A portable UAV ejection device

Abstract

The present invention relates to a portable unmanned aerial vehicle (UAV) ejection device, which belongs to the field of UAV technology. The device comprises a support rod, an ejection auxiliary mechanism, an elastic hanging rope, an aircraft bracket, an ejection mechanism, and an ejection mechanism fixing cable. The support rod is vertically installed in front of the UAV take-off platform and can be tilted in the direction of UAV ejection under the action of the ejection auxiliary mechanism. The fixed end of the elastic hanging rope is connected to the top of the bracket, and the free end is provided with a hook and loop assembly. The engaging end of the ejection mechanism is connected to the hook and loop assembly, and the fixed end is connected to the UAV take-off platform via the ejection mechanism fixing cable. The UAV is supported by the aircraft bracket and is located directly behind the support rod. The ejection hook installed at the bottom is movably connected to the hook and loop assembly to achieve its positioning before take-off. The present invention adopts a split-type slide-free design, which greatly reduces the weight and volume of the ejection device, making it easier for people to carry. The quick assembly and disassembly design reduces the number of people required for the operation and the labor intensity.

Description

Technical Field

[0001] The present invention belongs to the technical field of unmanned aerial vehicles (UAVs), and in particular relates to a portable UAV ejection device. Background Art

[0002] With the development of drone technology, drones have been widely used in both military and civilian fields, bringing innovations in working methods and improved work efficiency to fields such as film and television shooting, security, and line inspection. Multi-rotor drones use multiple rotating rotors to provide flight lift and have the ability to take off and land vertically. They are widely used in various fields, but due to the limitations of the flight principles of multi-rotor aircraft themselves, they have shortcomings in terms of flight time, flight speed, and payload capacity. Fixed-wing drones have advantages in flight time, flight speed, and payload capacity, but in order to achieve the speed required for takeoff, fixed-wing drones require a landing site for taxiing. They will not be able to play a role in some scenarios where takeoff conditions are not available (such as emergency rescue, rapid reconnaissance, aerial mapping, etc.), which seriously limits their application in a wider range of fields.

[0003] In order to enable fixed-wing UAVs to take off under limited field conditions, some UAVs use manual throwing, throwing the UAV like a paper airplane to obtain take-off speed. However, this method has restrictions on the weight and size of the UAV, and has certain requirements on the throwing action and physical strength of the personnel. Especially in high-altitude and plateau areas where the physical strength of the personnel is poor, it is difficult to use the throwing take-off method. In addition, some UAVs use catapults to obtain the ability to take off flexibly, using springs, elastic ropes, compressed gas, chemical fuels, batteries and other media to store energy. With the help of catapults, the UAVs can obtain kinetic energy and meet the take-off conditions. It has broad research and application prospects.

[0004] Current catapults for launching micro-UAVs weighing no more than 250 grams are portable. However, for lightweight small UAVs with strong mission capabilities and weighing no more than 15 kilograms, these catapults typically require components such as rails and brackets. These are heavy and bulky, often requiring specialized vehicles for transportation and a significant number of personnel for installation and commissioning. This makes them inconvenient to use and limits their potential application areas. Based on current needs and current status, it is imperative to research and design a portable catapult capable of launching lightweight small UAVs. Summary of the Invention

[0005] Technical issues to be solved:

[0006] In order to avoid the shortcomings of the existing technology, the present invention provides a portable drone ejection device, which is easy to carry and suitable for high-altitude and cold field environments. It reduces the requirements of fixed-wing drones for take-off conditions and is suitable for light and small drones. It can convert the energy stored in the elastic rope into kinetic energy for drone take-off to the greatest extent. It adopts a split-type slide-free design, which greatly reduces the weight and volume of the ejection device, making it easy for people to carry on their backs. It adopts a quick-install and quick-disassemble design, which reduces the number of people required for the operation and the labor intensity of the people.

[0007] The technical solution of the present invention is: a portable UAV ejection device, comprising a support rod, an ejection auxiliary mechanism, an elastic hanging rope, an aircraft bracket, an ejection mechanism and an ejection mechanism fixing cable;

[0008] The support rod is vertically installed in front of the drone take-off platform and can be tilted in the direction of the drone ejection under the action of the ejection auxiliary mechanism;

[0009] The fixed end of the elastic lanyard is connected to the top of the bracket, and the free end is provided with a hook and loop assembly; the engaging end of the ejection mechanism is connected to the hook and loop assembly, and the fixed end is connected to the drone take-off platform via a fixed cable of the ejection mechanism; the fixed position of the fixed cable of the ejection mechanism and the drone take-off platform is located directly behind the drone;

[0010] The drone is supported by an aircraft bracket, located directly behind the support pole, and is movably connected to the hook and ring assembly through the ejection hook installed at the bottom to achieve its positioning before takeoff;

[0011] During the ejection preparation stage, the support pole is in a vertical state, and the elastic hanging rope and the ejection mechanism fixing cable are both in a tensioned state; during the ejection start-up stage, the ejection mechanism and the hook and ring assembly are disconnected, and the UAV is driven by the elastic hanging rope to accelerate upward to take off, and then the support pole tilts forward, and the UAV's ejection hook and hook and ring assembly slip off, completing the ejection takeoff.

