Automatic ejection unmanned aerial vehicle system and ejection method thereof

Abstract

This invention relates to an automatic ejection unmanned aerial vehicle (UAV) system and method, belonging to the field of UAV technology, and solves the problems of existing foldable UAVs requiring manual wing deployment and slow takeoff response. It includes: a UAV and an automatic ejection mechanism; the UAV is a foldable UAV; the automatic ejection mechanism includes: an energy storage chamber, an ejection bay, and a UAV carrier; the energy storage chamber provides the power required for ejection; the ejection bay is cylindrical and used to load the folded UAV; the UAV carrier is located inside the ejection bay and above the energy storage chamber; the energy storage chamber can push the UAV carrier to slide along the ejection bay; the UAV carrier is used to eject the UAV from inside the ejection bay. This invention enables the ejection and takeoff of foldable UAVs, with the UAV automatically unfolding and entering flight mode after launch, achieving rapid response, takeoff, and reaching the mission state.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle technology, and in particular to an automatic ejection unmanned aerial vehicle system and its ejection method. Background Technology

[0002] Currently, most catapult-launched drone systems are fixed-wing aircraft or foldable fixed-wing aircraft.

[0003] Fixed rotor drones have fixed arm structures and are relatively large in size, making them inconvenient to carry or transport.

[0004] Foldable rotorcraft drones have solved the size problem, but they are all manually folded or unfolded, which makes takeoff inconvenient. Therefore, a rotorcraft drone capable of automatically unfolding its arms is needed.

[0005] Existing foldable rotary-wing drones all require manual unfolding of the wings, which is cumbersome; drone takeoff also requires manual operation or placement, which occupies a large amount of public resources. In order to achieve rapid takeoff of drones, a flight system suitable for foldable drones is needed. Summary of the Invention

[0006] Based on the above analysis, the present invention aims to provide an automatic ejection unmanned flight system and ejection method to solve the problems of existing folding drones requiring manual wing deployment and slow drone takeoff response during launch.

[0007] The objective of this invention is mainly achieved through the following technical solutions:

[0008] An automatic ejection unmanned aerial vehicle system includes: a drone and an automatic ejection mechanism; the drone is a foldable drone; the automatic ejection mechanism includes: an energy storage chamber, an ejection compartment, and a drone bracket; the energy storage chamber provides the power required for ejection; the ejection compartment is cylindrical and is used to load the folded drone; the drone bracket is disposed inside the ejection compartment and located above the energy storage chamber; the energy storage chamber can push the drone bracket to slide along the ejection compartment; the drone bracket is used to push the drone out of the ejection compartment.

[0009] Furthermore, the automatic ejection mechanism also includes an extension cavity and a sliding bracket.

[0010] Furthermore, the sliding bracket is slidably engaged with the protruding cavity; the sliding bracket is fixedly connected to the UAV bracket.

[0011] Furthermore, the sliding bracket includes a sliding piston rod, an outer support rod, and a top plate; the sliding piston rod and the outer support rod are parallel to each other and are connected as a whole through the top plate.

[0012] Furthermore, the sliding piston rod extends into the protruding cavity and can slidably seal the protruding cavity; the outer support rod is fixedly connected to the drone bracket.

[0013] Furthermore, an exhaust valve is provided between the energy storage chamber and the extension chamber.

[0014] Furthermore, the drone includes: a drone body, an automatic deployment mechanism, and a rotor arm; the rotor arm is rotatably mounted on the drone body via the automatic deployment mechanism.

[0015] Furthermore, the automatic deployment mechanism includes: a first support, a rotary spring-opening assembly, and a second support; the first support is fixedly installed on the main body of the UAV, and the second support is fixedly connected to the rotor arm; the first support and the second support are rotatably connected through the rotary spring-opening assembly.

[0016] Furthermore, the rotating spring-opening assembly includes: a rotating shaft and a torsion spring; the first support and the second support are rotatably connected by the rotating shaft; the torsion spring is sleeved on the rotating shaft and disposed between the first support and the second support, for realizing automatic reset after the first support and the second support rotate relative to each other.

[0017] A method for launching a foldable drone using an unmanned aerial vehicle (UAV) system; the method includes:

[0018] Step S1: Load the drone;

[0019] Specifically, the drone is folded and placed into the ejection compartment of the automatic ejection mechanism;

[0020] Step S2: Activate the automatic launch mechanism to accelerate the drone;

[0021] When the exhaust valve opens, the energy storage chamber releases gas, which pushes the sliding bracket to slide along the extension chamber; the sliding bracket drives the drone bracket to move synchronously; the drone bracket propels the drone to accelerate.

