UAV with self-deployable rotor and automatic deployment method thereof

Abstract

This invention relates to a drone with a self-deploying rotor and its automatic deployment method, belonging to the field of rotorcraft drone technology. It solves the problem that existing drones can only be manually folded or deployed, resulting in insufficient ease of takeoff. The invention 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; the automatic deployment mechanism includes: a first support, a rotating spring-opening component, a limiting component, and a second support; the first support is fixedly mounted on the drone body, and the second support is fixedly connected to the rotor arm; the first and second supports are rotatably connected via the rotating spring-opening component; the first and second supports are limited between each other by the limiting component. This invention achieves the automatic deployment of the wings of a foldable drone.

Description

Technical Field

[0001] This invention relates to the field of rotary-wing unmanned aerial vehicle (UAV) technology, and more particularly to a UAV with a self-deploying rotor and its automatic deployment method. Background Technology

[0002] Currently, most rotary-wing drones have fixed arm structures, which are too large and not conducive to carrying or transporting.

[0003] While foldable rotorcraft drones have solved their size problem, they are all manually folded and unfolded. Before taking off, the drones need to be held by hand or placed on the ground, which makes takeoff inconvenient. Therefore, there is a need for a rotorcraft drone that can automatically unfold its arms.

[0004] To address the aforementioned technical issues and solve the problem of foldable rotary-wing drones being unable to automatically unfold their arms, it is necessary to design a drone capable of automatically opening its rotors. Summary of the Invention

[0005] Based on the above analysis, the present invention aims to provide a drone with a self-deploying rotor to solve the problem that existing drones can only be manually folded or unfolded, resulting in insufficient ease of takeoff.

[0006] The objective of this invention is mainly achieved through the following technical solutions:

[0007] A drone with a self-deploying rotor includes: a drone body, an automatic deployment mechanism, and a rotor arm;

[0008] The rotor arm is rotatably mounted on the main body of the UAV via an automatic deployment mechanism;

[0009] The automatic deployment mechanism includes: a first support, a rotating spring-opening assembly, a limiting 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;

[0010] The first support and the second support are rotatably connected by a rotating spring-opening assembly; the first support and the second support are limited by a limiting assembly.

[0011] Furthermore, the rotary spring-opening assembly includes a rotary shaft and a torsion spring.

[0012] Furthermore, the first support and the second support are rotatably connected by a rotating shaft; the torsion spring is sleeved on the rotating shaft and disposed between the first support and the second support, for automatically resetting after the first support and the second support rotate relative to each other.

[0013] Furthermore, the limiting component includes: a claw, a sliding rod, and a pin.

[0014] Furthermore, the pin is slidably mounted inside the first support, and the pawl is fixedly mounted on the second support; the sliding rod moves synchronously with the pin; and the pawl can engage with the sliding rod.

[0015] Furthermore, a compression spring is fitted around the outside of the pin.

[0016] Furthermore, the sliding rod is fixedly installed at the upper end of the pin.

[0017] Furthermore, the compression spring is disposed between the sliding rod and the first support.

[0018] Furthermore, when the pin slides relative to the first support, it can cause the compression spring to compress or extend.

[0019] An automatic deployment method for a UAV with self-deploying rotors, used to achieve the automatic deployment of the rotor arms of the aforementioned UAV with self-deploying rotors;

[0020] The automatic unfolding method includes:

[0021] Step S1: Release the restraints on the folded rotor arm;

[0022] Step S2: The torsion spring automatically resets, thereby causing the rotor arm to unfold;

[0023] Step S3: After the rotor arm is deployed, the pawl's slot engages with the sliding rod, and the automatic deployment mechanism is locked, thus limiting the deployment of the rotor arm.

[0024] The technical solution of this invention can achieve at least one of the following effects:

[0025] 1) This invention achieves the folding and automatic unfolding function of the UAV rotor arm by setting a torsion spring and a limiting component between the first support and the second support.

[0026] 2) This invention reduces the structural size of the UAV by using the folding and automatic unfolding function of the rotor arm, thus achieving the technical effect of portability and rapid take-off of the UAV.

[0027] 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

[0028] 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.