[0012] A further technical solution of the present invention is: the ejection mechanism includes a housing, a steering gear, a grappling hook mechanism, an external voltage stabilizing circuit UBEC, a receiver, a battery, a safety buckle and a remote control; the housing includes a battery compartment and an equipment compartment, the battery is installed in the battery compartment; the steering gear, the external voltage stabilizing circuit UBEC and the receiver are installed in the equipment compartment;

[0013] The grab hook mechanism is installed on the top of the housing as the engaging end, and its engaging / releasing action is controlled by the steering gear;

[0014] The root of the safety buckle is installed on the grab hook mechanism, and the head buckle is connected to the hook and ring assembly;

[0015] The external voltage stabilizing circuit UBEC connects the battery with the receiver and the servo, provides them with an adaptive voltage, and acts as a switch;

[0016] The receiver receives the control signal from the remote controller and controls the servo to realize the engagement / release action of the ejection mechanism;

[0017] The shell side cover of the shell is provided with a transparent observation window for observing the internal external voltage stabilizing circuit UBEC and the indicator light of the receiver; the external voltage stabilizing circuit UBEC switch is provided on the shell side cover of the shell to control the power on and off of the ejection mechanism.

[0018] A further technical solution of the present invention is as follows: the grab hook mechanism includes a housing, a gear set, and a grab hook; a pair of arc-shaped grab hooks are symmetrically arranged, the base of which is a disc structure, which is rotatably connected to the inner bottom surface of the housing via a rotating shaft, and the outer circumferences of the two discs are provided with mutually meshing teeth; the gear set is arranged in the housing, including a large gear and a small gear;

[0019] The small gear is installed on the output shaft of the steering gear and meshes with the large gear, and the large gear meshes with the outer teeth of the disc of the first grab hook; the steering gear drives the small gear to rotate, which in turn drives the large gear, the first grab hook, and the second grab hook to rotate; when the two grab hooks rotate inward, the bite action is completed; when the two grab hooks rotate outward, the release action is completed.

[0020] A further technical solution of the present invention is as follows: the shackle assembly includes a shackle, a connecting rope and a hanging ring, the two ends of the connecting rope are respectively connected to one end of the shackle and the hanging ring; the other end of the shackle is fixed to the free end of the elastic hanging rope, and the other end of the hanging ring is engaged with the grab hook mechanism; the hanging ring is buckled with the buckle on the head of the safety buckle;

[0021] The ejection hook at the bottom of the drone is movably connected to the hook ring.

[0022] A further technical solution of the present invention is that the ejection assist mechanism includes a load balancing cable and a counterweight bag; the fixed end of the load balancing cable is connected to the top of the support pole, and the free end is fixed to the UAV takeoff platform directly in front of the support pole; the counterweight bag is hoisted in the middle of the load balancing cable after being loaded with counterweight;

[0023] During the ejection preparation stage, the load balancing cable is in a tensioned state; during the ejection start-up stage, the load balancing cable is acted upon by the gravity of the weight bag, pulling the support rod to tilt forward.

[0024] A further technical solution of the present invention is that the load balancing cable and the ejection mechanism fixing cable are both fixed to the UAV take-off platform through ground anchors.

[0025] A further technical solution of the present invention is: the support rod is assembled from multiple straight rods, and the connection is fixed by a first quick-release component; a fixed guide wheel is installed at the top of the support rod, and the bottom end is hinged to the lug on the support rod base through a second quick-release component, so that the support rod can freely rotate around the second quick-release component between the vertical direction and the horizontal angle in the ejection direction; the support rod base is fixed to the drone take-off platform by a ground anchor.

[0026] A further technical solution of the present invention is that: the first quick-release assembly and the second quick-release assembly have the same structure, and both include a bolt handwheel, a screw, a nut handwheel, a nut, and a washer; the head of the screw is threadedly mounted in the center hole of the bolt handwheel, and nuts are coaxially mounted at both ends of the center hole of the nut handwheel;

[0027] The screw rod passes through the mounting hole of the support rod and is screwed into the nut of the nut handwheel. Washers are provided between the bolt handwheel and the support rod, and between the support rod and the nut handwheel to avoid interference during rotation.