[0022] Step S3: The drone is launched from the cabin;

[0023] Specifically, after the drone carrier separates from the drone, the drone has a certain initial velocity and continues to slide upward in the ejection compartment until it flies out of the ejection compartment; thus completing the launch of the drone.

[0024] Step S4: Unmanned Aerial Vehicle (UAV) rotors deploy;

[0025] Specifically, the drone's rotor arms rotate and unfold to a horizontal position relative to the drone's main body, the drone's rotors start rotating, and the drone enters flight mode.

[0026] The technical solution of this invention can achieve at least one of the following effects:

[0027] 1) The unmanned aerial vehicle system of this invention has a simple and compact overall structure, making it easy to carry and transport. This invention uses high-pressure gas propulsion, resulting in minimal damage to the launching device during launch, and the launching device is simple, effective to maintain, with long maintenance intervals.

[0028] 2) The unmanned aerial vehicle system of this invention features a reusable ejection chamber that uses gas as the ejection medium, ensuring safety and zero pollution. The energy storage chamber of this invention can be repeatedly supplied with high-pressure gas, which can be produced on demand, significantly reducing the risks during storage and transportation. This ensures that the launching device can complete a sufficient number of launches during missions.

[0029] 3) The unmanned flight system of the present invention launches the foldable drone into the air through an automatic ejection mechanism. After launch, the drone automatically unfolds and enters flight mode, which can realize the drone's rapid response, take-off and flight mission state.

[0030] 4) This invention uses high-pressure gas ejection, producing no light or smoke effects, resulting in no pollution and facilitating concealment of the launch point. After completing the launch mission, the automatic ejection mechanism of this invention generates no significant residual heat, allowing for a second launch within a short time.

[0031] 5) This invention can adjust the pressure value of the energy storage chamber according to mission requirements to launch the UAV at different altitudes.

[0032] In this invention, the above-described technical solutions can be combined with each other to achieve more preferred combinations. Other features and advantages of this invention will be set forth in the following description, and some advantages may become apparent from the description or be learned by practicing the invention. The objects and other advantages of this invention can be realized and obtained from what is particularly pointed out in the description and drawings. Attached Figure Description

[0033] The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Throughout the drawings, the same reference numerals denote the same parts.

[0034] Figure 1 This is a schematic diagram of the structure of an automatic ejection unmanned flight system according to the present invention;

[0035] Figure 2 The present invention relates to a sliding bracket for an automatically ejected unmanned flight system;

[0036] Figure 3 This is a schematic diagram of the maximum travel state of the sliding bracket of an automatic ejection unmanned flight system according to the present invention;

[0037] Figure 4 for Figure 3 A magnified view of a portion of the image;

[0038] Figure 5 This is a schematic diagram of the loading state of an unmanned aerial vehicle (UAV) in an automatic ejection unmanned flight system according to the present invention.

[0039] Figure 6 This is a schematic diagram of the folded state of an unmanned aerial vehicle (UAV) of an automatically ejected unmanned flight system according to the present invention.

[0040] Figure 7 This is a schematic diagram of the deployed state of an unmanned aerial vehicle (UAV) of an automatically ejected unmanned flight system according to the present invention.

[0041] Figure 8 This is a schematic diagram of the free rotation state of the automatic deployment mechanism of an automatic ejection unmanned flight system according to the present invention.

[0042] Figure 9 This is a schematic diagram of the folded state of the rotor arm of an automatic ejection unmanned flight system according to the present invention;

[0043] Figure 10 This is a schematic diagram of the rotor arm of an automatically ejected unmanned flight system according to the present invention in its deployed state;

[0044] Figure 11 A partial cross-sectional view of the locking and limiting state of the automatic deployment mechanism of an unmanned aerial vehicle (UAV) in an automatic ejection unmanned flight system according to the present invention.

[0045] Figure 12 This is a top view of the locking and limiting state of the automatic deployment mechanism of an unmanned aerial vehicle (UAV) in an automatic ejection unmanned flight system according to the present invention.

