in a four-point fixing manner. Support rods are set on the left and right sides of the front end and the left and right sides of the rear end of the launch frame to support the UAV. Shear pins are set on the front support rods to achieve the separation of the UAV from the launch frame. The rear end support rods are provided with a slide, and the UAV slides out along the slide. CN2016112281876 discloses a rocket-assisted high-speed UAV launching mechanism, which supports the UAV in a three-point fixing manner. Support rods are set on the front middle part and the left and right sides of the rear end of the launch frame to support the UAV. Shear pins are set on the front middle support rods to achieve the separation of the UAV from the launch frame. The rear end support rods are provided with a slide, and the UAV slides out along the slide.

[0004] The shortcomings of the existing structure are: when the rocket is ignited, the shear pin is cut off, the drone is unconstrained, slides out along the slide, and takes off smoothly under the action of the rocket thrust. Using this support method, the shear force of the shear pin and the contact friction between the drone and the launch pad during launch are difficult to assess. If the assessment is inaccurate, the risk factor generated during launch will show a significant upward trend as the use time increases. Summary of the Invention

[0005] The purpose of the present invention is to solve the deficiencies of the above-mentioned prior art and to provide a UAV launch and fixing device with a simple structure, good UAV support effect, high launch safety, strong reliability, and the ability to avoid excessive resistance and radar reflection area during flight.

[0006] The technical solution adopted by the present invention to solve its technical problem is:

[0007] A UAV launch and fixing device, characterized in that it includes a UAV fixing frame fixed to the tail and belly of the UAV, a support plate, a locking seat fixed to the launch frame, a rotating shaft A, a pin shaft B, a pin shaft and an elastic reset portion of the support plate, the locking seat is provided with a pin shaft limiting slot with an opening facing the front side of the aircraft, the UAV fixing frame includes a left baffle, a right baffle and a bottom plate, the bottom plate is provided with a support plate groove for the support plate to extend or retract, the left baffle and the right baffle are arranged opposite to each other on both sides of the support plate groove, the lower end of the left baffle and the right baffle are opposite to each other, and the lower end of the left baffle and the right baffle are opposite to each other. The lower ends of the baffles are fixedly connected to the bottom plate, and the middle parts of the left and right baffles are symmetrically provided with shaft limiting slides that cooperate with the pin shaft B. The shaft limiting slides are V-shaped grooves composed of a recovery positioning groove and an extended positioning slot. The recovery positioning groove is connected to the extended positioning slot. A support plate is provided between the left and right baffles. The front end of the support plate is rotatably connected to the shaft A, the middle part is fixedly connected to the pin shaft B, and the rear end is fixedly connected to the pin shaft. The left end of the shaft A is connected to the left baffle, and the right end is connected to the right baffle. The left end of the pin shaft B extends out of the rotating shaft limiting slot on the left baffle, and the right end extends out of the rotating shaft limiting slot on the right baffle. When the support plate is extended, the pin shaft B is tightly fitted with the extended positioning slot, and the pin shaft is tightly fitted with the pin shaft limiting slot. When the support plate is retracted, the pin shaft is disengaged from the pin shaft limiting slot, and the pin shaft B is driven back to the recovery positioning slot by the elastic reset part of the support plate. The support plate is rotated out of the UAV fixing frame, and is limited by the pin shaft and the pin shaft limiting slot on the launch frame. When the support plate is extended, the pin shaft B is clamped in the extended positioning slot. , to limit the support plate and ensure the stability of the support plate in supporting the drone. When the drone takes off, under the action of rocket boost, the pin shaft disengages from the pin shaft limiting slot, thereby realizing the smooth launch of the drone. No shear pin is required and no relative friction is generated. The drone launch is highly safe. After the pin shaft disengages from the pin shaft limiting slot, the support plate is retracted between the left baffle and the right baffle through the support plate groove under the action of the support plate elastic reset part, which can avoid excessive resistance and radar reflection area value caused by the extension of the support plate during the flight of the drone.

