A medium-sized unmanned aerial vehicle launcher based on a lead screw rope collector

Abstract

The application discloses a medium-sized unmanned aerial vehicle launcher based on a screw rod rope collector, which comprises an energy supply part, a transmission part and a launching part; the energy supply part is a gas actuator located in a screw rod rope collector box body, the transmission part is the screw rod rope collector, and the launching part is a launching frame. A push rod of the gas actuator is in contact with a ball screw in the screw rod rope collector through an end face bearing, and a steel wire rope inlet and outlet in the screw rod rope collector is aligned with a sliding shuttle on the launching frame. The push rod of the gas actuator transmits a pushing force to the ball screw in the screw rod rope collector through the end face bearing, the ball screw spirally advances under the constraint of a ball nut, the steel wire rope is wound into a screw rod limiter, the sliding shuttle and a medium-sized unmanned aerial vehicle on the sliding shuttle slide on the launching frame, the acceleration of the unmanned aerial vehicle is realized, and the unmanned aerial vehicle takes off. Since the unmanned aerial vehicle launcher is small in size and portable, the launcher can be transported to a designated place by using a pickup truck to realize rapid launching, and safety and efficiency problems faced by gas / liquid pressure launchers and rocket boosting launchers are avoided.

Description

Technical Field

[0001] This invention pertains to drone launching devices, specifically relating to a medium-sized drone launcher based on a lead screw rope retractor. Background Technology

[0002] Unmanned aerial vehicles (UAVs) have been widely used in both military and civilian fields. In the military field, UAVs can perform functions such as electronic reconnaissance, radar detection, electronic warfare, and unmanned combat. In the civilian field, UAVs are characterized by low cost, no risk of personnel casualties, and high mobility, and their main applications include forest fire prevention, border patrol, emergency rescue and disaster relief, aerial photography, geological and geomorphological mapping, communication relay, atmospheric sampling, and environmental monitoring.

[0003] Currently, common launch methods for drones mainly include: elastic element catapult, pneumatic / hydraulic catapult, electromagnetic catapult, and rocket-assisted launch. Elastic element catapult primarily utilizes elastic materials such as rubber bands to store energy and launch the drone. However, the traction force on the drone during acceleration is not constant, and it cannot provide a high initial velocity. Furthermore, launching large drones requires a larger launch space for the energy storage of the elastic element. Rocket-assisted launch mainly uses small rockets to propel the drone. Its main disadvantages are high launch costs, high requirements for control system design, and safety risks due to ignition and noise during operation. Pneumatic / hydraulic catapult uses pneumatic / hydraulic fluid as the power source for drone takeoff and is currently the main launch method for medium-sized drones. Its main disadvantages are poor control over high-speed catapult systems and poor energy storage capacity, requiring timely replenishment of the pneumatic (hydraulic) source, thus preventing the achievement of high catapult efficiency. Summary of the Invention

[0004] To address the problems of poor control capabilities, significant safety hazards, and high costs associated with existing land-based UAV launch technologies such as pneumatic / hydraulic launchers and rocket-boosted launchers, this invention provides a UAV launch device.

[0005] To achieve the above objectives, the present invention aims to provide a medium-sized UAV launcher based on a lead screw rope retractor.

[0006] This medium-sized UAV launcher consists of three parts: a power supply section, a transmission section, and a launch section. The power supply section is a gas-fired actuator, which consists of an igniter, gunpowder, a propellant chamber, a sealing ring, an actuator sleeve (cylindrical in shape), a push rod (a cylinder with a cavity at the tail and a pin hole at the head), and a shear pin.

[0007] The transmission part is a ball screw winder, which consists of a ball screw pair (further processed from a standard part), end bearings, a screw transition part (a cylinder with a groove at one end and a shaft hole at the other end), a ball screw winder housing (a hollow cuboid with open ends, hereinafter referred to as the winder housing), a wire rope guide plate (an aluminum plate with guide grooves and screw holes), an actuator fixing cover, an actuator fixing nut, a screw limiter (with an inner diameter slightly larger than the outer diameter of the ball screw after the wire rope is wound, and roughly cylindrical in shape), and screws. The ball screw pair includes a ball screw (a round shaft with a helical raceway on the surface), a ball nut, and balls (spherical, located in the gap between the ball screw and the ball nut, not shown in the attached figure).

[0008] The launch section is a launch frame, which consists of a front support, a rear support, a steel wire rope, a chute, a shuttle (the upper part is arc-shaped and contacts the front wheel of the UAV, and the lower part is connected to the steel wire rope), a slide, and bolts.