[0046] Figure label:

[0047] 1-UAV body; 2-Automatic deployment mechanism; 3-Rotor arm; 4-Extension cavity; 5-Ejection compartment; 6-Exhaust valve; 7-Energy storage chamber; 8-Inflation port; 9-Sliding bracket; 10-UAV bracket;

[0048] 201-First support; 202-Rotating shaft; 203-Torsion spring; 204-Claw; 204a-Claw groove; 205-Sliding rod; 206-Pin; 207-Compression spring; 208-Second support;

[0049] 301 - Socket; 401 - Stop block;

[0050] 901 - Sliding piston rod; 902 - Outer support rod; 903 - Top plate; 904 - Sealing groove;

[0051] 1001-Receiving Block. Detailed Implementation

[0052] The preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which constitute a part of the present invention and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0053] Example 1

[0054] One specific embodiment of the present invention discloses an automatic ejection unmanned flight system, such as... Figures 1 to 12 As shown, it includes: a drone and an automatic catapult mechanism.

[0055] 1) Automatic ejection mechanism

[0056] The automatic ejection mechanism includes: an energy storage chamber 7, an ejection compartment 5, and a drone bracket 10; the energy storage chamber 7 provides the power required for ejection; the ejection compartment 5 is cylindrical and is used to load the folded drone; the drone bracket 10 is disposed inside the ejection compartment 5 and above the energy storage chamber 7; the energy storage chamber 7 can push the drone bracket 10 to slide along the ejection compartment 5; the drone bracket 10 is used to push the drone out of the ejection compartment 5.

[0057] like Figure 1 As shown, the automatic ejection mechanism also includes: an extension cavity 4 and a sliding bracket 9.

[0058] In one specific embodiment of the present invention, an exhaust valve 6 is provided between the energy storage chamber 7 and the extension chamber 4. When the exhaust valve 6 is closed, high-pressure gas is input into the energy storage chamber 7; when the exhaust valve 6 is open, the high-pressure gas in the energy storage chamber 7 can be released quickly, and when the high-pressure gas is discharged, it can propel the UAV to launch out of the ejection compartment 5.

[0059] Specifically, the energy storage chamber 7 is provided with an air inlet 8, which is used to fill the energy storage chamber 7 with high-pressure gas; an exhaust valve 6 is provided between the energy storage chamber 7 and the extension chamber 4. In implementation, the connection or closure between the energy storage chamber 7 and the extension chamber 4 can be controlled by opening or closing the exhaust valve 6.

[0060] Specifically, the sliding bracket 9 is slidably engaged with the protruding cavity 4; the sliding bracket 9 is fixedly connected to the drone bracket 10. When the sliding bracket 9 slides relative to the protruding cavity 4, it can drive the drone bracket 10 to move synchronously.

[0061] Furthermore, such as Figure 2 As shown, the sliding bracket 9 includes: a sliding piston rod 901, an outer support rod 902, and a top plate 903.

[0062] like Figure 2As shown, the sliding piston rod 901 and the outer support rod 902 are parallel to each other and are connected as one unit through the top plate 903.

[0063] Preferably, the outer support rod 902 is provided with two, three or four rods.

[0064] Specifically, the sliding piston rod 901 extends into the interior of the extension cavity 4 and can slidably seal the extension cavity 4. The upper end of the outer support rod 902 is fixedly connected to the top plate 903, and the lower end of the outer support rod 902 is fixedly connected to the drone bracket 10. Therefore, when the sliding piston rod 901 slides inside the extension cavity 4, the drone bracket 10 slides inside the ejection chamber 5.

[0065] Specifically, such as Figure 4 As shown, a piston portion is provided at the lower end of the sliding piston rod 901, and the piston portion fits against the inner wall of the protrusion cavity 4. One or more annular sealing grooves 904 are provided on the outer side of the piston portion, and elastic sealing rings are installed in the sealing grooves 904.

[0066] In one specific embodiment of the present invention, the drone bracket 10 is an annular plate structure; the drone bracket 10 is sleeved on the outside of the protruding cavity 4.

[0067] Specifically, the inner diameter of the drone bracket 10 is larger than the outer diameter of the protrusion cavity 4, and the outer diameter of the drone bracket 10 is smaller than the inner diameter of the ejection compartment 5.

[0068] Furthermore, in order to ensure reliable support of the drone by the drone bracket 10, a support block 1001 is fixedly installed above the drone bracket 10; correspondingly, a support interface 301 is provided on the rotor arm 3 of the drone; the support block 1001 and the support interface 301 can be assembled with each other.