[0008] The elastic reset part of the support plate described in the present invention includes a torsion spring shaft, a torsion spring pressure shaft, and a torsion spring. The torsion spring pressure shaft is arranged on the front side of the pin shaft B, the left end is connected to the left baffle, and the right end is connected to the right baffle. The torsion spring shaft is arranged between the torsion spring pressure shaft and the pin shaft B, the left end is connected to the left baffle, and the right end is connected to the right baffle. A torsion spring is sleeved on the torsion spring shaft, the front end torsion arm of the torsion spring is in conflict with the torsion spring pressure shaft, and the rear end torsion arm is in conflict with the pin shaft B. By setting the torsion spring, when the pin shaft disengages from the pin shaft limiting slot, the rear end of the support plate has no supporting force, and the pin shaft B comes out of the extending positioning slot and enters the recovery positioning slot under the elastic force of the torsion spring, thereby realizing the retraction of the support plate from the support plate groove.

[0009] The torsion spring shaft of the present invention includes a left torsion spring shaft and a right torsion spring shaft, the torsion spring pressure shaft includes a left torsion spring pressure shaft and a right torsion spring pressure shaft, the torsion spring includes a left torsion spring and a right torsion spring, the inner side of the left baffle is provided with a left inner baffle, the inner side of the right baffle is provided with a right inner baffle, the left inner baffle and the right inner baffle are arranged opposite to each other on both sides of the support plate groove, the lower end of the left inner baffle and the lower end of the right inner baffle are fixedly connected to the bottom plate respectively, the left inner baffle and the right inner baffle are symmetrically provided with a rotating shaft limiting slide groove, the support plate is arranged between the left inner baffle and the right inner baffle, the left end of the rotating shaft A passes through the left inner baffle and is connected to the left baffle, and the right end passes through the right inner baffle. The left end of the pin shaft B passes through the left inner baffle and the rotating shaft limiting slide groove on the left baffle in sequence, and the right end passes through the right inner baffle and the rotating shaft limiting slide groove on the right baffle in sequence. The left torsion spring shaft and the left torsion spring pressure shaft are arranged between the left baffle and the left inner baffle and are located in front of the pin shaft B. The left end of the left torsion spring pressure shaft is connected to the left baffle, and the right end is connected to the left inner baffle. The left torsion spring shaft is arranged between the left torsion spring pressure shaft and the pin shaft B, the left end is connected to the left baffle, and the right end is connected to the left inner baffle. The left torsion spring shaft is sleeved with a left torsion spring, the front end torsion arm of the left torsion spring conflicts with the left torsion spring pressure shaft, and the rear end torsion arm conflicts with the pin shaft B;

[0010] The right torsion spring shaft and the right torsion spring pressure shaft are arranged between the right baffle and the right inner baffle and are located in front of the pin shaft B. The right torsion spring pressure shaft and the left torsion spring pressure shaft are symmetrically arranged. The right end of the right torsion spring pressure shaft is connected to the right baffle, and the left end is connected to the right inner baffle. The right torsion spring shaft is arranged between the right torsion spring pressure shaft and the pin shaft B and is symmetrically arranged to the left torsion spring shaft. The right end of the right torsion spring shaft is connected to the right baffle, and the left end is connected to the right inner baffle. The right torsion spring shaft is sleeved with a right torsion spring, and the front end torsion spring of the right torsion spring The arm conflicts with the right torsion spring pressure shaft, and the rear end torsion arm conflicts with the pin shaft B. By arranging the support plate between the left inner baffle and the right inner baffle, the left torsion spring is arranged between the left baffle and the left inner baffle, and the right torsion spring is arranged between the right baffle and the right inner baffle, it can prevent the support plate from shaking left and right without affecting the recovery of the support plate. Through the joint action of the left torsion spring and the right torsion spring, the pin shaft B can smoothly escape from the extending positioning slot and enter the recovery positioning slot, the support plate recovery effect is good, and the structural layout is compact and reasonable.

[0011] The extending positioning slot of the present invention is located in the front side of the recovery positioning slot, and the lower end of the extending positioning slot is connected to the lower end of the recovery positioning slot. By arranging the extending positioning slot in the front side of the recovery positioning slot, it is ensured that when the pin shaft B is stuck in the extending positioning slot, the support plate is in an extended state.

[0012] The connection between the extending positioning slot and the recovering positioning slot of the present invention is in an arc-shaped smooth transition connection, so that under the action of the torsion spring, the pin B can smoothly escape from the extending positioning slot and enter the recovering positioning slot.

[0013] The shaft hole that matches the support plate and the rotating shaft A of the present invention is a long strip hole to ensure that the support plate can be smoothly rotated out of the support plate groove, so that the pin B is stuck in the extended positioning slot and the pin is stuck in the pin limit slot.