[0009] In the energy supply section, after receiving the ignition command, the igniter emits an electric spark to ignite the gunpowder in the chamber, generating high-temperature and high-pressure gunpowder gas. When the thrust generated by the gas pressure in the gas actuator on the push rod is greater than the shearing force of the shear pin, the shear pin is cut off, and the push rod begins to move axially under the action of the gas to perform work and supply energy.

[0010] In the transmission section, the gas actuator push rod interacts with one end of the ball screw through a lead screw transition piece and an end face bearing; the ball nut is fixed to the rope take-up housing by screws; the ball screw is constrained within the ball nut by the balls, allowing the ball screw to rotate around the central axis of the ball nut while moving linearly, thus converting linear motion into rotational motion; the wire rope is pressed against the other end of the ball screw by screws, and as the ball screw rotates, the wire rope can be continuously drawn into the spiral raceway of the ball screw; the lead screw limiter is installed at the rope take-up end of the ball screw by screws to prevent the ball screw from moving beyond its limit, while constraining the wire rope to always remain within the spiral raceway.

[0011] In the launching section, the inlet and outlet of the steel wire rope in the transmission section are on the same plane as the slide groove and shuttle of the launching section. The steel wire rope is wound on the ball screw and connected to the shuttle in the slide groove, pulling the shuttle to move in the slide groove of the launching frame. The front wheel of the UAV to be launched is placed on the shuttle. The front and rear supports are fixed to the launch frame slide by bolts, and the starting tilt angle of the launching frame can be adjusted.

[0012] Compared with the prior art, the beneficial effects of the present invention are:

[0013] 1. Powered by gunpowder: This medium-sized UAV launcher uses a gas actuator as its power supply device. Compared with existing medium-sized UAV launchers (such as gas / hydraulic launchers and rocket booster launchers), it is smaller in size and easier to carry and replace.

[0014] 2. Rapid takeoff acceleration and strong acceleration capability: The gunpowder is ignited by the igniter and burns rapidly, allowing the drone to quickly reach its maximum takeoff acceleration. At the same time, the high energy of the combustion gas can expand and drive the drone to accelerate continuously at a large acceleration.

[0015] 3. Simple structure and low requirements for processing technology: In the existing technology, the gas / hydraulic cylinders of gas / hydraulic catapults are expensive and difficult to manufacture, and rocket boosting requires even higher technical reserves. However, the components in the UAV launcher are common in industry, low in cost, easy to assemble, and suitable for promotion.

[0016] 4. The device is simple, small in size, and has low requirements for takeoff sites. It can be launched from a vehicle in different terrains, which can improve the launch efficiency of UAVs. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the structure of the medium-sized UAV launcher based on the screw rope retractor of the present invention.

[0018] Figure 2 For the present invention Figure 1 Axonometric view of a gas-fired actuator.

[0019] Figure 3 For the present invention Figure 1 Cross-sectional view of a gas-fired actuator.

[0020] Figure 4 For the present invention Figure 1 Isometric view of the lead screw rope take-up device.

[0021] Figure 5 For the present invention Figure 1 Cross-sectional view of the lead screw rope winding device.

[0022] Figure 6 For the present invention Figure 1 Axonometric view of the launch pad.

[0023] Figure 7 For the present invention Figure 1 A bottom view of the launcher.

[0024] The labels in the diagram are explained as follows:

[0025] 1-Gas actuator, 2-Screw rope retractor, 3-Launch mount;

[0026] 101-Igniter, 102-Gunpowder, 103-Powder chamber, 104-Sealing ring, 105-Actuator sleeve, 106-Push rod, 107-Shear pin;

[0027] 201-Actuator fixing nut, 202-Actuator fixing cover, 203-Rope retractor housing, 204-Screw transition piece, 205-End face bearing, 206-Ball nut, 207-Wire rope guide plate, 208-Ball screw,

[0028] 209 - Lead screw limiter;

[0029] 301-Front bracket, 302-Rear bracket, 303-Slide rail, 304-Slide groove, 305-Slide shuttle. Detailed Implementation

[0030] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are not intended to limit the present invention.

[0031] like Figure 1 As shown, a medium-sized UAV launcher based on a screw-type rope take-up device includes a power supply section, a transmission section, and a launch section. The power supply section is a gas actuator 1 located inside the screw-type rope take-up device 2 housing. The transmission section is the screw-type rope take-up device 2, and the launch section is the launch frame 3. The push rod of the gas actuator 1 contacts the ball screw in the screw-type rope take-up device 2 through an end-face bearing, while the wire rope inlet and outlet of the screw-type rope take-up device 2 are aligned with the shuttle on the launch frame 3. The device is generally described as follows: the push rod of the gas actuator 1 transmits thrust to the ball screw in the screw-type rope take-up device 2 through the end-face bearing. The ball screw, constrained by the ball nut, spirals forward, winding the wire rope into the screw limiter, driving the shuttle and the medium-sized UAV (not shown in the figure) on it to slide on the launch frame 3, thereby accelerating the UAV and enabling it to take off. Because of its small size and portability, the drone launcher can be transported to a designated location using a pickup truck for rapid launch, avoiding the safety and efficiency issues associated with pneumatic / hydraulic launchers and rocket-assisted launchers.

