Energy storage mechanism of unmanned aerial vehicle simulation launching device and simulation launching device

Abstract

The utility model discloses an unmanned vehicle simulation launching device's energy storage mechanism and simulation launching device relates to simulation unmanned vehicle launching technical field, and unmanned vehicle simulation launching device's energy storage mechanism includes fixed connecting rod and energy storage mechanism, and fixed connecting rod is used for with power mechanism connection, and energy storage mechanism includes elastic member and elastic element, and the first end of elastic member forms the sliding connection with fixed connecting rod, and the second end of elastic member is used for with unmanned vehicle contact, and the limit portion is on elastic member, and elastic element is set on elastic member, and fixed connecting rod can be close to limit portion and compress elastic element under the drive of power mechanism, and the elastic force of compressed elastic element can be used to the elastic member to eject the unmanned vehicle in the release state, and simulation launching device includes unmanned vehicle simulation launching device's energy storage mechanism, power mechanism and locking mechanism. The utility model will external force into elastic force, and the impact force of the instantaneous launching of unmanned vehicle is improved.

Description

Technical Field

[0001] This utility model relates to the field of simulated unmanned aerial vehicle (UAV) launch technology, and in particular to an energy storage mechanism and a simulated launch device for a UAV launch simulator. Background Technology

[0002] Unmanned aerial vehicles (UAVs) can be launched from land, water, or air. Depending on the type of UAV, launch method, and launch procedure, the functions simulated by the UAV simulator will also differ. Since there are many ways to launch UAVs, simulators are built to study different stages of the launch process for research, observation, and learning.

[0003] Most existing simulation devices use a power unit to directly drive the UAV for launch, such as a hydraulic cylinder directly connected to the UAV, which drives the launch by extending and retracting. This results in a relatively small force on the UAV at the moment of launch, failing to achieve the required high-intensity explosive force. Therefore, there is an urgent need for an energy storage mechanism and a simulated launch device for UAVs to solve these problems. Utility Model Content

[0004] The purpose of this invention is to provide an energy storage mechanism and a simulated launch device for unmanned aerial vehicles (UAVs) to solve the problems existing in the prior art and improve the impact force on the UAV at the moment of launch.

[0005] To achieve the above objectives, this utility model provides the following solution:

[0006] This utility model provides an energy storage mechanism for an unmanned aerial vehicle (UAV) simulated launch device, comprising:

[0007] A fixed link, which is used to connect to the power mechanism;

[0008] An energy storage mechanism includes a launcher and an elastic element. The first end of the launcher is slidably connected to the fixed link, and the second end of the launcher is used to contact the unmanned aerial vehicle (UAV) in a locked state. A limiting part is fixedly provided on the launcher. The elastic element is sleeved on the launcher located between the fixed link and the limiting part. The fixed link can approach the limiting part and compress the elastic element under the drive of the power mechanism. The launcher can eject the UAV in a released state by the elastic force of the compressed elastic element.

[0009] In one embodiment, the device further includes a positioning bushing fixedly connected inside the fixed connecting rod, the ejector being slidably connected inside the positioning bushing, and the elastic element being located between the positioning bushing and the limiting member and limited by the positioning bushing and the limiting member.

[0010] In one embodiment, the limiting part is a spring pin fixedly sleeved on the ejector component, the spring pin is sleeved on the end of the ejector component near the unmanned aerial vehicle, and the spring pin is connected to the end of the elastic element away from the positioning bushing.

[0011] In one embodiment, the spring pin is made of a rigid material.

[0012] In one embodiment, a slider is fixedly connected to the end of the fixed link, the slider is slidably connected to a slide rail, the slide rail is parallel to the axial direction of the ejector, and the axial direction of the ejector is parallel to the axial direction of the elastic element.

[0013] In one embodiment, the ejector is an ejector spindle.

[0014] In one embodiment, the fixed connecting rod is fixedly connected to a power connecting plate, and a power connecting sleeve is fixedly connected to the power connecting plate.

[0015] In one embodiment, the power connection plate and the fixed connecting rod are fixedly connected by bolts.