[0014] The position height of the pin shaft B on the support plate of the present invention is higher than the position height of the rotating shaft A, so that the support plate can smoothly extend from the support plate groove, and the pin shaft B is stuck in the extending positioning slot.

[0015] The groove wall of the pin shaft limiting groove of the present invention is an inclined surface inclined outward and upward from the groove bottom. When the rocket is boosted to take off, the pin shaft slides out of the pin shaft limiting groove along the inclined surface, so that when the UAV takes off, the pin shaft can smoothly escape from the pin shaft limiting groove.

[0016] The base plate of the present invention is provided with a pin shaft accommodating opening at the rear end of the support plate groove, and the pin shaft accommodating opening is communicated with the support plate groove. When the support plate is retracted, the pin shaft cooperates with the pin shaft accommodating opening, so that when the support plate is retracted under the action of the torsion spring, the pin shaft can also be retracted, further reducing the resistance of the drone during flight.

[0017] The rear end of the support plate described in the present invention is protruded with a presser foot, and the base plate is provided with a presser foot accommodating opening at the rear end of the pin shaft accommodating opening. The presser foot accommodating opening is communicated with the pin shaft accommodating opening. When the support plate is retracted, the presser foot cooperates with the presser foot accommodating opening. When the drone needs to be fixed, the presser foot is pressed to rotate the support plate out of the support plate groove, which makes installation and fixation convenient. When the support plate is retracted, the presser foot can also be retracted into the presser foot accommodating opening to reduce resistance during flight.

[0018] The beneficial effects of the present invention are as follows: the support plate is rotated out of the drone fixing frame, and the pin shaft is engaged and limited with the pin shaft limiting slot on the launch frame through the pin shaft. When the support plate is extended, the pin shaft B is clamped in the extended positioning slot to limit the support plate, ensuring the stability of the support plate supporting the drone. When the drone takes off, under the action of the rocket booster, the pin shaft disengages from the pin shaft limiting slot, and the drone is launched smoothly without using a shear pin and without generating relative friction. The drone launch is safe. After the pin shaft disengages from the pin shaft limiting slot, the support plate passes through the support plate groove under the action of the support plate elastic reset part and is retracted between the left baffle and the right baffle, thereby avoiding excessive resistance and radar reflection area value generated by the extension of the support plate during the flight of the drone; by arranging the torsion spring, when the pin shaft disengages from the pin shaft limiting slot, the rear end of the support plate has no supporting force, and the pin shaft B comes out of the extended positioning slot under the elastic force of the torsion spring and slides into the top end of the recovery positioning slot, so that the support plate is retracted from the support plate groove. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1It is a schematic diagram of the overall structure of the fixing device of the present invention (support plate retracted state).

[0020] Figure 2 This is a schematic diagram of the overall structure of the fixing device of the present invention from another angle (support plate retracted state).

[0021] Figure 3 It is a schematic diagram of the overall structure of the fixing device of the present invention (support plate extended state).

[0022] Figure 4 It is a schematic diagram of the support plate structure of the present invention.

[0023] Figure 5 It is a schematic diagram of the structure of the fixing device of the present invention and the UAV.

[0024] Figure 6 It is a schematic diagram of the launch rack structure of the present invention.

[0025] Figure 7 It is a structural schematic diagram of the locking seat of the present invention.

[0026] Figure 8 It is a schematic diagram of the structure of the launcher supporting the UAV of the present invention.

[0027] Figure 1: Launcher 1, Support Base 101, Front Left Support 102, Front Right Support 103, Rear Left Vertical Beam 1041, Rear Right Vertical Beam 1042, Rear Cross Beam 1043, Fixing Device 2, UAV Fixing Frame 201, Left Baffle 2011, Right Baffle 2012, Left Inner Baffle 2013, Right Inner Baffle 2014, Bottom Plate 2015, Support Plate Groove 20151, Pin Shaft Receiving Port 20152, Presser Foot Receiving Port 20153, Support Plate 202, Axis Hole A -2021, shaft hole B-2022, shaft hole C-2023, presser foot-2024, rotating shaft A-2031, pin shaft B-2032, pin shaft-2033, rotating shaft limiting slot-204, recovery positioning slot-2041, extending positioning slot-2042, left torsion spring shaft-2051, right torsion spring shaft-2052, left torsion spring pressure shaft-2053, right torsion spring pressure shaft-2054, left torsion spring-2061, right torsion spring-2062, locking seat-207, pin shaft limiting slot-2071, inclined surface-20711. DETAILED DESCRIPTION

[0028] The present invention will be described below with reference to the accompanying drawings and embodiments.

