A multi-point launching mechanism for unmanned aerial vehicles

Abstract

The utility model discloses a kind of unmanned aerial vehicle multi-point delivery mechanism, belong to cabinet rack technical field, comprising: unmanned aerial vehicle body, mounting mechanism, delivery unit is delivered object;The mounting mechanism is arranged below unmanned aerial vehicle body;The delivery unit has several, is installed on mounting mechanism, and delivery unit includes rigid fixed structure, electromagnetic release device, and the same control circuit control between the multiple units of the electromagnetic release device, realizes synchronous power-off release;The delivered object is provided with magnetic interface, and the magnetic interface is magnetically attracted and connected with electromagnetic release device when energization;The rigid fixed structure fixes the delivered object in flight, and is released before delivery;The electromagnetic release device magnetically attracts and connects the delivered object before the rigid fixed structure release. The utility model is fixed with mounting in flight using rigid structure, switches to electromagnetic adsorption before delivery, FPGA control unified power-off, completes synchronous delivery, keeps barycenter stable and attitude constant.

Description

Technical Field

[0001] This utility model relates to the field of drone deployment technology, specifically to a drone multi-point deployment mechanism. Background Technology

[0002] With the increasing demand in scenarios such as logistics delivery, agricultural seeding, and disaster relief, multi-point delivery technology using drones has received widespread attention. Currently, mainstream multi-point delivery methods mostly employ motor-driven hooks, mechanical latches, and servo motors for release. These methods suffer from problems such as complex mechanisms, inability to achieve simultaneous multi-point delivery, and unstable release attitude, making it difficult to meet the requirements for high reliability and high precision delivery. Utility Model Content

[0003] The purpose of this utility model is to provide a multi-point delivery mechanism for drones to solve the above problems. It can rigidly fix multiple objects to be delivered during flight, switch the connection method to electromagnetic connection before delivery, and achieve multi-point synchronous release through centralized power-off control. At the same time, it ensures that the delivered objects are stable in attitude when they leave the drone, avoiding tumbling or deviation.

[0004] Technical Solution: This utility model provides a multi-point delivery mechanism for unmanned aerial vehicles (UAVs), including: a UAV body, a mounting mechanism, and delivery units containing the delivered object; the mounting mechanism is located below the UAV body; several delivery units are mounted on the mounting mechanism, each delivery unit including a rigid fixing structure and an electromagnetic release device; multiple units of the electromagnetic release device are controlled by the same control circuit to achieve synchronous power-off release; the delivered object is provided with a magnetic interface, which is magnetically connected to the electromagnetic release device when energized; the rigid fixing structure fixes the delivered object during flight and releases it before delivery; the electromagnetic release device magnetically connects to the delivered object before the rigid fixing structure is released.

[0005] Furthermore, in the aforementioned multi-point deployment mechanism for unmanned aerial vehicles, the rigid fixing structure has a triangular layout with two sections in front and one in the back.

[0006] Furthermore, in the aforementioned multi-point delivery mechanism for unmanned aerial vehicles (UAVs), the rigid fixing structure includes a claw and a conical joint. The claw is located below the UAV body, and the conical joint is located above the delivered object. The conical joint and the claw are geometrically interlocked.

[0007] Furthermore, in the aforementioned multi-point delivery mechanism for drones, the gripper is embedded with a pressure sensor for real-time monitoring of the clamping force, and a spring is preloaded at the root of the tapered joint to counteract vibration harmonics.

[0008] Furthermore, in the aforementioned multi-point deployment mechanism for unmanned aerial vehicles, the electromagnetic release device is a ring electromagnet, the main body of which is made of neodymium iron boron material, with a copper coil surrounding the outer ring. The magnetic interface is a magnetic disk, which is precisely aligned with the ring electromagnet. The magnetic disk is made of 316L stainless steel.

[0009] Furthermore, in the aforementioned multi-point delivery mechanism for unmanned aerial vehicles, the guide disk surface adopts a micro-convex spherical design to compensate for assembly tolerances.

[0010] Furthermore, in the aforementioned multi-point delivery mechanism for unmanned aerial vehicles, the delivery unit is synchronously controlled by an FPGA circuit to ensure that the on / off time difference of the electromagnet is less than 1ms.

[0011] Furthermore, in the aforementioned multi-point delivery mechanism for unmanned aerial vehicles (UAVs), a fairing is provided below the UAV body to cover the object to be delivered below.

