Vertical gravity channel unmanned aerial vehicle accelerated release system and method

Abstract

This invention discloses a vertical gravity channel-type unmanned aerial vehicle (UAV) accelerated release system and method, belonging to the field of rapid UAV deployment and launch assistance. The system includes a release channel installed between a high point on a building and the ground. Along the direction of movement, the release channel sequentially includes a vertical channel section, a connected circular arc turning section, and a short horizontal channel section. The channel is equipped with a sliding rail guide assembly, which, in conjunction with a connecting seat and a dedicated slider roller assembly mounted on the UAV body or landing gear, fixes the UAV's running path and provides anti-sway and anti-rotation constraints within the circular arc section. Under the influence of gravity, the UAV gains kinetic energy through the vertical section and completes the transition of its velocity vector from vertical to horizontal in the circular arc turning section, giving the UAV a predetermined initial horizontal velocity component when exiting the channel. This invention achieves safe, controllable, and rapid release of the UAV without relying on catapult energy.

Description

Technical Field

[0001] This invention belongs to the field of rapid deployment and launch assistance for unmanned aerial vehicles (UAVs), specifically relating to a vertical gravity channel-type UAV accelerated release system and method. Background Technology

[0002] Existing rapid deployment technologies for drones mainly cover catapult takeoff, aerial delivery, and rail-assisted propulsion modes, and are applied in various fields. For example, the tubular vertical catapult technology disclosed in Chinese patent CN113086235B uses gunpowder combustion to generate high-pressure gas, which propels the UAV vertically along the directional groove. Although it can achieve rapid deployment in high-dynamic battlefields, it relies on high-energy propellant, has a large impact load, and requires a complex folding and storage mechanism and directional device. The system is highly complex and poses safety hazards. The pneumatic-hydraulic catapult system proposed in CN107323681B uses an accumulator to drive a hydraulic motor to accelerate the drum. Although it has an intelligent release function, it requires a complex hydraulic circuit such as a replenishing pump, solenoid valve group, and buffer brake cylinder. It has high continuous energy consumption, is difficult to maintain, and is not suitable for long-term fixed deployment in urban environments. The multi-set rectangular sliding rail delivery device disclosed in CN109747827B relies on an aerial mother aircraft platform and uses a combination of gravity and motor drive to achieve UAV rack sliding delivery. However, its structure is designed specifically for the internal space of the carrier aircraft, cannot utilize building height differences, and still requires power to drive the rack for transportation, failing to achieve true passive operation.

[0003] In fixed-scenario applications such as urban emergency inspections and high-rise logistics nodes, existing technologies reveal the following common problems: First, they all rely on external ejection energy or power drive, resulting in system complexity and high operation and maintenance costs; second, they lack effective utilization of the elevation differences of fixed buildings, leading to low energy conversion efficiency; third, they fail to solve the problem of smooth velocity vector transition from vertical acceleration to horizontal launch, resulting in poor attitude stability upon exiting the launch channel; fourth, their safety protection mechanisms are simplistic and difficult to adapt to the stringent requirements of urban environments for fall prevention, accidental release prevention, and wind and rain protection; and fifth, they lack the ability to quickly recover attitude and seamlessly take over flight control after exiting the launch channel, resulting in low success rates in complex urban wind fields. Therefore, there is an urgent need for a structurally simplified, zero-energy-consumption, and highly safe fixed UAV acceleration and release solution. Summary of the Invention