[0029] As shown in the accompanying drawings, a UAV launch fixing device, the fixing device 2 includes a UAV fixing frame 201 fixed to the tail and belly of the UAV, a support plate 202, a locking seat 207 fixed on the launch frame, a rotating shaft A2031, a pin B2032, a pin 2033 and an elastic reset portion of the support plate, the locking seat 207 is provided with a pin limit slot 2071 with an opening toward the front side of the aircraft, the UAV fixing frame 201 includes a left baffle 2011, a right baffle 2012 and a bottom plate 2015, the bottom plate 2015 is provided with a support plate groove 20151 for the support plate 202 to extend or retract, the left baffle 2011 and the right baffle 2012 are arranged opposite to each other on both sides of the support plate groove 20151, The lower end of the left baffle 2011 and the lower end of the right baffle 2012 are fixedly connected to the bottom plate 2015, and the middle parts of the left baffle 2011 and the right baffle 2012 are symmetrically provided with a shaft limiting slide 204 that cooperates with the pin shaft B2032. The shaft limiting slide 204 is a V-shaped groove composed of a recovery positioning groove 2041 and a stretching positioning card groove 2042. The recovery positioning groove 2041 is connected to the stretching positioning card groove 2042. A support plate 202 is provided between the left baffle 2011 and the right baffle 2012. The front end of the support plate 202 is rotatably connected to the shaft A2031, the middle part is fixedly connected to the pin shaft B2032, and the rear end is fixedly connected to the pin shaft 2033. The left side of the shaft A2031 is fixedly connected to the pin shaft B2032. The left end is connected to the left baffle 2011, and the right end is connected to the right baffle 2012. The left end of the pin shaft B2032 extends out of the rotating shaft limiting slot on the left baffle 2011, and the right end extends out of the rotating shaft limiting slot on the right baffle 2012. When the support plate 202 is extended, the pin shaft B2032 is tightly matched with the extended positioning slot 2042, and the pin shaft 2033 is tightly matched with the pin shaft limiting slot 2071. When the support plate is recovered, the pin shaft 2033 is disengaged from the pin shaft limiting slot 2071, and the pin shaft B2032 is driven back into the recovery positioning slot 2041 through the elastic reset part of the support plate. The support plate 202 is rotated out of the drone fixing frame 201, and is limited by the pin shaft 2033 and the pin shaft limiting slot 2071. When the support plate is extended, the pin B moves and clamps in the shaft limiting slot 204 to limit the support plate 202, ensuring the stability of the support plate 202 in supporting the drone. When the drone takes off, under the action of the rocket boost, the pin 2033 disengages from the pin limiting slot 2071, thereby achieving a smooth launch of the drone without the need for a shear pin and without generating relative friction. The drone launch is highly safe. After the pin 2033 disengages from the pin limiting slot 2071, the support plate 202 is retracted between the left baffle 2013 and the right baffle 2014 through the support plate groove 20151 under the action of the support plate elastic reset part, thereby avoiding excessive resistance and radar reflection area value caused by the extension of the support plate during the flight of the drone.

[0030] In this embodiment, the support plate 202 is provided with an axis hole A2021, an axis hole B2022, and an axis hole C2023 from front to back, the rotating shaft A2031 cooperates with the axis hole A2021, the pin shaft B cooperates with the axis hole B2022, and the pin shaft cooperates with the axis hole C2023.

[0031] The elastic reset part of the support plate includes a torsion spring shaft, a torsion spring pressure shaft, and a torsion spring. The torsion spring pressure shaft is arranged on the front side of the pin shaft B2032, with the left end connected to the left baffle and the right end connected to the right baffle. The torsion spring shaft is arranged between the torsion spring pressure shaft and the pin shaft B, with the left end connected to the left baffle and the right end connected to the right baffle. A torsion spring is sleeved on the torsion spring shaft, and the front end torsion arm of the torsion spring is in conflict with the torsion spring pressure shaft, and the rear end torsion arm is in conflict with the pin shaft B. By setting the torsion spring, when the pin shaft disengages from the pin shaft limiting slot, the rear end of the support plate has no supporting force, and the pin shaft B comes out of the extending positioning slot and enters the recovery positioning slot under the elastic force of the torsion spring, thereby realizing the retraction of the support plate from the support plate groove.