[0012] Furthermore, in the aforementioned multi-point delivery mechanism for unmanned aerial vehicles, the delivery unit is equipped with a safety interlock mechanism. The claw is in an open state when releasing the delivered object. After the electromagnet is de-energized and releases the delivered object, the claw self-locks and remains closed. The claw is prohibited from opening until the electromagnet reaches its rated magnetic flux.

[0013] Furthermore, in the aforementioned multi-point deployment mechanism for unmanned aerial vehicles, the annular electromagnet is equipped with a capacitor, maintaining an electromagnetic attraction force for 0.5 seconds after power is cut off. A Hall sensor is installed at the annular electromagnet to detect the magnetic flux in order to dynamically adjust the current balance.

[0014] As can be seen from the above technical solution, the present invention has the following beneficial effects: The multi-point delivery mechanism for UAVs described in the present invention adopts a combination of rigid fixed structure and electromagnetic release device. During flight, the rigid structure is used for fixed mounting, and before delivery, it switches to electromagnetic adsorption. The FPGA controls the unified power-off to complete synchronous delivery, maintain the stability of the center of gravity and the constant attitude. The micro-convex spherical design of the guide disk surface is precisely aligned with the electromagnet to compensate for assembly tolerances. The deflector is set to reduce the impact of the rotor downwash airflow and improve the stability of the delivered object during delivery. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of a multi-point delivery mechanism structure for a drone (multi-rotor vertical take-off and landing drone) according to the present invention; Figure 2 This is a schematic diagram of a multi-point delivery mechanism structure for a drone (fixed-wing drone) according to the present invention; Figure 3 This is a schematic diagram of the rigid fixing structure of this utility model; Figure 4 This is a schematic diagram of the electromagnetic release device of this utility model.

[0016] In the diagram: 1. UAV body; 2. Mounting mechanism; 3. Drop unit; 4. Dropped object; 31. Rigid fixing structure; 32. Electromagnetic release device; 41. Magnetic interface; 311. Claw; 312. Conical connector. Detailed Implementation

[0017] Example 1 like Figure 1-4 The illustrated multi-point delivery mechanism for unmanned aerial vehicles (UAVs) includes: a UAV body 1, a mounting mechanism 2, delivery units 3, and a delivery object 4. The mounting mechanism 2 is located below the UAV body 1. Several delivery units 3 are mounted on the mounting mechanism 2. Each delivery unit 3 includes a rigid fixing structure 31 and an electromagnetic release device 32. Multiple units of the electromagnetic release device 32 are controlled by the same control circuit to achieve synchronous power-off release. The delivery object 4 is equipped with a magnetic interface 41, which magnetically connects to the electromagnetic release device 32 when energized. The rigid fixing structure 31 secures the delivery object 4 during flight and releases it before delivery. The electromagnetic release device 32 magnetically connects to the delivery object 4 before the rigid fixing structure 31 is released. By combining the rigid fixing structure 31 and the electromagnetic release device 32, the rigid structure secures the delivery object during flight, switching to electromagnetic adsorption before delivery. An FPGA controls a unified power-off, completing the synchronous delivery.

[0018] like Figure 1-2 The above describes a multi-point delivery mechanism for drones. The drone body 1 can be either a multi-rotor vertical take-off and landing drone or a fixed-wing drone.

[0019] like Figure 3 The diagram shows a multi-point delivery mechanism for a drone. The rigid fixing structure 31 has a triangular layout with two in front and one in the back. The rigid fixing structure 31 includes claws 311 and a conical joint 312. The claws 311 are located below the drone body 1 and are made of titanium alloy to withstand impact. The conical joint 312 is located above the delivered object 4 and is geometrically interlocked with the claws 311. The conical joint 312 is a carbon fiber rigid joint.

[0020] In this embodiment, the jaw 311 is embedded with a pressure sensor for real-time monitoring of clamping force, and the tapered joint 312 is preloaded with a spring at its root to counteract vibration harmonics.

[0021] Example 2 Based on Example 1, in this example, as... Figure 4The diagram shows a multi-point delivery mechanism for unmanned aerial vehicles (UAVs). The electromagnetic release device 32 is a ring electromagnet with a main body made of neodymium iron boron material and an outer ring of copper coil. The single-point attraction force is greater than 150N. The magnetic interface 41 is a magnetic disk, which is precisely aligned with the ring electromagnet. The magnetic disk is made of 316L stainless steel.