[0016] This utility model also provides an unmanned aerial vehicle (UAV) simulation launch device, including a power mechanism fixedly connected to the power connection sleeve; a locking mechanism for locking and releasing the UAV; and an energy storage mechanism for the UAV simulation launch device.

[0017] In one embodiment, the power mechanism is a hydraulic pump, and the hydraulic rod of the hydraulic pump is connected to the power connection sleeve.

[0018] The present invention achieves the following technical advantages over the prior art:

[0019] The energy storage mechanism of the unmanned aerial vehicle (UAV) simulation launch device provided by this utility model, when simulating the ejection of an UAV, provides a power mechanism that pushes the fixed connecting rod to compress the elastic element sleeved on the ejection component. When the compression reaches a certain level, the restriction on the UAV is removed, and the elastic force generated by the compression of the elastic element will eject the UAV instantly.

[0020] This invention converts the applied thrust into the elastic force of the elastic element after an external force is applied to the fixed connecting rod. The elastic force then becomes the power source to provide a power source for the launch of the simulated unmanned aerial vehicle. The applied external force is converted into the required high-strength elastic force, thus completing the storage and conversion of energy and improving the impact force at the moment of launch of the unmanned aerial vehicle. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 A schematic diagram of the energy storage mechanism of the unmanned aerial vehicle simulation launch device provided by this utility model;

[0023] In the diagram: 1-fixed connecting rod, 2-slider, 3-ejector, 4-elastic element, 5-positioning bushing, 6-spring pin, 7-power connection plate, 8-power connection sleeve. Detailed Implementation

[0024] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0025] The purpose of this invention is to provide an energy storage mechanism and a simulated launch device for an unmanned aerial vehicle (UAV) to solve the problems existing in the prior art, so as to transform the applied force with a relatively slow extension speed into a high-intensity explosive force.

[0026] To make the above-mentioned objectives, features and advantages of this utility model more apparent and understandable, the utility model will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0027] Example 1

[0028] like Figure 1As shown, this embodiment provides an energy storage mechanism for a simulated launch device for unmanned aerial vehicles (UAVs), including a fixed link 1 and an energy storage mechanism. The fixed link 1 is used to connect with a power mechanism. The energy storage mechanism includes a launcher 3 and an elastic element 4. The first end of the launcher 3 is slidably connected to the fixed link 1, and the second end of the launcher 3 is used to contact the UAV in a locked state. A limiting part is fixedly provided on the launcher 3. The elastic element 4 is sleeved on the launcher 3 located between the fixed link 1 and the limiting part. Under the drive of the power mechanism, the fixed link 1 can approach the limiting part and compress the elastic element 4. The launcher 3, under the elastic force of the compressed elastic element 4, can launch the UAV in a released state.

[0029] In this embodiment, when the unmanned aerial vehicle (UAV) simulation launch device is used to simulate the launch of an UAV, the energy storage mechanism provides a power mechanism that pushes the fixed link 1 to compress the elastic element 4 on the launch component 3. When the compression reaches a certain level, the restriction on the UAV is lifted, and the elastic force generated by the compression of the elastic element 4 will launch the UAV instantly.

[0030] In this embodiment, after an external force is applied to the fixed connecting rod, the applied thrust is converted into the elastic force of the elastic element 3. The elastic force becomes the power source to provide power for the launch of the simulated unmanned aerial vehicle. The applied external force is converted into the required high-strength elastic force, completing the storage and conversion of energy, thereby increasing the impact force on the unmanned aerial vehicle at the moment of launch.

[0031] In one embodiment, the energy storage mechanism of the unmanned aerial vehicle simulation launch device further includes a positioning sleeve 5 fixedly connected inside the fixed link 1, an ejector 3 is slidably connected inside the positioning sleeve 5, and an elastic element 4 is located between the positioning sleeve 5 and the limiting element and is limited by the positioning sleeve 5 and the limiting element.

[0032] The positioning bushing 5 can limit the ejector 3. When the ejector 3 pushes the unmanned aerial vehicle with the movement of the fixed link 1, the elastic element 4 is compressed, and the thrust provided by the power mechanism is converted into the elastic force of the elastic element 4 for storage.