[0032] In this embodiment, the torsion spring shaft includes a left torsion spring shaft 2051 and a right torsion spring shaft 2052, the torsion spring pressure shaft includes a left torsion spring pressure shaft 2053 and a right torsion spring pressure shaft 2054, and the torsion spring includes a left torsion spring 2061 and a right torsion spring 2062. The inner side of the left baffle 2011 is provided with a left inner baffle 2013, and the inner side of the right baffle 2012 is provided with a right inner baffle 2014. The left inner baffle 2013 and the right inner baffle 2014 are arranged opposite to each other on both sides of the support plate groove. The lower end of the left inner baffle 2013 and the lower end of the right inner baffle 2014 are fixedly connected to the bottom plate 2015 respectively. The left inner baffle 2013 and the right inner baffle 2014 are symmetrically provided with a rotating shaft limiting slide groove, and the left end of the pin shaft B2032 passes through the left inner baffle 2013 and the left baffle 2011 in sequence. The right end of the rotating shaft limiting slide passes through the rotating shaft limiting slides on the right inner baffle 2014 and the right baffle 2012 in sequence. A left torsion spring shaft 2051 and a left torsion spring pressure shaft 2053 are provided between the left inner baffle 2013 and the left baffle 2011 on the front side of the pin shaft B2032. The left end of the left torsion spring pressure shaft 2053 is connected to the left baffle 2011, and the right end is connected to the left inner baffle 2013. The left torsion spring shaft 2051 is provided between the left torsion spring pressure shaft 2053 and the pin shaft B2032, the left end is connected to the left baffle 2011, and the right end is connected to the left inner baffle 2013. A left torsion spring 2061 is sleeved on the left torsion spring shaft 2051. The front end torsion arm of the left torsion spring 2061 conflicts with the left torsion spring pressure shaft 2053, and the rear end torsion arm conflicts with the pin shaft B2032.

[0033] A right torsion spring shaft 2052 and a right torsion spring pressure shaft 2054 are provided on the front side of the pin shaft B2032 between the right inner baffle 2014 and the right baffle 2012. The right torsion spring pressure shaft 2054 is symmetrically arranged with the left torsion spring pressure shaft 2053. The right end of the right torsion spring pressure shaft 2054 is connected to the right baffle 2012, and the left end is connected to the right inner baffle 2014. The right torsion spring shaft 2052 is provided between the right torsion spring pressure shaft 2054 and the pin shaft B2032 and is symmetrically arranged with the left torsion spring shaft 2051. The right end of the right torsion spring shaft 2052 is connected to the right baffle 2012. The left end is connected to the right inner baffle 2014, and the right torsion spring shaft 2052 is sleeved with a right torsion spring 2062. The front end torsion arm of the right torsion spring 2062 conflicts with the right torsion spring pressure shaft 2054, and the rear end torsion arm conflicts with the pin shaft B2032. By setting the torsion spring, when the pin shaft 2033 disengages from the pin shaft limiting slot 1051, the rear end of the support plate 202 has no supporting force, and the pin shaft B2032 disengages from the extending positioning slot 2042 and enters the recovery positioning slot 2041 under the elastic force of the torsion spring, and the support plate 202 is retracted from the support plate groove 20151.

[0034] In this embodiment, the front end torsion arm of the left torsion spring 2061 is arranged at the lower end of the left torsion spring pressure shaft 2053 and conflicts with the left torsion spring pressure shaft 2053, the rear end torsion arm is arranged at the lower end of the pin shaft B2032 and conflicts with the pin shaft B2032, the front end torsion arm of the right torsion spring 2062 is arranged at the lower end of the right torsion spring pressure shaft 2054 and conflicts with the right torsion spring pressure shaft 2054, the rear end torsion arm is arranged at the lower end of the pin shaft B2032 and conflicts with the pin shaft B2032, after the pin shaft 2033 disengages from the pin shaft limiting slot, the pin shaft B2032 disengages from the extending positioning slot 2042 and returns to the recovery positioning slot 2041 under the action of the elastic force of the rear end torsion arm of the left torsion spring 2061 and the rear end torsion arm of the right torsion spring 2062, so that the support plate is retracted.