[0022] In this embodiment, the disk surface of the guide disk adopts a micro-convex spherical design with a radius of curvature R of 50±0.1mm to compensate for assembly tolerances.

[0023] In this embodiment, the delivery unit 3 is synchronously controlled by an FPGA circuit to ensure that the time difference between the on and off of the electromagnet is less than 1ms. The delivery unit 3 is equipped with a safety interlock mechanism. The claw 311 is in the open state when releasing the delivered object 4. After the electromagnet is de-energized and releases the delivered object 4, the claw 311 self-locks and remains closed. The claw 311 is prohibited from being opened until the electromagnet reaches the rated magnetic flux.

[0024] In this embodiment, the annular electromagnet is equipped with a capacitor, and maintains an electromagnetic attraction force for 0.5s after power is cut off. A Hall sensor is installed at the annular electromagnet to detect the magnetic flux in order to dynamically adjust the current balance.

[0025] In this embodiment, the delivery unit 3 has an anti-accidental release mechanism. Before the electromagnet reaches full power, the claw 311 is prohibited from opening and there is vibration monitoring. When the acceleration is greater than 5G, the rigid fixing structure 31 automatically switches to clamping mode.

[0026] like Figure 1 The diagram shows a multi-point delivery mechanism for a drone. A fairing is provided below the drone body 1 to cover the object to be delivered below, thereby reducing the impact of the downwash airflow from the rotor on the object to be delivered.

[0027] It should be noted that the above description is merely a technical solution of the utility model and not a limitation. Although the present utility model has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solution of the utility model without departing from the scope of the present utility model, and all such modifications and substitutions should be covered within the scope of the claims of the present utility model.

Claims

1. A multi-point delivery mechanism for unmanned aerial vehicles (UAVs), characterized in that: include: Unmanned aerial vehicle body (1); Mounting mechanism (2), which is located below the body (1) of the UAV; The deployment unit (3) has several units and is installed on the mounting mechanism (2). The deployment unit (3) includes a rigid fixing structure (31) and an electromagnetic release device (32). Multiple units of the electromagnetic release device (32) are controlled by the same control circuit to achieve synchronous power-off release. The object to be placed (4) is provided with a magnetic interface (41), which is magnetically connected to the electromagnetic release device (32) when energized. The rigid fixing structure (31) fixes the dropped object (4) during flight and releases it before dropping; The electromagnetic release device (32) magnetically connects to the object (4) before the rigid fixing structure (31) is released; The rigid fixing structure (31) has a triangular layout, with two in front and one in the back; The rigid fixing structure (31) includes a claw (311) and a tapered joint (312). The claw (311) is located below the drone body (1), and the tapered joint (312) is located above the object to be deployed (4). The tapered joint (312) and the claw (311) are geometrically interlocked. The jaw (311) is embedded with a pressure sensor for real-time monitoring of clamping force, and the tapered joint (312) is preloaded with a spring at its root to counteract vibration harmonics. The electromagnetic release device (32) is a ring electromagnet, the main body is made of neodymium iron boron material, and the outer ring is surrounded by copper coil. The magnetic interface (41) is a magnetic disk, which is precisely aligned with the ring electromagnet. The magnetic disk is made of 316L stainless steel. The delivery unit (3) is synchronously controlled by FPGA circuit to ensure that the time difference between the on and off of the electromagnet is less than 1ms; The delivery unit (3) is equipped with a safety interlock mechanism. The claw (311) is in the open state when the delivered object (4) is released. After the electromagnet is de-energized and the delivered object (4) is released, the claw (311) is self-locked and kept closed. The claw (311) is prohibited from being opened before the electromagnet reaches the rated magnetic flux.

2. The multi-point delivery mechanism for unmanned aerial vehicles according to claim 1, characterized in that: The disk surface of the guide disk adopts a micro-convex spherical design to compensate for assembly tolerances.

3. The multi-point delivery mechanism for unmanned aerial vehicles according to claim 1, characterized in that: A fairing is provided below the body (1) of the drone, which covers the object (4) to be deployed below.

4. The UAV multi-point delivery mechanism according to claim 1, characterized in that: The annular electromagnet is equipped with a capacitor and maintains an electromagnetic attraction force for 0.5 seconds after power is cut off. A Hall sensor is installed at the annular electromagnet to detect the magnetic flux in order to dynamically adjust the current balance.

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