[0028] A further technical solution of the present invention is that the bolt handwheel and the nut handwheel are both columnar structures with a central hole, and the middle and side parts of the column are hollow structures, which are used to reduce weight, increase grip friction, and facilitate the insertion of the power lever.

[0029] A further technical solution of the present invention is that the aircraft bracket includes a symmetrically arranged left aircraft bracket and a right aircraft bracket, which are used to support the left wing and the right wing of the UAV respectively;

[0030] The left aircraft support includes an upper rod, a middle rod, and a folding support leg; the middle rod is vertically arranged, with its bottom end fixed to the drone takeoff platform via the folding support leg, and its top end connected to the upper rod via a lockable hinge mechanism; the initial angular position required for the drone catapult takeoff is adapted by adjusting the relative angular position of the upper rod and the middle rod; the axial length of the middle rod is adjustable to adapt to the position required for the drone catapult takeoff;

[0031] The right aircraft bracket has the same structure as the left aircraft bracket.

[0032] Working process: Set the ground as the aircraft take-off platform. After all components are installed on the ground, adjust the installation angle and height position of the UAV; before launching the UAV, check the UAV connection power supply and communication control link system to check whether the functions are intact, buckle the ejection hook at the bottom of the UAV into the hook ring, and enter the launch state; after confirming that the UAV and the UAV ejection device are configured and can be ejected, remove the safety buckle, toggle the remote control lever, release the ejection mechanism, and the elastic hanging rope drives the UAV to fly forward and accelerate. At the same time, the support rod tilts forward, the UAV's ejection hook is disengaged from the hook ring, and the UAV is ejected and takes off, completing a UAV ejection take-off operation.

[0033] Beneficial effects

[0034] The beneficial effects of the present invention are as follows: the ejection device of the present invention adopts a split design, eliminating the slide rail commonly used in traditional ejection devices, thereby greatly reducing the weight, size and system complexity of the ejection device;

[0035] The support rod and aircraft bracket are large components of the catapult device. They adopt a plug-in foldable design and quick-release components, which are easy to assemble and disassemble. After disassembly, the size is convenient for personnel to carry. During transportation, the counterweight bag serves as a storage bag to accommodate components such as cables, anchors, elastic ropes, and remote control catapult mechanisms. When arriving at the work site, heavy objects such as sand and gravel are added to reduce the weight of the equipment to be carried and improve portability.

[0036] The catapult device uses an elastic rope as an energy storage medium. The length and elastic coefficient of the elastic rope used can be changed to adapt to the catapult mission of drones with different weights and different take-off speeds. In particular, the catapult device eliminates the slide rail slider in the traditional catapult device, which greatly reduces the weight and size of the entire catapult device. Without the limitation of the slide rail length, the acceleration stroke of the drone catapult can be longer, reducing the overload on the drone during catapult, avoiding damage to the drone due to excessive overload, lowering the structural strength requirements of the ejected drone, reducing the weight cost required to convert existing drones into catapult-type ones, and adapting to a wider range of drone types.

[0037] The ejection device uses ground anchors to fix the support rods, cables, base, aircraft bracket and other components. While reducing the weight of the ejection device and improving portability, it is also adaptable to different environments, especially the operating requirements of field environments.

[0038] This ejection device rationally distributes the positions and load-bearing methods of various force-transmitting and load-bearing components, reducing its structural load and weight. The counterweight bag is suspended by a load-balancing cable, unloading the tension of the elastic rope on the support pole, greatly reducing the load on the support pole that causes it to bend, lowering the strength requirements of the support pole as a whole and the joints between the sections, and reducing the structural weight. At the same time, this load-bearing method eliminates the need for the support pole base to prevent the support pole from being pulled down by the elastic rope, greatly reducing the structural weight of the base.

[0039] The aircraft bracket is divided into two parts, one supporting the left and right wings of the drone. Each part of the bracket can be folded and adjusted in length, angle and position, improving portability and flexibility. The cables and elastic cords provide the required launch angle and position for different drones. The upper rods stabilize the wings and stabilize the drone's posture during launch. The foldable legs and ground anchor points at the bottom of the aircraft bracket improve its adaptability to different surface conditions.

[0040] A series of loops connected to the free end of the elastic lanyard ensures a secure connection between the catapult mechanism hook, drone hook, and safety loop during the launch phase. After launch preparations are complete, the safety loop is easily removed. Once the catapult mechanism hook is released, the loop pulls the drone to accelerate and smoothly unhook at the appropriate position, preventing damage to drone components in flight. Compared to the bracket, trolley, and slider in traditional rail-type catapults, which accelerate along with the drone after release, the loops used in this catapult are lighter in weight, allowing the energy stored in the elastic lanyard to be converted into the drone's kinetic energy to the greatest extent possible.