[0032] like Figure 2 , Figure 3 The gas actuator 1 includes an igniter 101, gunpowder 102, a chamber 103, a sealing ring 104, an actuator sleeve 105, a push rod 106, and a shear pin 107. The cavity between the actuator sleeve 105 and the push rod 106 is a gas chamber. Initially, the shear pin 107 fixes the push rod 106, preventing axial displacement. When the igniter 101 receives an ignition command, it generates an electric spark to ignite the gunpowder 102. The high-temperature, high-pressure gas generated by the combustion of the gunpowder 102 quickly fills the gas chamber. Because the sealing ring 104 prevents the gas from leaving the gas chamber, it exerts a thrust on the push rod 106. When the thrust reaches the strength limit of the shear pin 107, the shear pin 107 is broken, and the push rod 106 moves axially under the action of the gas, outputting energy outward.

[0033] like Figure 4, Figure 5 The lead screw rope take-up device 2 includes an actuator fixing nut 201, an actuator fixing cover 202, a take-up device housing 203, a lead screw transition piece 204, an end face bearing 205, a ball screw pair, a wire rope guide plate 207, and a lead screw limiter 209. The ball screw pair consists of a ball nut 206 and a ball screw 208. The gas actuator 1 is fixed to the left side of the take-up device housing 203 by the actuator fixing nut 201 and the actuator fixing cover 202. The ball nut 206 is fixed to the right side of the take-up device housing 203 by screws. The wire rope guide plate 207 and the lead screw limiter 209 are also fixed to the right side of the take-up device housing 203 by screws. The end face bearing 205 is installed at the left shoulder of the ball screw 208. The push rod of the gas actuator 1 is pressed against the end face bearing 205 by the lead screw transition piece 204. The ball screw assembly is a standard component. When the ball screw 208 moves axially, it is constrained by the ball nut 206 and rotates around its axis. The wire rope enters the screw limiter 209 through the gap between the wire rope guide plate 207 and the screw limiter 209, and is fixed to the rightmost side of the ball screw 208. As the ball screw 208 spirals forward, it is drawn into the spiral raceway. At the same time, the screw limiter 209 ensures that the wire rope will not slip out of the raceway and cause jamming.

[0034] like Figure 6 , Figure 7 The launcher 3 includes a front support 301, a rear support 302, and a slide rail 303. A groove 304 is opened on the slide rail, and a shuttle 305 is placed on the groove 304. The UAV is connected to the shuttle 305 via its front wheel and placed on the slide rail 303, and the wire rope of the lead screw rope retractor is connected to the shuttle 305.

[0035] This invention aims to solve the problem of in-situ launch of military fixed-wing UAVs on land under field conditions. For a medium-sized UAV with a mass of 50kg, the UAV can reach a takeoff speed of 25m / s after accelerating for 2.5m on the launch pad slide 304.

[0036] The specific process of launching a drone using the drone launcher of the present invention is as follows: First, a medium-sized drone weighing about 50 kg is placed on the shuttle 305, and the steel wire rope of the screw rope retractor 2 is connected to the shuttle 305; an ignition command is sent to the igniter 101 of the gas actuator 1, and the gunpowder 102 begins to burn, generating high-temperature and high-pressure gas; when the gas pressure reaches the shearing strength of the shear pin 107, the shear pin 107 is broken, and the push rod 106 begins to move axially and rotate around its rotation axis under the push of the gas; the steel wire rope is pulled back into the screw limiter 209, pulling the shuttle 305 and the drone to begin to accelerate; when the drone accelerates to the end of the launcher slide 304, it hits the slide 303 at a speed of 25 m / s, the shuttle 305 separates from the drone, and the drone takes off.

[0037] The above description is merely an embodiment of the present invention and is not intended to limit the scope of protection of the present invention. Any equivalent structural transformations made based on the description and drawings of the present invention, or direct or indirect applications in other related technical fields, are included within the scope of protection of the present invention.