[0004] To address the aforementioned technical problems, this invention provides a vertical gravity channel-type UAV acceleration and release system and method. Through a continuous channel structure consisting of a vertical section, an arc-shaped turning section, and a short horizontal section, the UAV's motion path within the channel is fixed, and a velocity vector transition is achieved. This allows the UAV to acquire a horizontal initial velocity component upon exiting the channel. Safe and controllable release is achieved through speed limiting, buffering, gating, and emergency braking. The system includes a release channel installed high above a building between the building and the ground. Along the direction of motion, the release channel sequentially includes a vertical section, a connected arc-shaped turning section, and a short horizontal section. The channel is equipped with a sliding rail guide assembly, which, in conjunction with a connecting seat and a dedicated slider roller assembly mounted on the UAV's fuselage or landing gear, fixes the UAV's running path and provides anti-sway and anti-rotation constraints within the arc-shaped section. Under the influence of gravity, the UAV gains kinetic energy through the vertical section and completes the velocity vector transition from the vertical to the horizontal direction in the arc-shaped turning section, giving the UAV a predetermined horizontal initial velocity component upon exiting the channel. This invention further incorporates a speed-limiting component, a buffer component, an emergency brake, an end-launch window, and a gating component. It can trigger a pre-set thrust via sensors and a controller before exiting the launch channel, achieving attitude recovery and flight control takeover instantly upon exiting the channel. This invention enables safe, controllable, and rapid deployment of UAVs without relying on ejection power, making it suitable for scenarios such as emergency deployment in high-rise buildings, urban logistics nodes, and emergency inspections.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] A vertical gravity channel-type unmanned aerial vehicle (UAV) acceleration and release system includes:

[0007] A continuous release channel installed at a high point of a building between the building and the ground. The release channel includes, in sequence along the direction of motion, an interconnected vertical section, a circular arc turning section, and a short horizontal section. The vertical section is used to enable the UAV to gain kinetic energy under pure gravity. The exit tangent of the circular arc turning section is consistent with the desired flight launch direction, which is used to smoothly transition the UAV's velocity vector from the vertical direction to the horizontal direction, so that the UAV can obtain a horizontal initial velocity component after passing through the circular arc turning section.

[0008] A slide rail guide assembly installed on the inner wall of the release channel;

[0009] A slider roller assembly that rolls or slides with the slide rail guide assembly, the slider roller assembly is connected to the UAV body, and the slider roller assembly is provided with a keyway and a limiting rib to provide anti-rotation constraint;

[0010] An anti-sway constraint is installed within the arc turning section. The anti-sway constraint includes a lateral guide wheel and an elastic clamping roller. The lateral guide wheel and the elastic clamping roller, together with the slider roller assembly, form a radial and tangential composite limit to suppress the swaying of the UAV within the arc turning section.

[0011] An end-release window and gating component are set at the end of the release channel;

[0012] A controller connected to the end-release window and gating assembly is used to open the end-release window and gating assembly when the UAV reaches the end of the arc turning segment or the short horizontal segment channel and meets the release conditions, so that the UAV flies out of the release channel with a horizontal initial velocity component.

[0013] The present invention also provides a method for accelerating the release of a drone using the above-described vertical gravity channel-type drone acceleration release system, comprising the following steps:

[0014] The drone body is connected to the slider and roller assembly via a connector, so that the slider and roller assembly cooperates with the slide rail guide assembly;

[0015] The end release window and gating components are closed, and the controller completes the system self-test.

[0016] Before or during the operation of the drone, the controller triggers the drone's thrust preset based on the preset drop, channel curvature, and real-time position and speed information.

[0017] Release the upper lock, allowing the drone to slide down the vertical section of the channel under the action of gravity and enter the circular turning section, where the velocity vector transitions from the vertical direction to the horizontal direction.

[0018] During operation, the speed is limited by the speed limiting component. If an abnormality is detected, the emergency brake is triggered to slow down or stop the vehicle.

[0019] When the drone reaches the end of the arc turning section or the short horizontal section of the channel and meets the release conditions, the end release window and gating component are opened, and the drone flies out of the release channel with a horizontal initial velocity component.

[0020] The moment the drone flies out of the release channel, the controller takes over the flight control thrust and attitude recovery control.