[0069] In this invention, the circumferential positioning of the UAV in the ejection chamber 5 is achieved by the cooperation of the receiving block 1001 and the receiving interface 301, so that the UAV can only be ejected out of the chamber along the axial direction of the ejection chamber 5, and cannot rotate circumferentially in the ejection chamber 5.

[0070] Furthermore, such as Figure 4 As shown, a stop block 401 is provided at the upper end of the protrusion cavity 4. The stop block 401 is located on the outside of the protrusion cavity 4 and at the top of the protrusion cavity 4. The stop block 401 is used to limit the displacement of the drone bracket 10 and prevent the drone bracket from detaching from the protrusion cavity 4.

[0071] In this invention, a sliding seal is achieved between the sliding piston rod 901 and the extension chamber 4 through an elastic sealing ring. When the exhaust valve 6 is opened, the high-pressure gas in the energy storage chamber 7 enters the extension chamber 4 and pushes the piston part upward, thereby realizing the upward movement of the sliding bracket 9 and the UAV bracket 10. When the UAV bracket 10 slides along the ejection chamber 5, it can push the UAV out of the ejection chamber 5, ultimately realizing the ejection launch of the UAV.

[0072] like Figure 1 The image shows the initial state of the automatic ejection mechanism; as shown... Figure 5 The image shows the state of the folded drone inside the ejection compartment 5 of the automatic ejection mechanism.

[0073] like Figure 3 , Figure 4 As shown, this is the maximum stroke of the drone carrier 10. The piston is located at the top of the extension cavity 4, and the top of the sliding carrier 9 is located at the top of the ejection chamber 5. At this time, the drone carrier 10 cannot continue to move due to the limiting effect of the stop part 401. The drone carrier 10 pushes the drone to move and provides a certain initial speed, so that the drone separates from the drone carrier 10 and the drone can fly out of the ejection chamber 5, thus realizing the ejection of the drone.

[0074] 2) Unmanned aerial vehicles (UAVs) (e.g., catapult-launched quadcopter UAVs)

[0075] To achieve catapult flight of the unmanned aerial vehicle system of the present invention, this embodiment also provides a foldable and automatically deployable unmanned aerial vehicle, such as... Figure 6 , Figure 7 As shown.

[0076] like Figure 6 , Figure 7 As shown, the drone includes: a drone body 1, an automatic deployment mechanism 2, and a rotor arm 3; the rotor arm 3 is rotatably mounted on the drone body 1 via the automatic deployment mechanism 2.

[0077] Preferably, four rotor arms 3 are rotatably mounted on the main body 1 of the UAV of the present invention, and the four rotor arms 3 are evenly distributed along the circumferential direction of the main body 1 of the UAV. Furthermore, rotors are mounted on the rotor arms 3 for realizing the flight of the UAV.

[0078] like Figure 5 As shown, this is the launch-ready state of the UAV of the present invention. When the UAV is folded, it is placed in the ejection compartment 5 and can be powered by the energy storage chamber 7. After the UAV is launched from the ejection compartment 5, its rotor arms 3 will automatically unfold to the desired position under the action of the automatic unfolding mechanism. Figure 7 The unfolded state shown.

[0079] Furthermore, the main body 1 of the drone contains a control unit, which controls the drone to start rotating its rotors after it is deployed, thereby enabling the drone to fly.

[0080] Furthermore, a hangar is provided below the main body 1 of the drone, which is used to carry items to be transported or to carry testing instruments; when in use, items can be carried in the hangar as needed.

[0081] Furthermore, a control unit is installed inside the main body 1 of the drone. The drone control unit of this invention adopts a solution known in the prior art. The control unit is not part of this invention that distinguishes it from the prior art, and will not be described in detail here.

[0082] like Figure 6 As shown, when the rotor arms 3 are folded, the multiple rotor arms 3 are parallel to each other; the multiple rotor arms 3 are folded under the main body of the UAV 1; and can be installed in the ejection compartment 5.

[0083] like Figure 7 As shown, when the rotor arms 3 are deployed, multiple rotor arms 3 are located on the same plane.

[0084] like Figure 8 As shown, the automatic deployment mechanism 2 includes: a first support 201, a rotary spring-opening assembly, a limiting assembly, and a second support 208; the first support 201 is fixedly mounted on the UAV body 1, and the second support 208 is fixedly connected to the rotor arm 3; the first support 201 and the second support 208 are rotatably connected by the rotary spring-opening assembly. The first support 201 and the second support 208 are limited between each other by the limiting assembly.