[0033] Furthermore, the elastic element 4 can be a spring.

[0034] In one embodiment, the limiting part is a spring pin 6 fixedly sleeved on the ejector 3. The spring pin 6 is sleeved on the end of the ejector 3 near the unmanned aerial vehicle, and the spring pin 6 is connected to the end of the elastic element 4 away from the positioning sleeve 5.

[0035] On the one hand, the spring pin 6 can limit the elastic element, and on the other hand, the spring pin 6 absorbs the small impact or high frequency vibration at the moment the spring force is suddenly released. It disperses and transmits the huge concentrated force of the elastic element 4 through its contact surface with the ejector 3, which helps to improve the stress state of the ejector 3, reduce stress concentration points, and improve the fatigue life and reliability of the ejector 3 and the entire mechanism.

[0036] In one embodiment, the spring pin 6 is made of a rigid material.

[0037] The spring pin 6 is made of rigid material (usually high-strength alloy steel or tool steel). During the ejection process, huge impact force, acceleration and vibration will be generated instantly. The rigid material has extremely high yield strength and tensile strength, which can withstand these extreme loads without plastic deformation or fracture.

[0038] In one embodiment, a slider 2 is fixedly connected to the end of the fixed link 1. The slider 2 is slidably connected to the slide rail, which is parallel to the axial direction of the ejector 3, and the axial direction of the ejector 3 is parallel to the axial direction of the elastic element 4.

[0039] Slide 2 is fitted onto the slide rail, which drives the entire fixed connecting rod 1 to move, thus limiting the entire structure and preventing deviation.

[0040] In one embodiment, the ejector 3 is the ejection spindle.

[0041] In one embodiment, a power connection plate 7 is fixedly connected to a fixed connecting rod 1, and a power connection sleeve 8 is fixedly connected to the power connection plate 7.

[0042] The power connection plate 7 is used to connect the entire power connection sleeve 8 to the fixed connecting rod 1.

[0043] In one embodiment, the power connection plate 7 is fixedly connected to the fixed connecting rod 1 by bolts.

[0044] Using bolts for connection makes it easy to replace and disassemble the power connection plate 7, simplifying the overall maintenance difficulty and reducing maintenance costs.

[0045] The hydraulic pump, through precise oil circuit control, drives the hydraulic cylinder and hydraulic rod to perform explosive linear motion. Energy is efficiently transferred to the energy storage mechanism via the power connection sleeve 8, ultimately propelling the unmanned aerial vehicle away from the launch device with controllable high acceleration. Other power supply methods can also be used; the hydraulic pump is just one example, such as electric telescopic masts, pneumatic cylinders, and other structures capable of propulsion.

[0046] Example 2

[0047] This embodiment provides an unmanned aerial vehicle (UAV) simulation launch device, including a power mechanism, a locking mechanism, and an energy storage mechanism of the UAV simulation launch device in Embodiment 1. The power mechanism is connected to the power connection sleeve 8, and the locking mechanism is used to lock and release the UAV.

[0048] In one embodiment, the power mechanism is a hydraulic pump, and the hydraulic rod of the hydraulic pump is connected to the power connection sleeve 8.

[0049] In some implementations, the power mechanism drives the fixed linkage 1 to convert energy into the elastic potential energy of the energy storage mechanism, and then releases the locking mechanism from the unmanned aerial vehicle (UAV), ejecting the UAV. The locking mechanism can be of various types, such as mechanical clamping, electromagnetic clamping, or hydraulic clamping. When the elastic element 4 is compressed to a certain degree, the locking mechanism is operated to release the UAV from its restraint, allowing the elastic force of the elastic element 4 to eject the UAV.