[0021] Beneficial effects:

[0022] 1. This invention fully utilizes the gravitational potential energy of the building's elevation difference, eliminating all external launch energy sources such as gunpowder, hydraulics, and motors. It also eliminates the need for complex components such as energy storage devices, pump stations, and solenoid valve groups, simplifying the system structure and reducing operation and maintenance costs. It is particularly suitable for long-term unattended deployment at fixed urban nodes.

[0023] 2. The invention features a unique circular arc turning segment geometry structure. Through precise design of the exit tangent direction, the vertical gravity acceleration is smoothly converted into a horizontal initial velocity. The UAV has a predetermined horizontal velocity component as soon as it exits the channel, eliminating the need for in-flight turning, thus shortening the response time. This fundamentally solves the energy loss and attitude instability problems caused by the additional maneuvering required by traditional vertical catapults.

[0024] 3. The dual-rail guide rail assembly of the present invention works in conjunction with the special slider roller assembly to form a radial-tangential composite limit in the arc section through the keyway, limiting rib, lateral guide wheel and elastic pressing roller, so as to achieve full anti-sway and anti-rotation constraint.

[0025] 4. The adjustable friction speed limiting component of the present invention achieves passive speed limiting, and the emergency brake adopts a power failure self-locking structure, forming a quadruple interlock with the wind and rain sensor, door control component, and fall protection secondary protection mechanism. Any abnormality in any link will trigger channel closure and mechanical locking. The system safety reaches SIL 3 level, far exceeding the single-point protection mechanism of traditional ejection systems.

[0026] 5. This invention sets an attitude recovery trigger sensor at the end of the arc segment, and the controller presets the thrust before exiting the channel. At the moment of exiting the channel, the flight control system works together to complete the mode switching and rapid convergence of the attitude angle. Even in a level 5 wind field, it can still achieve a stable flight success rate, which is significantly better than the design of the prior art that relies on passive stabilization after launch.

[0027] 6. This invention adopts a modular channel structure to support quick replacement of curvature radius and exit direction, and its weatherproof shell and drainage and dust removal design are suitable for all-weather deployment. The multi-unit sequential release function meets the application needs of emergency inspection, logistics clusters and other applications, filling the gap in urban construction drone deployment technology. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the overall structure of a vertical gravity channel-type UAV acceleration and release system according to the present invention;

[0029] Figure 2 A schematic diagram showing the fit between the slide rail guide assembly and the slider roller assembly;

[0030] Figure 3 This is an internal schematic diagram of a vertical gravity channel-type UAV acceleration and release system according to the present invention.

[0031] The attached diagram is labeled as follows: 1. Release channel; 2. Vertical section channel; 3. Circular arc turning section; 4. Short horizontal section channel; 5. Slide rail guide assembly; 6. Slider roller assembly; 7. UAV body; 8. Speed ​​limiting assembly; 9. Buffer assembly; 10. Emergency brake; 11. End release window and gate control assembly; 12. Weatherproof shell; 13. Fall protection secondary protection mechanism; 14. Attitude recovery trigger sensor; 15. Controller; 16. Power supply and communication interface. Detailed Implementation

[0032] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention. Furthermore, the technical features involved in the various embodiments of this invention described below can be combined with each other as long as they do not conflict with each other.

[0033] like Figure 1 As shown, a vertical gravity channel-type UAV acceleration and release system of the present invention includes a release channel 1, a vertical channel section 2, an arc turning section 3, a short horizontal channel section 4, a slide rail guide assembly 5, a slider roller assembly 6, a UAV body 7, a speed limiting assembly 8, a buffer assembly 9, an emergency brake 10, an end release window and gate control assembly 11, a weatherproof shell 12, a fall protection secondary protection mechanism 13, an attitude recovery trigger sensor 14, a controller 15, and a power supply and communication interface 16.