[0035] The extending positioning slot 2042 is located on the front side of the recovery positioning slot 2041, and the lower end of the extending positioning slot 2042 is connected to the lower end of the recovery positioning slot 2041. By arranging the extending positioning slot 2042 on the front side of the recovery positioning slot 2041, it is ensured that when the pin shaft B2032 is stuck in the extending positioning slot, the support plate is in an extended state.

[0036] The connection between the extending positioning slot 2042 and the recovery positioning slot 2041 is in an arc-shaped smooth transition connection, so that under the action of the torsion spring, the pin B2032 can smoothly escape from the extending positioning slot 2042 and enter the recovery positioning slot 2041.

[0037] The shaft hole A2021 that matches the support plate 202 and the rotating shaft A2031 is a long strip hole to ensure that the support plate can be smoothly rotated out of the support plate groove, the pin B is stuck in the rotating shaft limiting groove, and the pin is stuck in the pin limiting slot.

[0038] The height of the pin B2032 on the support plate is higher than that of the rotating shaft A2031 , so that the rear end of the support plate 202 can smoothly extend from the support plate groove 20151 , and the pin B2032 is stuck in the extending positioning slot 2042 .

[0039] The groove wall of the pin shaft limiting groove 2071 is an upward inclined surface 20711 from the bottom of the groove to the outside. When the rocket is assisted to take off, the pin shaft 2033 slides out of the pin shaft limiting groove 2071 along the inclined surface, so that when the UAV takes off, the pin shaft 2033 can smoothly disengage from the pin shaft limiting groove 2071.

[0040] A pin shaft accommodating opening 20152 is provided on the base plate 2015 at the rear end of the support plate groove 20151. The pin shaft accommodating opening 20152 is communicated with the support plate groove 20151. When the support plate is retracted, the pin shaft 2033 cooperates with the pin shaft accommodating opening 20152, so that when the support plate 202 is retracted under the action of the torsion spring, the pin shaft can also be retracted, further reducing the resistance of the drone during flight.

[0041] The rear end of the support plate is provided with a presser foot 2024, and the base plate 2015 is provided with a presser foot accommodating opening 20153 at the rear end of the pin shaft accommodating opening 20152. The presser foot accommodating opening 20153 is communicated with the pin shaft accommodating opening 20152. When the support plate is retracted, the presser foot cooperates with the presser foot accommodating opening. When the drone needs to be fixed, the presser foot is pressed to rotate the support plate out of the support plate groove, which is convenient for installation and fixation. When the support plate is retracted, the presser foot can also be retracted into the presser foot accommodating opening.

[0042] In this embodiment, Figure 6-Figure 8 As shown, the launcher 1 includes a support base 101, a front left support member 102, a front right support member 103 and a rear support frame. The front left support member 102 is fixed to the left side of the front end of the support base 101, the front right support member 103 is fixed to the right side of the front end of the support base 101, and the rear support frame is fixed to the middle of the rear end of the support base 101 to achieve three-point support for the UAV. The front left support member 102 and the front right support member 102 are used to support the left and right sides of the UAV wings, and the rear support member 103 is fixed to the middle of the rear end of the support base 101. The frame is used to cooperate with the fixing device 2 to support the tail and belly of the UAV. The rear support frame is composed of a rear left vertical beam 1041, a rear right vertical beam 1042, and a rear cross beam 1043. The lower end of the rear left vertical beam 1041 is fixedly connected to the support base 101, and the upper end is fixedly connected to the left end of the rear cross beam 1043. The lower end of the rear right vertical beam 1042 is fixedly connected to the support base 101, and the upper end is fixedly connected to the right end of the rear cross beam 1043. A locking seat 207 is fixedly connected to the rear cross beam.

[0043] When the present invention is installed:

[0044] Fix the drone fixing frame 201 on the tail and belly of the drone. At this time, the support plate 202 is in a retracted state, the rotating shaft A2031 is located at the front end of the shaft hole A2021, and the pin shaft B2032 is located at the top of the recovery positioning groove 2041. Under the elastic force of the left torsion spring 2061 and the right torsion spring 2062, the lower end surface of the support plate 202 does not leak out of the lower end surface of the base plate; install the locking seat 207 to the middle position of the rear support frame of the launcher.