[0041] After the catapult mechanism's hook is released, the elastic rope drives the drone forward. At the same time, the tension of the elastic rope on the support rod gradually decreases. Under the action of the counterweight mounted on the load balancing rope, the support rod quickly tilts toward the drone's launch direction, clearing obstacles in the drone's flight direction. The drone does not need to immediately climb at a large angle to avoid obstacles, which improves the safety of drone launch and the range of drones that can be adapted.

[0042] The ejection mechanism can be engaged and released by a remote control. The operator can eject the drone while monitoring from the ground station, further reducing the number of personnel required for the ejection. The ejection mechanism is equipped with a safety ring. When the elastic rope is stretched and connected in place and the ejection device is in the launch state, the safety ring is used to prevent premature launch due to human error or ejection mechanism failure, which may cause harm to on-site personnel and the drone, thereby improving safety.

[0043] The quick-release assembly used in this ejection device makes the entire process of transporting, installing, deploying, and ejecting the device "tool-free," eliminating the need for additional tools and delicate work. This shortens the pre-ejection preparation time, and can greatly reduce the difficulty and labor intensity of personnel operation, especially under conditions such as plateau hypoxia, where human body functions are reduced and delicate work is difficult to perform.

[0044] The operation of this ejection device does not require high-pressure gas sources, large batteries and other equipment. The remote-controlled ejection mechanism can also be replaced by a mechanical ejection mechanism or a simple knot, which improves the applicability and reliability in complex and harsh environments in the field. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] Figure 1 is a schematic side view of an embodiment;

[0046] Figure 2 、 Figure 3 It is a partial enlargement of the schematic side view of the embodiment;

[0047] Figure 4 is a schematic diagram of the three-dimensional structure of the ejection device of the embodiment;

[0048] Figure 5 This is a partial enlarged view of the support rod portion of the embodiment;

[0049] Figure 6 1 is a schematic structural diagram of the support rod base of the embodiment;

[0050] Figure 7 2. It is a schematic diagram of the tilting of the support rod of the embodiment;

[0051] Figure 8 Schematic diagram of a UAV and a catapult device in a state ready for launch according to an embodiment;

[0052] Figure 9 is a schematic diagram of a horizontal viewing angle along the ejection direction of the embodiment;

[0053] Figure 10 2. It is a schematic diagram of the three-dimensional structure of the ejection mechanism of the embodiment;

[0054] Figure 11 is a schematic diagram of the interior of the ejection mechanism of the embodiment;

[0055] Figure 12 is a schematic diagram of the internal gear set of the grappling hook mechanism of the embodiment;

[0056] Figure 13 This is a schematic diagram of the three-dimensional structure of the quick-release assembly of the embodiment;

[0057] Figure 14 This is a schematic diagram of the angle adjustment and folding storage of the aircraft bracket in the embodiment;

[0058] Explanation of reference numerals: 1-support pole; 2-support pole base; 3-load balancing cable; 4-weight bag; 5-elastic hanging rope; 6-aircraft bracket; 7-drone; 8-ejection mechanism fixing cable; 9-ejection mechanism; 10-first ground anchor; 11-second ground anchor; 12-third ground anchor; 13-first quick-release assembly; 14-second quick-release assembly; 15-fixed guide wheel; 16-connecting rope; 17-aircraft bracket folding leg; 18-aircraft bracket upper rod; 19-bolt handwheel; 20-nut handwheel; 21-ear; 22-hook; 23-ejection hook; 24-hanging ring ;25-safety buckle;26-grappling hook;27-shell side cover;28-shell;29-grappling hook mechanism;30-external voltage stabilizing circuit UBEC switch;31-transparent observation window;32-servo;33-external voltage stabilizing circuit UBEC;34-receiver;35-battery;36-battery compartment cover;37-equipment compartment;38-battery compartment;39-tie;40-bolt;41-washer;42-marking color code;43-nut;44-chamfer;45-side hollowing;46-aircraft left bracket;47-aircraft right bracket;48-gear set;49-grappling hook mechanism housing. DETAILED DESCRIPTION

[0059] The embodiments described below with reference to the accompanying drawings are exemplary and are intended to explain the present invention, but should not be construed as limiting the present invention.

[0060] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like to indicate directions or positional relationships based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction. The terms "UAV take-off platform", "UAV take-off plane" and "ground" are the operating areas of the ejection device, and are only for the convenience of describing the present invention and listing application example scenarios, and do not indicate or imply that the ejection device must include this component or can only work on the ground. Therefore, they should not be understood as limiting the present invention.