[0034] Release channel 1 is a continuously formed closed or semi-closed channel. Its upper end is fixed to the exterior facade, roof beam, or elevated support structure of a high-rise building via an upper mounting base, and its lower end is fixed to a ground base via a lower mounting base. Release channel 1, along the UAV's flight direction, sequentially includes a vertical channel section 2, an arc-shaped turning section 3, and a short horizontal channel section 4. The vertical channel section 2 provides the main drop to accumulate kinetic energy; the arc-shaped turning section 3 is used to achieve a smooth transition of the velocity vector from the vertical to the horizontal direction, and its exit tangent direction is designed to be consistent with or approximately consistent with the desired flight launch direction, thus giving the UAV a horizontal initial velocity component when leaving the channel. The short horizontal channel section 4 provides a brief attitude stabilization window and thrust take-off window before exiting the channel, and its configuration can be selected according to the application scenario. An end release window and a door control assembly 11 are provided at the end of the short horizontal channel 4. The end release window and door control assembly 11 include a window frame, a door, and a door control drive mechanism. The window frame is fixedly connected to the end of the short horizontal channel 4 via a flange connection and / or bolt connection. The door can move relative to the window frame between a closed position and an open position. The door control drive mechanism is installed on the window frame and is connected to the door for driving the door to open and close. The end release window and door control assembly 11 are provided with a door position detection element, which is connected to the controller 15 to output a door status signal. A weatherproof shell 12 is provided on the outer side of the release channel 1. The weatherproof shell 12 covers at least the arc-shaped turning section 3 and the short horizontal section channel 4, and is fixedly connected to the release channel 1 via a support / clamp / connecting plate. The end of the weatherproof shell 12 is connected to the end release window and the window frame of the door control assembly 11, and a sealing structure (including but not limited to sealing strips and sealing gaskets) is provided between them to form a rainproof and dustproof barrier for the end area when the door is closed. A drainage structure (including but not limited to drainage holes, guide channels, or water collection ports) is provided on the weatherproof shell 12 to draw out liquids entering the shell. A power supply and communication interface 16 is provided on the outer support structure of the ground base and / or the short horizontal section channel 4. The power supply and communication interface 16 includes a power input terminal, a communication port, and a waterproof quick-plug connector connected to the controller 15. The power supply and communication interface 16 is connected to the controller 15, the door control drive mechanism, and the door position detection device via a wiring harness. The wiring harness is laid along the outer side of the release channel 1 and passes through the weatherproof shell 12 through a waterproof cable connector. A cable fixing component is provided between the wiring harness and the release channel 1 to prevent loosening due to vibration.

[0035] like Figure 2 As shown, the slide rail guide assembly 5 is installed on the inner wall of the release channel 1 or on an independent support beam. Preferably, the slide rail guide assembly 5 is a double guide rail structure and is arranged symmetrically along the center of the release channel 1. The UAV body 7 is connected to the slider roller assembly 6 through the body and landing gear connecting seat. The slider roller assembly 6 forms a rolling or sliding engagement with the double guide rails to achieve low-friction guidance.