[0085] 2.1) Rotary spring-loaded assembly

[0086] like Figure 8 As shown, the rotating spring-opening assembly includes a rotating shaft 202 and a torsion spring 203.

[0087] The first support 201 and the second support 208 are rotatably connected by a rotating shaft 202; the torsion spring 203 is sleeved on the rotating shaft 202 and is disposed between the first support 201 and the second support 208 to realize automatic reset after the first support 201 and the second support 208 rotate relative to each other.

[0088] Specifically, the two ends of the torsion spring 203 abut against the first support 201 and the second support 208, respectively. When the first support 201 and the second support 208 rotate relative to each other, the torsion spring 203 is in a compressed state. When the torsion spring 203 returns to its original position, the first support 201 and the second support 208 are limited by the limiting component, and the two cannot rotate relative to each other.

[0089] like Figure 8 , Figure 9 As shown, when the rotor arm 3 is in the folded state, the two end faces of the first support 201 and the second support 208 are perpendicular; at this time, the torsion spring 203 is in a compressed state.

[0090] like Figure 10 , Figure 11 , Figure 12 As shown, when the rotor arm 3 is in the deployed state, the two end faces of the first support 201 and the second support 208 abut against each other. Furthermore, in the deployed state, the torsion spring 203 is also in a compressed state, and at this time, the torque of the torsion spring 203 is sufficient to overcome the gravitational pull of the rotor arm 3 on the rotation shaft 202.

[0091] Furthermore, the automatic opening of the second support 208 of the present invention can be achieved by the reset of the torsion spring 203, or by the automatic reset function of a spring energy storage device such as a tension spring or a leaf spring.

[0092] Furthermore, the second support 208 is provided with a threaded hole at one end connected to the rotor arm 3, and the rotor arm 3 is provided with an external thread at one end. The rotor arm 3 is fixedly connected to the second support 208 by means of threaded connection.

[0093] 2.2) Limiting components

[0094] In one specific embodiment of the present invention, such as Figure 8 As shown, in order to limit the deployment of the rotor arm 3, the automatic deployment mechanism 2 is also equipped with a limiting component.

[0095] like Figure 8 As shown, the limiting assembly includes: a claw 204, a sliding rod 205, a pin 206, and a compression spring 207.

[0096] Specifically, the pin 206 is slidably installed inside the first support 201, and a compression spring 207 is sleeved on the outside of the pin 206; the sliding rod 205 is fixedly installed at the upper end of the pin 206; and the compression spring 207 is disposed between the sliding rod 205 and the first support 201.

[0097] Specifically, the first support 201 is provided with a pin hole, which is a stepped hole.

[0098] The pin 206 is inserted into the pin hole to achieve a sliding connection with the first support 201; a compression spring 207 is installed in the large-diameter section of the stepped hole, and the small-diameter section of the stepped hole is in sliding engagement with the pin 206; such as Figure 8 As shown.

[0099] Furthermore, the sliding rod 205 moves synchronously with the pin 206; when the pin 206 slides relative to the first support 201, it can drive the compression spring 207 to compress or extend. Specifically, when the sliding rod 205 moves upward, the compression spring 207 extends, and when the sliding rod 205 moves downward, the compression spring 207 is compressed.

[0100] In one specific embodiment of the present invention, the claw 204 is fixedly mounted on the second support 208; the claw 204 can engage with the sliding rod 205.

[0101] Furthermore, a slot 204a is provided on one side of the pawl 204; after the slot 204a engages with the sliding rod 205, the second support 208 continues to rotate, and the pawl 204 will press the sliding rod 205 downward; when the sliding rod 205 moves downward, it will drive the pin 206 to move downward and the compression spring 207 will be compressed.

[0102] Specifically, the first support 201 is provided with a locking cavity, and the sliding rod 205 is disposed inside the locking cavity and is fixedly connected to the pin 206.

[0103] Specifically, the sliding rod 205 is set perpendicular to the pin 206, that is, the axis of the sliding rod 205 is perpendicular to the axis of the pin 206.

[0104] Specifically, the slot 204a shown is a semi-circular slot, such as... Figure 8 As shown.

[0105] As the rotor arm 3 gradually extends to a horizontal position, the pawl 204 on the second support 208 simultaneously presses down the sliding rod 205, the pin 206, and the compression spring 207. The pin 206 inside the first support 201 moves downwards, and simultaneously the sliding rod 205 slides into the slot 204a of the pawl 204, thus achieving the locking and limiting function of the rotor arm 3, ensuring that the rotor arm 3 is horizontal with the first support 201 after extension. Figure 10 As shown.