[0045] When the present invention is used:

[0046] Before the rocket booster launches the drone, the drone is supported by the launch frame 1. The front left support member 102 and the front right support member 103 on the launch frame 1 support the wings on the left and right sides of the drone. The locking seat 207 on the rear support frame cooperates with the fixing device 2 to support the tail and belly of the drone. When supporting, manually press the pressure foot 2024 to rotate the support plate 202 out from between the left inner baffle 2013 and the right inner baffle 2014, and the pin 2033 moves downward from the pin accommodating port 20152. The pin 2033 on the support plate and the locking seat The pin limit slot 2071 of 207 is plugged in and fixed. At the same time, the pin B2032 moves from the recovery positioning slot 2041 to the extension positioning slot 2042 and is clamped. At this time, the rotating shaft A2031 is against the rear end of the shaft hole A2021. Since the insertion point of the pin 2033 and the locking seat 207 is the support point of the drone, under the action of the gravity of the drone, the pin 2033 is clamped with the pin limit slot 2071 of the locking seat 207, and the pin B2032 is clamped in the extension positioning slot 2042, ensuring the stable support of the drone.

[0047] When the rocket ignites and boosts the drone, the drone takes off. Under the action of the forward thrust, the pin 2033 disengages along the inclined surface 20711 of the pin limit slot 2071. The rear end of the support plate 202 has no supporting force. Under the elastic force of the left torsion spring 2061 and the right torsion spring 2062, the pin B2032 quickly disengages from the extended positioning slot 2042 and returns to the recovery positioning slot 2041, driving the support plate 202 to pass through the support plate groove 20151 and retract it between the left baffle 2011 and the right baffle 2012. During this process, the pin 2033 is retracted into the pin accommodating opening 20152, and the presser foot 2024 is retracted into the presser foot accommodating opening 20153. During this process, the rotating shaft A2031 returns to the front end of the shaft hole A2021. Under the elastic force of the left torsion spring 2061 and the right torsion spring 2062, the lower end surfaces of the support plate 202, the pin 2033, and the presser foot 2024 do not leak out of the lower end surface of the bottom plate 2015. The support plate returns to its initial recovery state to ensure that it will not increase the resistance of the drone during flight and will not increase the radar reflection area.

Claims

1. A UAV launch and fixing device, characterized by: The invention comprises a drone fixing frame fixed on the belly of the drone, a support plate, a locking seat fixed on the launch frame, a rotating shaft A, a pin shaft B, a pin shaft and an elastic reset part of the support plate, the locking seat is provided with a pin shaft limiting card slot with an opening toward the front side of the aircraft, the drone fixing frame comprises a left baffle, a right baffle and a bottom plate, the bottom plate is provided with a support plate groove for the support plate to extend or retract, the left baffle and the right baffle are arranged opposite to each other on both sides of the support plate groove, the lower end of the left baffle and the lower end of the right baffle are fixedly connected to the bottom plate, the middle parts of the left baffle and the right baffle are symmetrically provided with a rotating shaft limiting slide groove matched with the pin shaft B, the rotating shaft limiting slide groove is a V-shaped groove composed of a recovery positioning groove and an extension positioning card slot. The positioning slot is connected to the extended positioning slot, and a support plate is provided between the left baffle and the right baffle. The front end of the support plate is rotatably connected to the rotating shaft A, the middle part is fixedly connected to the pin B, and the rear end is fixedly connected to the pin. The shaft hole matching the support plate and the rotating shaft A is a long strip hole, the left end of the rotating shaft A is connected to the left baffle, and the right end is connected to the right baffle. The left end of the pin B extends out of the rotating shaft limiting slide groove on the left baffle, and the right end extends out of the rotating shaft limiting slide groove on the right baffle. When the support plate is extended, the pin B is tightly fitted with the extended positioning slot, and the pin is tightly fitted with the pin limiting slot. When the support plate is retracted, the pin is disengaged from the pin limiting slot, and the pin B is driven back into the recovery positioning slot through the elastic reset portion of the support plate.

2. The UAV launch and fixing device according to claim 1, characterized in that: The elastic reset part of the support plate includes a torsion spring shaft, a torsion spring pressure shaft, and a torsion spring. The torsion spring pressure shaft is arranged on the front side of the pin shaft B, the left end is connected to the left baffle, and the right end is connected to the right baffle. The torsion spring shaft is arranged between the torsion spring pressure shaft and the pin shaft B, the left end is connected to the left baffle, and the right end is connected to the right baffle. A torsion spring is sleeved on the torsion spring shaft, the front end torsion arm of the torsion spring is in conflict with the torsion spring pressure shaft, and the rear end torsion arm is in conflict with the pin shaft B.