[0029] Figure 1 This is the folded state of the UAV with self-deploying rotors according to the present invention;

[0030] Figure 2 This is the deployed state of the UAV with self-deploying rotors according to the present invention;

[0031] Figure 3 The image shows the placement of the UAV with self-deploying rotors of the present invention inside the launch tube;

[0032] Figure 4 This represents the free rotation state of the automatic deployment mechanism of the present invention;

[0033] Figure 5 This is the folded state of the rotor of the UAV with self-deploying rotor of the present invention;

[0034] Figure 6 The rotor of the UAV with self-deploying rotor of the present invention is in the deployed state;

[0035] Figure 7 Partial cross-sectional view of the locking and limiting state of the automatic deployment mechanism of the present invention;

[0036] Figure 8 This is a top view of the locking and limiting state of the automatic deployment mechanism of the present invention.

[0037] Figure label:

[0038] 1-UAV body; 2-Automatic deployment mechanism; 3-Rotor arm; 4-Hanging bay; 5-Launch tube; 6-Energy storage chamber; 201-First support; 202-Rotation shaft; 203-Torsion spring; 204-Claw; 204a-Slot; 205-Sliding rod; 206-Pin; 207-Compression spring; 208-Second support. Detailed Implementation

[0039] 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.

[0040] Example 1

[0041] One specific embodiment of the present invention discloses a drone with self-deploying rotors, such as... Figure 1 , Figure 2 As shown.

[0042] Specifically, the UAV with self-deploying rotors of the present invention includes: a UAV body 1, an automatic deployment mechanism 2, and rotor arms 3; the rotor arms 3 are rotatably mounted on the UAV body 1 via the automatic deployment mechanism 2. Preferably, four rotor arms 3 are rotatably mounted on the UAV body 1, and the four rotor arms 3 are evenly distributed along the circumferential direction of the UAV body 1. Furthermore, rotors are mounted on the rotor arms 3 for enabling the UAV to fly.

[0043] like Figure 3 As shown, this is the launch-ready state of the UAV of the present invention. When the UAV is folded, it is inserted into the launch tube 5 and can be powered by the energy storage chamber 7. After the UAV is launched from the launch tube 5, its rotor arms 3 will automatically unfold to the desired position under the action of the automatic unfolding mechanism. Figure 2 The unfolded state shown.

[0044] 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.

[0045] Furthermore, a hangar 4 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 4 as needed.

[0046] like Figure 1 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 launch tube 5.

[0047] like Figure 2 As shown, when the rotor arms 3 are deployed, multiple rotor arms 3 are located on the same plane.

[0048] like Figure 4 As shown, the automatic deployment mechanism 2 includes: a first support 201, a rotating spring-opening assembly, a limiting assembly, and a second support 208.

[0049] Specifically, the first support 201 is fixedly installed on the main body 1 of the UAV, 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 a rotating spring-opening assembly; the first support 201 and the second support 208 are limited by a limiting assembly.

[0050] (1) Rotating spring-opening assembly

[0051] In one specific embodiment of the present invention, the rotating spring-opening assembly includes: a rotating shaft 202 and a torsion spring 203.

[0052] Specifically, such as Figure 4As shown, the first support 201 and the second support 208 are rotatably connected by a rotating shaft 202.

[0053] like Figure 5 As shown, the torsion spring 203 is sleeved on the rotating shaft 202 and is disposed between the first support 201 and the second support 208, for the purpose of realizing automatic reset after the first support 201 and the second support 208 rotate relative to each other.

[0054] Specifically, the two ends of the torsion spring 203 abut against the first support 201 and the second support 208, respectively.

[0055] When the first support 201 and the second support 208 rotate relative to each other, the torsion spring 203 is in a compressed state.

[0056] 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.

[0057] like Figure 4 , Figure 5 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.

[0058] like Figure 6 , Figure 7 , Figure 8 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. In the deployed state of the rotor arm 3, 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 torque of the rotor arm 3 on the rotation shaft 202.

[0059] Furthermore, rotors are installed on rotor arm 3 to enable the drone to fly.

[0060] 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.

[0061] 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.

[0062] 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.