[0106] After the drone is recovered, the compression spring 207 can be further compressed by pulling down the pin 206, the sliding rod 205 can be separated from the claw 204, the claw 204 can be released, and the rotor arm 3 can be folded.

[0107] 2.3) Launching principle of the catapult-launched UAV of the present invention:

[0108] Fold the drone's rotor arm 3 into Figure 6 As shown in the diagram, the drone is placed into the ejection chamber 5. The inner wall of the ejection chamber 5 limits the rotor arm 3, and the drone bracket 10 inside the ejection chamber 5 supports and lifts the drone's rotor arm 3, completing the installation of the drone within the automatic ejection mechanism, achieving the desired result. Figure 5 The state shown.

[0109] Furthermore, using a portable air pump, gas is injected into the energy storage chamber 7 through the air inlet 8 of the ejection compartment 5 until the specified pressure is reached (set as needed).

[0110] Furthermore, the fully charged automatic ejection drone system is placed at a designated location, and the exhaust valve 6 is opened. High-pressure gas instantly fills the extension chamber 4 and pushes the sliding bracket 9 upwards at an accelerated speed. The sliding bracket 9 and the drone bracket 10 are fixedly connected. Therefore, the sliding bracket 9 will push the ejection-type quadcopter drone by pushing the drone bracket 10. When the sliding bracket 9 reaches its maximum stroke, the ejection-type quadcopter drone separates from the drone bracket 10. At the same time, the ejection-type quadcopter drone completes its ejection from the cabin and continues to move upwards at a preset speed. It automatically deploys the rotor arms 3, and the control unit controls the motor to drive the rotor to rotate, achieving the desired effect. Figure 7 The image shows the unmanned flight status.

[0111] Example 2

[0112] This embodiment provides a method for launching a drone from an unmanned aerial vehicle (UAV) using an unmanned aerial vehicle system, which is used to launch a foldable UAV from the unmanned aerial vehicle system in Embodiment 1.

[0113] The ejection method includes:

[0114] Step S1: Load the drone;

[0115] Specifically, the drone is folded and placed into the ejection compartment 5 of the automatic ejection mechanism;

[0116] Step S2: Activate the automatic launch mechanism to accelerate the drone;

[0117] When the exhaust valve 6 is opened, the energy storage chamber 7 releases gas, which pushes the sliding bracket 9 to slide along the extension chamber 4; the sliding bracket 9 drives the drone bracket 10 to move synchronously; the drone bracket 10 pushes the drone to accelerate.

[0118] Step S3: The drone is launched from the cabin;

[0119] Specifically, after the drone carrier 10 separates from the drone, the drone has a certain initial velocity and continues to slide upward in the ejection compartment 5 until it flies out of the ejection compartment 5; thus completing the launch of the drone.

[0120] Furthermore, after the drone is ejected from the cabin, step S4: the drone's rotors deploy;

[0121] Specifically, the rotor arm 3 of the drone rotates and unfolds to a horizontal position relative to the main body 1 of the drone, the rotor of the drone starts to rotate, and the drone enters the flight state.

[0122] In step S1, after the drone is folded, the multiple rotor arms 3 are parallel to each other and retracted below the drone body 1. After the folded drone is loaded into the ejection compartment 5, the rotor arms 3 are pressed against the side wall of the ejection compartment 5 under the elastic force of the torsion spring 203, and the side wall of the ejection compartment 5 limits the multiple rotor arms 3, restricting the rotor arms 3 from rotating relative to the drone body 1.

[0123] Furthermore, in step S1, after the UAV is loaded into place, the receiving interface 301 at the end of the rotor arm 3 engages with the receiving block 1001 on the UAV bracket 10, and the receiving block 1001 is inserted into the receiving interface 301; through the mutual engagement of the receiving block 1001 and the receiving interface 301, the rotation of the folded rotor arm 3 relative to the UAV body 1 is further restricted.

[0124] In step S2, the acceleration process of the drone is as follows:

[0125] Step S21:

[0126] The energy storage chamber 7 releases high-pressure gas: Specifically, high-pressure gas is introduced into the energy storage chamber 7 through the gas inlet 8; the exhaust valve 6 is opened, and the high-pressure gas in the energy storage chamber 7 is released and enters the extension chamber 4.