[0061] refer to Figure 1 、 Figure 2 and Figure 3 The present embodiment provides a UAV ejection device, which is characterized by comprising a support rod 1, a support rod base 2, an aircraft bracket 6, a first ground anchor 10, a second ground anchor 11, a third ground anchor 12, a load balancing cable 3, a counterweight bag 4, an elastic hanging rope 5, an ejection mechanism 9, an ejection mechanism fixing cable 8, a first quick-release assembly 13, and a second quick-release assembly 14. The lower end of the support rod 1 is connected to the support rod base 2 through the quick-release assembly 14, and the support rod base 2 is fixed to the ground through the ground anchor 11. The upper end of the support rod 1 is connected to the load The balancing cable 3 and the elastic hanging rope 5 are connected, and the other end of the load balancing cable 3 is fixed to the ground using a ground anchor 10. The counterweight bag 4 is loaded with counterweight and hung on the middle of the load balancing cable 3; one end of the ejection mechanism fixed cable 8 is connected to the ejection mechanism 9, and the other end is fixed to the ground by a ground anchor 12; the ejection mechanism 9 is connected to the free end of the stretched elastic hanging rope 5, and the drone 7 is connected to the hanging ring of the free end of the elastic hanging rope 5 through the ejection hook 16. The aircraft bracket 6 is arranged on both sides, supporting the left and right wings of the drone 7 respectively.

[0062] Reference Figure 1 As shown, the support rod 1, support rod base 2, load balancing rope 3, elastic hanging rope 5, ejection mechanism, ejection mechanism fixing rope 8 and anchor for fixation in the ejection device are in the same plane, the load balancing rope 3 and counterweight bag 4 are on one side of the support rod 1, and the elastic hanging rope 5, ejection mechanism, ejection mechanism fixing rope 8 are on the other side of the support rod 1. In the ready-to-launch state, the load balancing rope 3, elastic hanging rope 5 and ejection mechanism fixing rope 8 are in a taut state.

[0063] Reference Figure 2 、 3As shown, the load-balancing cable 3, the support pole base 2, and the ejection mechanism fixing cable 8 are fixed to the ground by a ground anchor 12. The ground anchor 10 used to fix the load-balancing cable 3 is located on the side of the UAV 7 in the ejection direction. The position of the ground anchor 10 is just right to keep the load-balancing cable 3 in a tensioned state when the support pole 1 is in the vertical position. When the support pole 1 is in the vertical position, the position on the load-balancing cable 3 for mounting the counterweight bag 4 and the size of the counterweight bag 4 allow the counterweight bag 4 to be suspended in the air without contacting the support pole 1 or the ground. In the absence of other external forces, the support pole 1 can be tilted towards the ejection direction at a relatively fast speed under the action of the counterweight bag 4.

[0064] Reference Figure 4 As shown, the support rod 1 is composed of multiple sections of rods and is fixedly connected by a first quick-release component 13 to prevent loosening. The length of each section of the rod itself and its accessories is a length that is convenient for carrying. The connection between the lower end of the lowest section of the rod and the support rod base 2 has a shaft sleeve for the second quick-release component 14 to pass through.

[0065] Reference Figure 5 As shown, a fixed guide wheel 15 is provided at the upper end of the uppermost rod of the support rod 1 for fixing the load balancing cable 3 and the elastic hanging rope 5 and limiting the connection between the load balancing cable 3 and the elastic hanging rope 5 to the correct position.

[0066] Reference Figure 6 As shown, the support pole base 2 has an ear-like component 21 for connecting to the support pole 1, and has limiting holes at the front and back for passing the ground anchor 11; after using the quick-release assembly to connect with the support pole 1, the support pole can rotate freely around the quick-release assembly between the vertical direction and the horizontal angle in the ejection direction, and the ground anchor 11 passes through the limiting hole of the support pole base to fix the support pole base 2, and accessories can be added to the bottom of the support pole base to adapt to different ground environments.

[0067] Reference Figure 7 As shown, after the ejection mechanism 9 is released, the support rod 1 tilts toward the ejection direction under the action of the counterweight.

[0068] Reference Figure 8 As shown, the free end of the elastic lanyard 5 has a hook for connecting to the ejection hook 23 on the drone body, and a hanging ring 24 for the ejection mechanism hook 26 to engage and the safety buckle 25 to buckle.