[0036] likeFigure 3 As shown, a mounting cavity is provided at the end of the short horizontal section of the channel 4. A guide rail assembly 5 is arranged within the mounting cavity along the direction of the UAV's movement for guidance. A speed limiting assembly 8 is fixedly installed on the bottom plate and / or side wall of the mounting cavity, located upstream of the UAV's direction of movement. The friction element of the speed limiting assembly 8 is positioned opposite the force-bearing surface of the slider-roller assembly 6 to apply frictional damping to the slider-roller assembly 6 to achieve speed limiting. The speed limiting assembly 8 is fixedly connected to the channel frame via a mounting base. A buffer assembly 9 is fixedly installed within the mounting cavity, located in the area near the end release window and gate control assembly 11 along the UAV's direction of movement. The buffer surface of the buffer assembly 9 faces the movement path of the slider-roller assembly 6 to absorb the collision energy between the slider-roller assembly 6 or the UAV body 7 and the end of the mounting cavity. An emergency brake 10 is fixedly mounted on a slide rail guide mounting base and / or channel frame, located downstream of the speed limiting component 8 and upstream of the end release window and gate control component 11. The clamping element of the emergency brake 10 engages with the locking surface of the slide rail guide component 5 and / or the slider roller assembly 6 to clamp the slide rail guide component 5 or lock the slider roller assembly 6 upon triggering. The end release window and gate control component 11 are located at the end opening of the short horizontal channel 4, including a window frame, a door, and a gate control drive mechanism. The window frame is fixedly connected to the end of the short horizontal channel 4, and the door is mounted on the window frame and switches between a closed and open position under the action of the gate control drive mechanism. A weatherproof housing 12 is located outside the short horizontal channel 4 and covers the mounting cavity. The weatherproof housing 12 is fixedly connected to the channel frame and forms a protective boundary by mating with the window frame at its end. A secondary fall protection mechanism 13 is installed within the mounting cavity and includes an anchor and a flexible connector. The anchor is fixed near the channel frame and / or window frame. One end of the flexible connector is connected to the anchor, and the other end is connected to the UAV body 7 and / or the slider roller assembly 6 to provide secondary restraint to the UAV before the end-release window and gate control assembly 11 open. An attitude recovery trigger sensor 14 is installed on the side wall and / or top plate of the mounting cavity at a predetermined position within a range of 2 to 5 meters upstream of the end-release window and gate control assembly 11. It is used to detect the positioning status of the UAV body 7 and / or the slider roller assembly 6 and output a trigger signal. A controller 15 is installed outside the short horizontal section of the channel 4 or outside the mounting cavity. The controller 15 is electrically / signally connected to the emergency brake 10, the end-release window and gate control assembly 11, and the attitude recovery trigger sensor 14, and receives gate control status and trigger signals, and outputs braking and gate control drive commands. The power supply and communication interface 16 is located near the controller 15 and fixed to the outer support structure of the channel and / or the ground base. The power supply and communication interface 16 is connected to the controller 15 via a wiring harness to provide power and communication links to the controller 15 and its connected end release window and gate control assembly 11, emergency brake 10 and attitude recovery trigger sensor 14.

[0037] Preferably, the attitude recovery trigger sensor 14 can be a position switch, a photoelectric sensor, or a rail-based odometer, used to determine that the UAV has reached a predetermined position. The controller 15 can trigger thrust pre-setting before the UAV enters the circular turning section 3 or when it has traveled a predetermined distance of 10 to 30 meters, so that it reaches the attitude control threshold before exiting the passage. At the moment the UAV exits the passage, the controller 15 works with the flight control system to complete the mode switch, and achieves rapid convergence of attitude angles based on the inertial measurement unit and altitude and velocity estimation, thereby entering stable flight after obtaining the horizontal initial velocity component.

[0038] Preferably, the controller 15 calculates the release interval based on channel occupancy detection and speed estimation, and achieves queued safe release through upper locking and lower gating. In another embodiment, after release, the slider roller assembly 6 can be retracted to the upper end by a hoisting mechanism for reuse.

[0039] Preferably, the release channel 1 is a modular structure, with the vertical channel 2, the arc turning section 3, and the short horizontal channel 4 connected by flanges or quick-locking devices. The arc turning section 3 is a replaceable module to change the radius of curvature or the direction of the outlet tangent.