[0127] It is worth noting that the high-pressure gas mentioned in this invention refers to the gas pressure in the energy storage chamber 7 being higher than the gas pressure in the extension chamber 4 and the ejection compartment 5; the high pressure mentioned in this invention is a relative concept and not a specific pressure value.

[0128] Step S22:

[0129] High-pressure gas propelled the drone to accelerate its glide;

[0130] Specifically, after the high-pressure gas enters the extension chamber 4, it pushes the sliding piston rod 901 inside the extension chamber 4 to slide upward; the sliding bracket 9 is fixedly connected to the UAV bracket 10 through the outer support rod 902, and the sliding bracket 9 and the UAV detachment 10 move synchronously; when the sliding bracket 9 slides upward, it drives the UAV bracket 10 to slide upward in the ejection chamber 5; the UAV bracket 10 pushes the UAV to accelerate in the ejection chamber 5.

[0131] Step S23: The drone carrier 10 separates from the drone;

[0132] like Figure 4 As shown, when the drone carrier 10 slides to its maximum travel, it stops moving due to the limiting effect of the stop part 401; the drone continues to move at its original speed, and the drone separates from the drone carrier 10.

[0133] Step S3: Unmanned Aerial Vehicle Ejection:

[0134] Specifically, the drone is positioned above the drone carrier 10. After the drone carrier 10 separates from the drone, the drone has a certain initial velocity and continues to slide upward in the ejection chamber 5 until it flies out of the ejection chamber 5, thus completing the launch of the drone.

[0135] Furthermore, the drone retains a certain flight speed even after being ejected from the ejection chamber 5.

[0136] Furthermore, in step S4, the deployment process of the UAV's rotor arm 3 is as follows:

[0137] Step S41: After the UAV is ejected from the ejection bay 5, the restriction on the folded rotor arm 3 is released.

[0138] Step S42: When the UAV is in the folded state, the torsion spring 203 is in the compressed state; after the UAV is ejected from the cabin, the torsion spring 203 automatically resets and pushes the second support 208 of the automatic deployment mechanism 2 to rotate relative to the first support 201, thereby driving the rotor arm 3 to deploy through the second support 208.

[0139] Step S43: After the rotor arm 3 is deployed, the second support 208 engages with the first support 201, and the slot 204a of the pawl 204 engages with the sliding rod 205. Further, the pawl 204 pushes the sliding rod 205 down, and the sliding rod 205 presses down the pin 206 and the compression spring 207. The compression spring 207 has an upward elastic force, and the elastic force of the compression spring 207 can push the sliding rod 205 upward, so that the sliding rod 205 abuts against the slot 204a of the pawl 204, restricting the separation of the sliding rod 205 and the pawl 204. At this time, the automatic deployment mechanism 2 is in a locked state.

[0140] Specifically, the elastic modulus of the torsion spring 203 is greater than that of the compression spring 207.

[0141] Specifically, when the rotor arms 3 are deployed, multiple rotor arms 3 are located on the same plane. After the UAV is deployed, the internal control unit controls the rotors to rotate, and the UAV enters flight mode.

[0142] After the rotor arm 3 of the UAV of the present invention is deployed, the downward bending of the rotor arm 3 is restricted by a torsion spring 203, and the upward bending of the rotor arm 3 is restricted by a compression spring 207. That is, when the rotor arm 3 bends downward from a horizontal position, it compresses the torsion spring 203 and is blocked by the elastic force of the torsion spring 203; when the rotor arm 3 bends upward from a horizontal position, it compresses the compression spring 207 and is blocked by the elastic force of the compression spring 203. The rotor arm 3 maintains a stable horizontal position under the combined limiting action of the torsion spring 203 and the compression spring 207.

[0143] Furthermore, when it is necessary to fold the rotor arm 3 of the UAV, pull down the pin 206 to move the sliding rod 205 down and separate it from the pawl 204; at this time, the automatic deployment mechanism 2 is in the unlocked state, and applying external force to the rotor arm 3 can make the second support 208 rotate relative to the first support 201, compress the torsion spring 203, and realize the refolding of the rotor arm 3.

[0144] Compared with the prior art, the technical solution provided in this embodiment has at least one of the following beneficial effects:

[0145] 1. This invention provides an unmanned flight system that combines an automatic catapult mechanism with a catapult-type rotary-wing UAV, enabling the catapult launch of UAVs and allowing the UAVs to quickly enter flight mode after launch.