[0050] Work process:

[0051] A hydraulic pump (or other thrust-providing method) is used as the power supply mechanism. The output end of the power mechanism is connected to the power connection sleeve 8, and the sliders 2 at both ends of the fixed connecting rod 1 are sleeved on the slide rail. At the same time, the unmanned aerial vehicle is clamped by the locking mechanism, the ejector 3 contacts the unmanned aerial vehicle, and the power connection sleeve 8 is moved by the power mechanism. The power connection plate 7 and the fixed connecting rod 2, which are fixed to the power connection sleeve 8, will also move under the push of the power mechanism. At this time, the sliders 2 will slide on the slide rail.

[0052] When the fixed link 2 is pushed by the hydraulic pump, the ejector 3 will slide in the positioning sleeve 5, so that the entire ejector 3 compresses the elastic element 4. When a certain amount of compression is reached, the locking mechanism is opened, the limit on the unmanned aerial vehicle is removed, and the elastic force of the elastic element 4 becomes the power source to provide power for the launch of the simulated unmanned aerial vehicle, and the simulated launch of the unmanned aerial vehicle is carried out.

[0053] This utility model uses specific examples to illustrate its principles and implementation methods. The above description of the embodiments is only for the purpose of helping to understand the method and core idea of ​​this utility model. At the same time, for those skilled in the art, there will be changes in the specific implementation methods and application scope based on the idea of ​​this utility model. In summary, the content of this specification should not be construed as a limitation of this utility model.

Claims

1. An energy storage mechanism for an unmanned aerial vehicle (UAV) simulated launch device, characterized in that, include: A fixed link, which is used to connect to the power mechanism; An energy storage mechanism includes a launcher and an elastic element. The first end of the launcher is slidably connected to the fixed link, and the second end of the launcher is used to contact the unmanned aerial vehicle (UAV) in a locked state. A limiting part is fixedly provided on the launcher. The elastic element is sleeved on the launcher located between the fixed link and the limiting part. Under the drive of the power mechanism, the fixed link can approach the limiting part and compress the elastic element. The launcher can eject the UAV in a released state by the elastic force of the compressed elastic element.

2. The energy storage mechanism of the unmanned aerial vehicle simulated launch device according to claim 1, characterized in that: It also includes a positioning bushing fixedly connected inside the fixed connecting rod, the ejector being slidably connected inside the positioning bushing, and the elastic element being located between the positioning bushing and the limiting part and limited by the positioning bushing and the limiting part.

3. The energy storage mechanism of the unmanned aerial vehicle simulation launch device according to claim 2, characterized in that: The limiting part is a spring pin fixedly sleeved on the ejector component. The spring pin is sleeved on the end of the ejector component near the unmanned aerial vehicle, and the spring pin is connected to the end of the elastic element away from the positioning bushing.

4. The energy storage mechanism of the unmanned aerial vehicle simulation launch device according to claim 3, characterized in that: The spring pin is made of a rigid material.

5. The energy storage mechanism of the unmanned aerial vehicle simulation launch device according to claim 1, characterized in that: The end of the fixed connecting rod is fixedly connected to a slider, which is slidably connected to a slide rail. The slide rail is parallel to the axial direction of the ejector, and the axial direction of the ejector is parallel to the axial direction of the elastic element.

6. The energy storage mechanism of the unmanned aerial vehicle simulated launch device according to claim 1, characterized in that: The ejector component is the ejector spindle.

7. The energy storage mechanism of the unmanned aerial vehicle simulated launch device according to claim 1, characterized in that: The fixed connecting rod is fixedly connected to a power connecting plate, and the power connecting plate is fixedly connected to a power connecting sleeve.

8. The energy storage mechanism of the unmanned aerial vehicle simulation launch device according to claim 7, characterized in that: The power connection plate and the fixed connecting rod are fixedly connected by bolts.

9. A simulated launch device for an unmanned aerial vehicle, characterized in that, include: A power mechanism, which is fixedly connected to the power connection sleeve; A locking mechanism for locking and releasing the unmanned aerial vehicle; And the energy storage mechanism of the unmanned aerial vehicle simulation launch device according to any one of claims 1-8.

10. The unmanned aerial vehicle simulation launch device according to claim 9, characterized in that: The power mechanism is a hydraulic pump, and the hydraulic rod of the hydraulic pump is connected to the power connection sleeve.

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