[0063] (2) Limiting components

[0064] In one specific embodiment of the present invention, such as Figure 4 As shown, the limiting component includes: a claw 204, a sliding rod 205, a pin 206, and a compression spring 207.

[0065] 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.

[0066] Specifically, the first support 201 is provided with a pin hole, which is a stepped hole.

[0067] 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 4 As shown.

[0068] 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.

[0069] 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.

[0070] 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.

[0071] 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.

[0072] 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. Figure 4 , Figure 8 As shown.

[0073] Specifically, the slot 204a shown is a semi-circular slot, such as... Figure 4 As shown.

[0074] 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 6 As shown.

[0075] 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.

[0076] (3) Working principle:

[0077] Fold the drone's rotor arm 3 into Figure 1 As shown in the diagram, it is placed into launch tube 5. The inner wall of launch tube 5 limits the rotor arm 3, completing the installation of the UAV in the automatic catapult mechanism, achieving the desired result. Figure 3 The state shown.

[0078] Furthermore, using a portable air pump, gas is injected into the energy storage chamber 6 through the air inlet of the launch tube 5 until a specified pressure is reached (set as needed). Opening the exhaust valve releases the high-pressure gas from the energy storage chamber 6, ejecting the drone from the chamber. The drone continues to move upwards at its initial velocity and automatically deploys its rotor arms 3. The control unit then controls the motors to rotate the rotors, achieving the desired speed. Figure 2 The image shows the unmanned flight status.

[0079] Example 2

[0080] In one specific embodiment of the present invention, an automatic deployment method for a UAV with a self-deploying rotor is provided to achieve the automatic deployment of the rotor arm 3 of the UAV with a self-deploying rotor in Embodiment 1.

[0081] The automatic unfolding method includes:

[0082] Step S1: Release the restraints on the folded rotor arm 3;

[0083] Step S2: The torsion spring 203 automatically resets, thereby driving the rotor arm 3 to unfold;

[0084] Step S3: After the rotor arm 3 is deployed, the slot 204a of the pawl 204 engages with the sliding rod 205, and the automatic deployment mechanism 2 is in a locked state, thereby limiting the deployment of the rotor arm 3.

[0085] In step S1, the UAV of the present invention takes off by catapult; when the UAV is in a folded state, it is placed in the launch tube 5, and the launch tube 5 limits the rotor arm 3 to keep it in a folded state. After the UAV is launched out of the tube, the folded state of the UAV is released, and the launch tube 5 can no longer limit the rotor arm 3.

[0086] Furthermore, an energy storage chamber 6 is located below the inside of the launch tube 5, which is used to provide power for the UAV to be ejected from the tube.

[0087] In step S2: when the drone is released from the folded state, the rotor arm 3 can be automatically released and deployed under the elastic force of the torsion spring 203.

[0088] In step S2: the torsion spring 203 drives the second support 208 and the rotor arm 3 to rotate relative to the first support 201, thereby causing the pawl 204 and the sliding rod 205 to gradually come into contact until the sliding rod 205 is engaged in the slot 204a.

[0089] In step S2, as the rotor arm 3 gradually unfolds, the angle between the side of the first support 201 and the side of the second support 208 gradually decreases.

[0090] In step S3, the torsion spring 203 continues to drive the second support 208 to rotate relative to the first support 201, the pawl 204 presses down the sliding rod 205, and then the sliding rod 205 presses down the compression spring 207 and the pin 206 until the rotor arm 3 is perpendicular to the UAV body 1 and the rotor arm 3 is fully extended.

[0091] In step S3, when the rotor arm 3 is fully extended, the side of the first support 201 and the side of the second support 208 are parallel to or fit together.

[0092] Furthermore, when the rotor arm 3 is fully extended, the compression spring 207 is in a compressed state. The compression spring 207 has an upward elastic force, which can push the sliding rod 205 upward, causing the sliding rod 205 to press against the groove 204a of the pawl 204, thus preventing the sliding rod 205 from separating from the pawl 204. At this time, the automatic deployment mechanism 2 is in a locked state. Figure 6-8 As shown.