[0146] 2. The ejection method of the present invention uses high-pressure gas to drive the sliding bracket 9 and the UAV bracket 10 to move at high speed, thereby propelling the UAV to move at high speed, so that the UAV can be ejected from the ejection chamber 5, and the UAV has a certain initial speed when it exits the chamber.

[0147] 3. In the unmanned flight system of the present invention, the cooperation between the receiving block 1001 of the UAV bracket 10 in the ejection compartment 5 and the receiving interface 301 at the end of the rotor arm 3 enables circumferential positioning of the UAV and restricts the circumferential rotational displacement of the UAV.

[0148] 4. The catapult-type rotary-wing UAV of the present invention achieves folding of the UAV's wings by setting a foldable rotor arm 3, and further achieves rapid unfolding of the folded wings by setting a torsion spring 203, so that the UAV has a flight attitude after being ejected from the ejection compartment 5, realizing rapid switching and connection between the UAV's folded state and flight state, and has good take-off convenience.

[0149] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.

Claims

1. An automatically ejected unmanned flight system, characterized in that, include: Unmanned aerial vehicles (UAVs) and automatic catapult mechanisms; The drone in question is a foldable drone; The automatic ejection mechanism includes: an energy storage chamber (7), an ejection compartment (5), and a drone bracket (10); the energy storage chamber (7) provides the power required for ejection; the ejection compartment (5) is cylindrical and is used to load the folded drone; the drone bracket (10) is located inside the ejection compartment (5) and above the energy storage chamber (7); the energy storage chamber (7) can push the drone bracket (10) to slide along the ejection compartment (5); the drone bracket (10) is used to push the drone out of the ejection compartment (5); the drone includes: unmanned aerial vehicles (UAVs). The drone body (1), automatic deployment mechanism (2), and rotor arms (3) are arranged in a folded state. Multiple rotor arms (3) are parallel to each other. Multiple rotor arms (3) are folded under the drone body (1) and can be installed in the ejection compartment (5). The rotor arms (3) are limited by the inner wall of the ejection compartment (5). A receiving block (1001) is fixedly installed above the drone bracket (10). The rotor arms (3) of the drone are provided with a receiving interface (301). The receiving block (1001) and the receiving interface (301) can be assembled with each other. The automatic ejection mechanism further includes: an extension cavity (4) and a sliding bracket (9); the sliding bracket (9) is slidably engaged with the extension cavity (4); the sliding bracket (9) includes: a sliding piston rod (901), an outer support rod (902), and a top plate (903); the sliding piston rod (901) and the outer support rod (902) are parallel to each other and are connected as one unit through the top plate (903); the sliding piston rod (901) extends into the extension cavity (4) and is capable of sliding tightly. The protruding cavity (4) is sealed; the upper end of the outer support rod (902) is fixedly connected to the top plate (903), and the lower end of the outer support rod (902) is fixedly connected to the drone bracket (10); the drone bracket (10) is a circular plate structure; the drone bracket (10) is located between the protruding cavity (4) and the ejection compartment (5); a stop block (401) is provided at the upper end of the protruding cavity (4), and the stop block (401) is used to limit the displacement of the drone bracket (10).

2. The automatic ejection unmanned flight system according to claim 1, characterized in that, An exhaust valve (6) is provided between the energy storage chamber (7) and the extension chamber (4).

3. The automatic ejection unmanned flight system according to claim 2, characterized in that, An air inlet (8) is provided on the energy storage chamber (7), and the air inlet (8) is used to fill the energy storage chamber (7) with air.

4. A method for launching an unmanned aerial vehicle (UAV) into an unmanned flight system, characterized in that, The unmanned aerial vehicle system according to any one of claims 1-3 is used to launch a foldable unmanned aerial vehicle; the launch method includes: Step S1: Load the drone; Specifically, the drone is folded and placed into the ejection compartment (5) of the automatic ejection mechanism; Step S2: Activate the automatic launch mechanism to accelerate the drone; The exhaust valve (6) opens, the energy storage chamber (7) releases gas, and pushes the sliding bracket (9) to slide along the extension chamber (4); the sliding bracket (9) drives the UAV bracket (10) to move synchronously; the UAV bracket (10) pushes the UAV to accelerate. Step S3: The drone is launched from the cabin; Specifically, after the drone carrier (10) separates from the drone, the drone has an initial velocity and continues to slide upward in the ejection compartment (5) until it flies out of the ejection compartment (5); thus completing the launch of the drone.

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