[0040] Preferably, the slider roller assembly 6 includes a V-groove roller or an enveloping roller that mates with the dual guide rails. The V-groove roller has an outer surface shape resembling a "V," matching the "V" groove on the guide rail of the slide rail guide assembly 5, ensuring stable movement of the slider on the guide rail. This design achieves a high-precision fit between the slider and the guide rail, providing sufficient contact area and friction to ensure stability during movement and prevent lateral deviation. The enveloping roller has an enveloping shape, forming omnidirectional contact with the guide rail surface of the slide rail guide assembly 5, suitable for applications requiring uniform pressure distribution over a large contact surface. This type of roller is typically used for guidance under high loads or high speeds, reducing wear and improving transmission efficiency. Furthermore, keyways and limiting ribs are provided to provide anti-rotation constraints. The keyway connects with a mating key on the slide rail guide assembly 5 to ensure the correct position and directional movement of the slider roller assembly 6 on the guide rail, preventing deviation or detachment during movement. Limiting ribs are provided on both sides of the slider roller assembly 6 or on the guide rail to limit the longitudinal or lateral movement range of the slider roller assembly 6, ensuring that the slider roller assembly 6 will not be damaged or fail due to excessive offset.

[0041] Preferably, an anti-sway constraint is provided within the arc turning section 3. The anti-sway constraint includes a lateral guide wheel and an elastic clamping roller, forming a radial and tangential composite limit on the UAV constraint components to suppress swaying.

[0042] Preferably, the speed limiting component 8 includes an adjustable friction speed limiting unit, which achieves speed limiting by contacting the friction plate with the guide rail and slider of the slide rail guide component 5, and the friction force can be adjusted by the controller 15 or the mechanical pre-tightening structure.

[0043] Preferably, the emergency brake 10 is a power-off self-locking structure, including a spring-loaded clamp or wedge-shaped stopper; when overspeed, gate control failure, drone power failure or sensor abnormality is detected, the controller 15 triggers the emergency brake 10 to clamp the guide rail or lock the slider.

[0044] Preferably, the end release window and gate control assembly 11 includes a gate body, a driver, and an interlocking mechanism; the interlocking mechanism is linked at least to a position sensor, a weather sensor, and a UAV power-on status signal to ensure that the gate body is opened only when the following release conditions are met:

[0045] Speed ​​conditions: After passing through the vertical section 2 and the circular turning section 3, the UAV reaches a predetermined speed threshold, for example, the horizontal speed of the UAV reaches the range of 2 m / s to 5 m / s.

[0046] Position conditions: The UAV enters the predetermined position range of the arc turning segment 3, for example, the UAV reaches the area 10 to 20 meters away from the exit of the arc segment, ensuring that it is on a stable motion trajectory.

[0047] Attitude conditions: The attitude control status of the UAV has reached the set attitude control threshold. For example, the pitch angle of the UAV is within ±5 degrees and the yaw angle is within ±10 degrees, ensuring that the UAV has the correct flight attitude when it is released.

[0048] Environmental conditions: The wind and rain sensor detects wind speeds below 10 m / s and no heavy rain to ensure that the release window will not open accidentally under severe weather conditions.

[0049] Power status conditions: The drone confirms that its battery level is normal and the electrical system has been successfully started through the power-on status signal, and it is in good working condition.

[0050] Only when all of the above conditions are met simultaneously will the interlocking mechanism control the actuator to open the door and release the drone into the external environment.

[0051] Preferably, the weatherproof outer shell 12 covers the outside of the release channel 1 and has a drain or water collection tank at the bottom.

[0052] Preferably, the secondary fall protection mechanism 13 is a safety rope, a grappling hook, or a secondary locking device. It remains connected when the drone has not reached the predetermined position (within 10 to 20 meters of the end release window) or when the gate is not open. The secondary fall protection mechanism 13 will automatically or be released under controlled conditions after the following release conditions are met:

[0053] Speed ​​conditions: The horizontal speed of the UAV within the arc turning section 3 or the short horizontal section channel 4 reaches the range of 2 m / s to 5 m / s.

[0054] Position conditions: The drone enters the predetermined position range of the arc turning section 3, such as an area about 10 to 20 meters away from the exit, ensuring that the drone is close to the end of the release channel 1.

[0055] Attitude conditions: The attitude control of the UAV has reached the predetermined threshold, such as the pitch angle being controlled within ±5 degrees and the yaw angle being controlled within ±10 degrees, to ensure that the UAV is in a stable flight attitude.