[0069] Reference Figure 9As shown, the aircraft bracket 6 is divided into two parts, a left aircraft bracket 46 and a right aircraft bracket 47, which respectively support the left and right wings of the drone. The upper rod 18 of the bracket is connected to the middle rod by a lockable hinge mechanism. The relative angle position of the upper rod and the middle rod can be adjusted to adapt to the initial angle position required for the ejection and take-off of the drone 7, and stabilize the posture of the drone 7 at the initial stage of ejection release. The length of the middle rod of the aircraft bracket 6 can be adjusted to adapt to the position required for the ejection and take-off of the drone 7; the lower part of the bracket is a foldable support foot 17, a ground anchor tip or both, which can fix the aircraft bracket to the ground after unfolding, so as to fix the aircraft support rod 1 to different grounds such as hard and soft; when folded, the support foot 17 is parallel to the vertical rod, and the upper rod can rotate up and down around the upper end of the middle vertical rod and can be fixed at any angle. When folded and stored, the upper rod is parallel to the middle vertical rod.

[0070] Reference Figure 10 、 Figure 11 、 Figure 12 As shown, the remote control ejection mechanism 9 of this embodiment includes a housing 28, a housing side cover 27, a battery compartment cover 36, a servo 32, a grappling hook mechanism 29, a UBEC external voltage stabilizing circuit 33, a receiver 34, a battery 35, a safety buckle 25, an ejection mechanism fixing cable 8, and a remote control. The housing is divided into two parts: an equipment compartment and a battery compartment 38. The servo 32, the UBEC external voltage stabilizing circuit 33, and the receiver 34 are installed in the equipment compartment. The battery compartment 38 accommodates the battery 35. The servo 32 is connected to the grappling hook mechanism 29 above. The ejection mechanism fixing cable 8 and the safety buckle are connected to the grappling hook mechanism 29. The grappling hook mechanism includes a gear set 48, a grappling hook 26, and a grappling hook mechanism housing 49. The gear set 48 is engaged through gears and drives the grappling hook 29 to release and engage through an appropriate transmission ratio. The gear set 48 is schematically shown in the figure, and includes but is not limited to single-stage and multi-stage gear sets.

[0071] The UBEC (external voltage regulator circuit) 33 shown connects the battery 35 to the receiver 34 and the servo 32, providing them with an appropriate voltage and acting as a switch. The receiver 34 receives control signals from the remote control to remotely open and close the catapult mechanism's grappling hook mechanism 29. The side cover 27 of the housing 28 has a transparent observation window 31 for observing the internal UBEC (external voltage regulator circuit) 33 and the indicator lights of the receiver 34. The UBEC (external voltage regulator circuit) switch 30 is provided on the housing 28 and the side cover 27 to control the power on and off of the remote control catapult mechanism. The battery compartment cover 36 and the battery compartment 38 contain foam material to secure the battery 35 and act as a buffer. The battery 35 and the battery compartment cover 36 have straps to facilitate the removal and installation of the battery 35.

[0072] The grappling hook mechanism 29 includes the grappling hook 26, a gear set 48, and a grappling hook mechanism housing 49. The grappling hook mechanism 29 is connected to the servo 32 through its housing 49. The output torque of the servo 32 output shaft controls the opening and closing of the grappling hook 26 through the gear set 48. The grappling hook mechanism housing 49 is used to connect the catapult mechanism fixing cable 8 and the safety buckle 25.

[0073] Reference Figure 13 As shown, the quick-release assembly suitable for tool-free operation in this example includes a bolt handwheel 19, a nut handwheel 20, a screw 40, a nut 43, a washer 41, and a marking color code 42. The center of the bolt handwheel 19 is connected to the head of the screw 40, and the nut handwheel 20 is connected to the nut 43. Washers 41 are connected to both types of handwheels, and the marking color codes are located at corresponding positions of the bolts, handwheels, washers and other components.

[0074] Both types of handwheels are nearly cylindrical in shape, suitable for gripping. A slot for a bolt 40 and nut 43 is located in the center of the cylinder's plane. Holes 45 are cut out in the center and sides of the cylinder to reduce weight and increase grip friction, making it easier to insert the power lever and remove tight bolts and nuts. Nuts 43 are attached to both sides of the nut handwheel 20, so there's no need to distinguish between the front and back sides during operation.

[0075] Thick washers 41 are provided on both the bolt handwheel 19 and the nut handwheel 20 to prevent interference with other components during handwheel rotation. The inner wall of the hole of the thick washer 41 on the bolt handwheel 19 is chamfered 44 to facilitate alignment of the screw with the nut 43.

[0076] The marking color mark 42 is a striking color and contains fluorescent material, which is easy to identify even in poor lighting conditions. The marking color mark 42 indicates the screw head of the bolt 40, the nut handwheel washer 41, the position of the through hole through which the screw is to pass, and the direction of the assembled parts, so that the operation can be completed smoothly under poor visual conditions. The screw part of the bolt 40 is also provided with a marking color mark 42 to remind whether the bolt 40 has been inserted into place.