3. The UAV launch and fixing device according to claim 2, characterized in that: The torsion spring shaft includes a left torsion spring shaft and a right torsion spring shaft, the torsion spring pressure shaft includes a left torsion spring pressure shaft and a right torsion spring pressure shaft, the torsion spring includes a left torsion spring and a right torsion spring, the inner side of the left baffle is provided with a left inner baffle, the inner side of the right baffle is provided with a right inner baffle, the left inner baffle and the right inner baffle are arranged opposite to each other on both sides of the support plate groove, the lower end of the left inner baffle and the lower end of the right inner baffle are fixedly connected to the bottom plate respectively, the left inner baffle and the right inner baffle are symmetrically provided with a rotating shaft limiting slide groove, the support plate is arranged between the left inner baffle and the right inner baffle, the left end of the rotating shaft A passes through the left inner baffle and is connected to the left baffle, and the right end passes through the right inner baffle and is connected to the right The left end of the pin shaft B passes through the left inner baffle and the rotating shaft limiting slide groove on the left baffle in sequence, and the right end passes through the right inner baffle and the rotating shaft limiting slide groove on the right baffle in sequence. The left torsion spring shaft and the left torsion spring pressure shaft are arranged between the left baffle and the left inner baffle and are located in front of the pin shaft B. The left end of the left torsion spring pressure shaft is connected to the left baffle, and the right end is connected to the left inner baffle. The left torsion spring shaft is arranged between the left torsion spring pressure shaft and the pin shaft B, the left end is connected to the left baffle, and the right end is connected to the left inner baffle. A left torsion spring is sleeved on the left torsion spring shaft, and the front end torsion arm of the left torsion spring conflicts with the left torsion spring pressure shaft, and the rear end torsion arm conflicts with the pin shaft B; The right torsion spring shaft and the right torsion spring pressure shaft are arranged between the right baffle and the right inner baffle and are located in front of the pin B. The right torsion spring pressure shaft and the left torsion spring pressure shaft are symmetrically arranged. The right end of the right torsion spring pressure shaft is connected to the right baffle, and the left end is connected to the right inner baffle. The right torsion spring shaft is arranged between the right torsion spring pressure shaft and the pin B and is symmetrically arranged with the left torsion spring shaft. The right end of the right torsion spring shaft is connected to the right baffle, and the left end is connected to the right inner baffle. The right torsion spring shaft is sleeved with a right torsion spring, and the front end torsion arm of the right torsion spring conflicts with the right torsion spring pressure shaft, and the rear end torsion arm conflicts with the pin B.

4. A UAV launch and fixation device according to claim 1, 2 or 3, characterized in that: The extending positioning slot is located at the front side of the recovering positioning slot, and the lower end of the extending positioning slot is communicated with the lower end of the recovering positioning slot.

5. The UAV launch and fixing device according to claim 4, characterized in that: The connection between the extending positioning slot and the recovering positioning slot is in an arc-shaped smooth transition connection.

6. The UAV launch and fixing device according to claim 1, 2, 3 or 5, characterized in that: The height of the pin B on the support plate is higher than the height of the rotating shaft A.

7. The UAV launch and fixation device according to claim 1, 2, 3 or 5, characterized in that: The groove wall of the pin shaft limiting groove is an inclined surface inclined outwardly and upwardly from the groove bottom.

8. The UAV launch and fixing device according to claim 1, 2, 3 or 5, characterized in that: A pin shaft accommodating opening is provided on the bottom plate at the rear end of the support plate groove, and the pin shaft accommodating opening is communicated with the support plate groove. When the support plate is retracted, the pin shaft cooperates with the pin shaft accommodating opening.

9. The UAV launch and fixing device according to claim 8, characterized in that: The rear end of the support plate is provided with a presser foot, and the base plate is provided with a presser foot accommodating opening at the rear end of the pin shaft accommodating opening. The presser foot accommodating opening is connected to the pin shaft accommodating opening. When the support plate is retracted, the presser foot cooperates with the presser foot accommodating opening.

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