[0056] Environmental conditions: The wind and rain sensor detects wind speeds below 10 m / s and no heavy rain, ensuring that it will not release falsely under severe weather conditions.

[0057] Power status conditions: The drone is powered on and the battery level is normal, and the system has started successfully.

[0058] When the above conditions are met, the secondary fall protection mechanism 13 releases the drone automatically or in a controlled manner, allowing the drone to continue the release operation.

[0059] The present invention also provides a method for accelerating the release of a drone using a vertical gravity channel-type drone acceleration release system, comprising:

[0060] Step 1: Connect the UAV body 7 to the slider roller assembly 6 via the body or landing gear connector, so that it can cooperate with the slide rail guide assembly 5;

[0061] Step 2: Close the end release window and gating component 11, and the controller 15 completes the system self-test, including at least the gating status, the availability of the speed limit component 8, the status of the emergency brake 10, and the sensor status.

[0062] Step 3: Before the UAV enters release channel 1 or during operation, the controller 15 triggers the UAV thrust preset based on the preset drop, channel curvature and real-time position and speed information;

[0063] Step 4: Release the upper lock, allowing the drone to slide down the vertical section 2 under the action of gravity and enter the circular arc turning section 3, where the velocity vector transitions from the vertical direction to the horizontal direction.

[0064] Step 5: During operation, the speed limiting component 8 passively or semi-actively limits the speed. If an abnormality is detected, the emergency brake 10 is triggered to decelerate or stop the vehicle.

[0065] Step 6: When the UAV reaches the end of the circular turning section 3 or the short horizontal section of the channel 4 and meets the speed, position, attitude, environmental and power conditions, open the end release window and the gate control component 11, and the UAV exits the channel with a horizontal initial velocity component.

[0066] Step 7: The moment the UAV leaves the passage, the controller 15 completes the flight control thrust takeover and attitude recovery control, and enters a stable flight state.

[0067] Preferably, the triggering time for the UAV thrust preset in step 3 is: within a predetermined distance or time window before the UAV runs to the arc turning segment 3, so that the UAV thrust reaches a threshold that can provide attitude control margin before exiting the channel.

[0068] Preferably, the abnormality in step 5 includes at least one of the following: overspeed, oscillation exceeding the threshold, guide rail jamming, gate control not in place, strong wind or rainstorm warning, or drone power-on failure; when an abnormality occurs, the end gate control is kept closed and the emergency brake 10 is triggered.

[0069] Preferably, the method further includes a step of retrieving and resetting the slider roller assembly 6 after release, wherein the retrieval method is winch retrieval, chain retrieval, or reverse drive retrieval.

[0070] Those skilled in the art will readily understand that the above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A vertical gravity channel-type unmanned aerial vehicle (UAV) acceleration and release system, characterized in that, include: A continuous release channel is installed between the building and the ground. The release channel includes, in sequence along the direction of movement, an interconnected vertical section, a circular turning section, and a short horizontal section. The vertical section is used to enable the UAV to gain kinetic energy under pure gravity. The exit tangent of the circular arc turning section is consistent with the desired flight launch direction, which is used to smoothly transition the UAV's velocity vector from the vertical direction to the horizontal direction, so that the UAV can obtain a horizontal initial velocity component after passing through the circular arc turning section. A slide rail guide assembly installed on the inner wall of the release channel; A slider roller assembly that rolls or slides with the slide rail guide assembly, the slider roller assembly is connected to the UAV body, and the slider roller assembly is provided with a keyway and a limiting rib to provide anti-rotation constraint; An anti-sway constraint is installed within the arc turning section. The anti-sway constraint includes a lateral guide wheel and an elastic clamping roller. The lateral guide wheel and the elastic clamping roller, together with the slider roller assembly, form a radial and tangential composite limit to suppress the swaying of the UAV within the arc turning section. An end-release window and gating component are set at the end of the release channel; A controller connected to the end-release window and gating assembly is used to open the end-release window and gating assembly when the UAV reaches the end of the arc turning segment or the short horizontal segment channel and meets the release conditions, so that the UAV flies out of the release channel with a horizontal initial velocity component.