[0077] In conjunction with the accompanying drawings, the method of using the present invention is as follows:

[0078] In this embodiment, a UAV ejection operation process suitable for takeoff without a runway, especially in the field, high altitude hypoxia conditions, etc., includes on-site observation, ejection device installation and deployment, UAV pre-ejection inspection and preparation, and UAV ejection takeoff process.

[0079] During the on-site observation phase, the topography, soil quality, wind speed and direction of the operation area are observed to check for any surrounding hazards. The appropriate location for installing and deploying the ejection device and the appropriate direction for the UAV to launch are selected.

[0080] 1) Place the support base 2 according to the wind direction of the on-site environment so that the UAV can take off against the wind after the catapult device is deployed, and use the ground anchor 11 to fix the position of the support base 2;

[0081] 2) Assemble the various sections of the support rod 1 in sequence and secure them using the quick-release assemblies 13 and 14. Connect the load-balancing cable 3 and elastic lanyard 5 to the support rod 1 and position them correctly on the upper fixed guide wheel 15. Use the quick-release assembly to connect the support rod 1 to the support rod base 2 and check whether it can rotate correctly.

[0082] 3) Place the support pole 1 in a vertical position, pull the load-balancing cable 3 to a straight position and secure it with a ground anchor 10. Then, place the support pole 1 in a horizontal position and connect the weight bag 4 loaded with the weight to the hanging point of the load-balancing cable 3.

[0083] 4) Pull the elastic rope 5 to make the support pole 1 upright until the deformation or tension of the elastic rope 5 reaches the required level. Record the position of the free end of the elastic rope 5 and use it to determine the position of the anchor 12 for fixing the cable 8 of the ejection mechanism, thus completing the fixation of the ejection mechanism 9.

[0084] 5) Turn on the ejection mechanism UBEC external voltage regulator circuit switch 30 to test whether the remote control is working properly, stretch the elastic lanyard 5, and control the ejection mechanism to engage the lanyard at the free end of the elastic lanyard 5 and buckle it into the safety buckle 25;

[0085] 6) unfold the folded aircraft bracket 6, fix it in a suitable position, and adjust its height and the angle of the upper rod to adapt to the UAV ejection requirements;

[0086] 7) Place the UAV in the correct position on the aircraft bracket 6, snap the belly ejection hook 16 into the hook ring 24, and enter the launch state;

[0087] 8) Remove the safety buckle 25, turn the remote control lever, release the ejection mechanism 9, the elastic hanging rope 5 drives the drone to fly forward and accelerate, the support pole 1 tilts forward, the drone ejection hook 16 is separated from the hanging ring 24, and the drone is ejected and takes off.

[0088] Although the embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are illustrative and are not to be construed as limitations on the present invention. A person skilled in the art may change, modify, replace and modify the above embodiments within the scope of the present invention without departing from the principles and purpose of the present invention.