Claims

1. A medium-sized UAV launcher based on a lead screw rope retractor, characterized in that: It includes a power supply section, a transmission section, and a launch section. The power supply section is a gas actuator located inside the screw rope take-up unit. The transmission section is the screw rope take-up unit, and the launch section is the launch frame. The gas actuator push rod contacts the ball screw in the screw rope take-up unit through an end face bearing, while the wire rope inlet and outlet in the screw rope take-up unit are aligned with the shuttle on the launch frame. The gas actuator push rod transmits thrust to the ball screw in the screw rope take-up unit through the end face bearing. Under the constraint of the ball nut, the ball screw spirals forward, winding the wire rope into the screw limiter, driving the shuttle and the medium-sized UAV on it to slide on the launch frame, realizing the acceleration and takeoff of the UAV.

2. A medium-sized UAV launcher based on a screw-driven rope retractor according to claim 1, characterized in that: The power supply part is a gas actuator, which consists of an igniter, gunpowder, a chamber, a sealing ring, an actuator sleeve, a push rod, and a shear pin.

3. A medium-sized UAV launcher based on a lead screw rope retractor according to claim 1, characterized in that: The transmission part is a ball screw winder, which consists of a ball screw pair, end face bearing, screw transition component, ball screw winder housing, wire rope guide plate, actuator fixing cover, actuator fixing nut, screw limiter and screw; the ball screw pair includes ball screw, ball nut and balls.

4. A medium-sized UAV launcher based on a lead screw rope retractor according to claim 1, characterized in that: The launching section is the launch frame, which consists of a front support, a rear support, a wire rope, a chute, a shuttle, a slide, and bolts.

5. A medium-sized UAV launcher based on a lead screw rope retractor according to claim 2, characterized in that: The cavity between the actuator sleeve and the push rod is an air chamber; initially, the shear pin fixes the push rod, preventing it from undergoing axial displacement.

6. A medium-sized UAV launcher based on a lead screw rope retractor according to claim 5, characterized in that: When the igniter receives the ignition command, it generates an electric spark to ignite the gunpowder. The high-temperature and high-pressure gas produced by the combustion of the gunpowder quickly fills the gas chamber. Due to the sealing ring, the gas cannot leave the gas chamber and will generate a thrust on the push rod. When the thrust reaches the strength limit of the shear pin, the shear pin is broken, and the push rod moves axially under the action of the gas, outputting energy outward.

7. A medium-sized UAV launcher based on a lead screw rope retractor according to claim 3, characterized in that: The gas actuator is fixed to the left side of the take-up coil housing via the actuator fixing nut and actuator fixing cover. The ball nut is fixed to the right side of the take-up coil housing via screws. The wire rope guide plate and the screw limiter are also fixed to the right side of the take-up coil housing via screws. The end face bearing is installed at the left shoulder of the ball screw. The gas actuator push rod is pressed against the end face bearing via the screw transition piece. The ball screw pair is a standard part. When the ball screw moves axially, it is constrained by the ball nut and rotates around the axis. The wire rope enters the screw limiter through the gap between the wire rope guide plate and the screw limiter and is fixed to the rightmost side of the ball screw. As the ball screw helically advances, it is drawn into the helical raceway. At the same time, the screw limiter ensures that the wire rope will not slip out of the raceway and cause jamming.

8. A medium-sized UAV launcher based on a lead screw rope retractor according to claim 4, characterized in that: The slide has a groove, and the shuttle is placed on the groove; the drone is connected to the shuttle via its front wheel and placed on the slide, and the wire rope of the screw rope retractor is connected to the shuttle.

9. A medium-sized UAV launcher based on a lead screw rope retractor according to claim 3, characterized in that: In the transmission section, the gas actuator push rod interacts with one end of the ball screw through a lead screw transition piece and an end face bearing; the ball nut is fixed to the rope take-up housing by screws; the ball screw is constrained within the ball nut by the balls, allowing the ball screw to rotate around the central axis of the ball nut while moving linearly, thus converting linear motion into rotational motion; the wire rope is pressed against the other end of the ball screw by screws, and as the ball screw rotates, the wire rope can be continuously drawn into the spiral raceway of the ball screw; the lead screw limiter is installed at the rope take-up end of the ball screw by screws to prevent the ball screw from moving beyond its limit, while constraining the wire rope to always remain within the spiral raceway.

10. A medium-sized UAV launcher based on a lead screw rope retractor according to claim 4, characterized in that: In the launching section, the wire rope inlet and outlet of the transmission section are in the same plane as the slide groove and shuttle of the launching section. The wire rope is wound on the ball screw and connected to the shuttle in the slide, pulling the shuttle to move in the slide groove of the launching frame. The front wheel of the UAV to be launched is placed on the shuttle. The front and rear supports are fixed to the slide of the launching frame by bolts, and the starting tilt angle of the launching frame is adjusted.

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