2. The vertical gravity channel-type UAV acceleration and release system according to claim 1, characterized in that, Also includes: A speed limiting component is installed in the release channel, and the speed limiting component is connected to the slide rail guide component or the slider roller component; A buffer assembly is installed at the end of the arc turning section or in the short horizontal section of the channel; An emergency brake connected to a controller is connected to a slide rail guide assembly or a slider roller assembly. When the controller detects an abnormality, it triggers the emergency brake to clamp the slide rail guide assembly or lock the slider roller assembly.

3. The vertical gravity channel-type UAV acceleration and release system according to claim 1, characterized in that, Also includes: A weatherproof outer shell covers the outside of the release channel, and a drain or water collection tank is provided at the bottom of the weatherproof outer shell; A secondary fall protection mechanism, interlocked with the end-release window and gate control assembly, maintains connection with the drone when the drone has not reached the predetermined position or the gate control has not been opened.

4. The vertical gravity channel-type UAV acceleration and release system according to claim 1, characterized in that, Also includes: An attitude recovery trigger sensor is installed at the end of the arc turning section or at a short horizontal section of the channel, and the attitude recovery trigger sensor is connected to the controller. A power supply and communication interface is provided on the release channel, which is connected to the controller.

5. The vertical gravity channel-type UAV acceleration and release system according to claim 1, characterized in that, The slide rail guide assembly includes two guide rails.

6. The vertical gravity channel-type UAV acceleration and release system according to claim 5, characterized in that, The dual guide rails are symmetrically arranged along the center of the release channel, and the slider roller assembly includes a V-groove roller or an envelope roller that cooperates with the dual guide rails.

7. The vertical gravity channel-type UAV acceleration and release system according to claim 1, characterized in that, The release channel has a modular structure. The vertical channel section, the arc turning section, and the short horizontal channel section are connected by flanges or quick-locking devices. The arc turning section is a replaceable module.

8. A method for accelerating the release of a drone using a vertical gravity channel-type drone acceleration and release system as described in any one of claims 1-7, characterized in that, Includes the following steps: The drone body is connected to the slider and roller assembly via a connector, so that the slider and roller assembly cooperates with the slide rail guide assembly; The end release window and gating components are closed, and the controller completes the system self-test. Before or during the operation of the drone, the controller triggers the drone's thrust preset based on the preset drop, channel curvature, and real-time position and speed information. Release the upper lock, allowing the drone to slide down the vertical section of the channel under the action of gravity and enter the circular turning section, where the velocity vector transitions from the vertical direction to the horizontal direction. During operation, the speed is limited by the speed limiting component. If an abnormality is detected, the emergency brake is triggered to slow down or stop the vehicle. When the drone reaches the end of the arc turning section or the short horizontal section of the channel and meets the release conditions, the end release window and gating component are opened, and the drone flies out of the release channel with a horizontal initial velocity component. The moment the drone flies out of the release channel, the controller takes over the flight control thrust and attitude recovery control.

9. The method according to claim 8, characterized in that, The triggering timing for the drone thrust preset is 10 to 30 meters before the drone reaches the arc turning section, or 2 to 10 seconds before the drone reaches the arc turning section; the abnormality includes at least one of the following: overspeed, oscillation exceeding the threshold, guide rail jamming, gate control not in place, strong wind or rainstorm warning, or drone power-on failure; when any of the above abnormalities occur, the end release window and gate control components are kept closed, and the emergency brake is triggered.

10. The method according to claim 8, characterized in that, It also includes a step of recovering and resetting the slider roller assembly after the drone flies out of the release channel, with recovery methods including winch recovery, chain recovery, or reverse drive recovery.

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