[0093] When the sliding rod 205 is pressed against the slot 204a of the pawl 204, the first support 201 and the second support 208 cannot rotate relative to each other, thereby restricting the rotor arm 3 from rotating relative to the UAV body 1.

[0094] Compared with the prior art, the technical solution provided in this embodiment has at least one of the following beneficial effects:

[0095] 1. This invention achieves automatic deployment of the UAV rotor arm 3 through a torsion spring. Before launch, the rotor arm 3 is limited by the launch tube 5. After launch, the rotor arm 3 automatically deploys, realizing the immediate deployment of the foldable UAV after launch, which facilitates the take-off of the UAV and is simple to operate.

[0096] 2. The present invention limits the unfolded rotor arm 3 by setting a limiting component on the first support 201, preventing it from rotating, thereby ensuring the stability of the unfolded UAV rotor state.

[0097] 3. The limiting component of the present invention includes a pawl 204, a pin 206, a compression spring 207, and a sliding rod 205. Through the cooperation of the pawl 204 and the sliding pin 205, the connection between the first support 201 and the second support 208 is realized; then, the compression spring 207 provides an upward pressure to prevent the pawl 204 and the sliding rod 205 from separating, and finally restricts the relative rotation of the first support 201 and the second support 208.

[0098] 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. A drone with self-deploying rotors, characterized in that, include: The drone body (1), automatic deployment mechanism (2), and rotor arms (3) are rotatably mounted on the drone body (1) via the automatic deployment mechanism (2). When the rotor arms (3) are folded, multiple rotor arms (3) are parallel to each other. The multiple rotor arms (3) are folded together below the drone body (1). The automatic deployment mechanism (2) includes: a first support (201), a rotation and pop-out assembly, a limiting assembly, and a second support (208). The first support (201) is fixedly mounted on the drone body. On the body (1), 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 a rotating spring assembly; the first support (201) and the second support (208) are limited by a limiting assembly; 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; when the rotor arm (3) is in the unfolded state, the two end faces of the first support (201) and the second support (208) abut against each other; The limiting component includes: a claw (204), a sliding rod (205), and a pin (206); The sliding rod (205) is set perpendicular to the pin (206); the pin (206) is slidably installed inside the first support (201), and the pawl (204) is fixedly installed on the second support (208); the sliding rod (205) moves synchronously with the pin (206); the pawl (204) can engage with the sliding rod (205); a compression spring (207) is sleeved on the outside of the pin (206); when rotated... As the rotor arm (3) gradually extends to the horizontal position, the sliding rod (205), the pin (206), and the compression spring (207) are simultaneously pressed down by the claw (204) on the second support (208). The pin (206) in the first support (201) moves downward, and at the same time, the sliding rod (205) slides into the slot (204a) of the claw (204). The slot (204a) is a semi-circular slot, which realizes the locking and limiting function of the rotor arm (3).

2. The UAV with self-deploying rotors according to claim 1, characterized in that, The rotating spring-opening assembly includes a rotating shaft (202) and a torsion spring (203).

3. The UAV with self-deploying rotors according to claim 2, characterized in that, 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.

4. The UAV with self-deploying rotors according to claim 3, characterized in that, The sliding rod (205) is fixedly installed at the upper end of the pin (206).

5. The UAV with self-deploying rotors according to claim 4, characterized in that, The compression spring (207) is disposed between the sliding rod (205) and the first support (201).

6. The UAV with self-deploying rotors according to claim 5, characterized in that, When the pin (206) slides relative to the first support (201), it can drive the compression spring (207) to compress or extend.

7. An automatic deployment method for a UAV with self-deploying rotors, characterized in that, The method is used to achieve the automatic deployment of the rotor arm (3) of the UAV with self-deploying rotor as described in any one of claims 1-6; the automatic deployment method includes: Step S1: Release the restraints on the folded rotor arm (3); Step S2: The torsion spring (203) automatically resets, thereby driving the rotor arm (3) to unfold; Step S3: After the rotor arm (3) is deployed, the slot (204a) of the pawl (204) engages with the sliding rod (205), and the automatic deployment mechanism (2) is locked, thereby limiting the deployment of the rotor arm (3).

Images