Claims

1. A portable UAV ejection device, characterized by: It includes a support rod, an ejection auxiliary mechanism, an elastic lanyard, an aircraft bracket, an ejection mechanism and a ejection mechanism fixing cable; The support rod is vertically installed in front of the drone take-off platform and can be tilted in the direction of the drone ejection under the action of the ejection auxiliary mechanism; The fixed end of the elastic lanyard is connected to the top of the bracket, and the free end is provided with a hook and loop assembly; the engaging end of the ejection mechanism is connected to the hook and loop assembly, and the fixed end is connected to the drone take-off platform via a fixed cable of the ejection mechanism; the fixed position of the fixed cable of the ejection mechanism and the drone take-off platform is located directly behind the drone; The drone is supported by an aircraft bracket, located directly behind the support pole, and is movably connected to the hook and ring assembly through the ejection hook installed at the bottom to achieve its positioning before takeoff; During the ejection preparation phase, the support rod is in a vertical state, and the elastic hanging rope and the ejection mechanism fixing cable are both in a tensioned state; during the ejection start phase, the ejection mechanism and the hook and ring assembly are disconnected, and the UAV is driven by the elastic hanging rope to accelerate upward to take off, and then the support rod tilts forward, and the UAV's ejection hook and hook and ring assembly slip off, completing the ejection takeoff; The ejection mechanism includes a housing, a servo, a grappling hook mechanism, an external voltage stabilizing circuit UBEC, a receiver, a battery, a safety buckle, and a remote control; the housing includes a battery compartment and an equipment compartment, and the battery is installed in the battery compartment; the servo, the external voltage stabilizing circuit UBEC, and the receiver are installed in the equipment compartment; The grab hook mechanism is installed on the top of the housing as the engaging end, and its engaging / releasing action is controlled by the steering gear; The root of the safety buckle is installed on the grab hook mechanism, and the head buckle is connected to the hook and ring assembly; The external voltage stabilizing circuit UBEC connects the battery with the receiver and the servo, provides them with an adaptive voltage, and acts as a switch; The receiver receives the control signal from the remote controller and controls the servo to realize the engagement / release action of the ejection mechanism; The shell side cover is provided with a transparent observation window for observing the internal external voltage stabilizing circuit UBEC and the indicator light of the receiver; the external voltage stabilizing circuit UBEC switch is provided on the shell side cover of the shell to control the power supply of the ejection mechanism; The grab hook mechanism includes a housing, a gear set, and a grab hook; a pair of arc-shaped grab hooks are symmetrically arranged, with the base of the hooks being a disc structure, which is rotatably connected to the inner bottom surface of the housing via a rotating shaft, and the outer circumferences of the two discs are provided with mutually meshing teeth; the gear set is arranged in the housing, including a large gear and a small gear; The pinion is mounted on the output shaft of the steering gear and meshes with the large gear, which in turn meshes with the outer teeth of the disc of the first grabbing hook. The steering gear drives the pinion to rotate, which in turn drives the large gear, the first grabbing hook, and the second grabbing hook to rotate. When the two grabbing hooks rotate inward, the engagement action is completed; when the two grabbing hooks rotate outward, the release action is completed. The shackle assembly includes a shackle, a connecting rope and a hanging ring, the two ends of the connecting rope are respectively connected to the shackle and one end of the hanging ring; the other end of the shackle is fixed to the free end of the elastic hanging rope, and the other end of the hanging ring is engaged with the grab hook mechanism; the hanging ring is buckled with the buckle on the head of the safety buckle; The ejection hook at the bottom of the drone is movably connected to the hook ring; The ejection auxiliary mechanism includes a load balancing cable and a counterweight bag; the fixed end of the load balancing cable is connected to the top of the support pole, and the free end is fixed to the UAV take-off platform directly in front of the support pole; the counterweight bag is hoisted in the middle of the load balancing cable after being loaded with counterweight; in the ejection preparation stage, the load balancing cable is in a tensioned state; in the ejection start-up stage, the load balancing cable is acted upon by the gravity of the counterweight bag, pulling the support pole forward to tilt.

2. The portable drone ejection device according to claim 1, characterized in that: The load balancing cable and the ejection mechanism fixing cable are both fixed to the UAV take-off platform through ground anchors.

3. The portable UAV ejection device according to claim 1, characterized in that: The support rod is composed of multiple straight rods and the connection is fixed by a first quick-release component; a fixed guide wheel is installed on the top of the support rod, and the bottom end is hinged to the lug on the support rod base through a second quick-release component, so that the support rod can freely rotate around the second quick-release component between the vertical direction and the horizontal angle in the ejection direction; the support rod base is fixed to the drone take-off platform by a ground anchor.

4. The portable UAV ejection device according to claim 3, characterized in that: The first quick-release assembly and the second quick-release assembly have the same structure, and both include a bolt handwheel, a screw, a nut handwheel, a nut, and a washer; the head of the screw is threadedly mounted in the center hole of the bolt handwheel, and nuts are coaxially mounted at both ends of the center hole of the nut handwheel; The screw rod passes through the mounting hole of the support rod and is screwed into the nut of the nut handwheel. Washers are provided between the bolt handwheel and the support rod, and between the support rod and the nut handwheel to avoid interference during rotation.

5. The portable UAV ejection device according to claim 4, characterized in that: The bolt handwheel and the nut handwheel are both columnar structures with a central hole, and the middle and side parts of the column are hollow structures, which are used to reduce weight, increase grip friction, and facilitate the insertion of the power lever.

6. A portable UAV ejection device according to any one of claims 1 to 5, characterized in that: The aircraft bracket includes a symmetrically arranged left aircraft bracket and a right aircraft bracket, which are used to support the left wing and the right wing of the UAV respectively; The left aircraft support includes an upper rod, a middle rod, and a folding support leg; the middle rod is vertically arranged, with its bottom end fixed to the drone takeoff platform via the folding support leg, and its top end connected to the upper rod via a lockable hinge mechanism; the initial angular position required for the drone catapult takeoff is adapted by adjusting the relative angular position of the upper rod and the middle rod; the axial length of the middle rod is adjustable to adapt to the position required for the drone catapult takeoff; The right aircraft bracket has the same structure as the left aircraft bracket.

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