Unmanned aerial vehicle mission load locking device
By designing a drone mission payload locking device, and utilizing the cooperation of a limit rod and a pusher, the problem of excessive load causing damage to the mission payload during launch was solved, achieving the effect of stable drone launch and angle adjustment.
Patent Information
- Application Number
- CN202423108891.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-17
- Publication Date
- 2025-10-31
- Estimated Expiration
- 2034-12-17
AI Technical Summary
The problem of drone mission payloads being damaged due to excessive load during launch.
A UAV mission payload locking device was designed, including a locking mechanism and cooperating components. Through the cooperation of a limit rod and a pusher, the movement of the mission payload is restricted at the moment of launch to avoid excessive load. After the UAV flies smoothly, the device is unlocked for angle adjustment.
This effectively prevents damage to the angle adjustment structure between the mission payload and the UAV body during launch, ensuring a smooth launch of the UAV and enabling angle adjustment during flight.
Smart Images
Figure CN223494774U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a UAV mission payload locking device. Background Technology
[0002] With the advancement of science and technology and the rapid development of drones, drones have been widely used in surveying, agriculture, firefighting, and national defense. For example, payloads such as cameras, spraying equipment, or weapons are mounted on the underside of the drone. The payload and the drone itself typically have angle adjustment devices such as azimuth motors, pitch motors, or gear structures. When a rotary-wing drone launches from its launch tube, the high speed at launch places a significant load on the payload's angle adjustment device, potentially leading to damage. Utility Model Content
[0003] The main purpose of this invention is to provide a drone mission load locking device, which aims to prevent excessive load on the mission load when the drone is launched from the launch tube.
[0004] To achieve the above objectives, the UAV mission payload locking device proposed in this utility model includes:
[0005] A locking mechanism includes a mounting bracket, a pushing member, and a limiting rod. The pushing member is disposed on the mounting bracket, which has a limiting groove. The groove wall of the limiting groove has a through hole. The limiting rod is slidably mounted on the mounting bracket and can slide through the through hole into the limiting groove, or slide to a position spaced apart from the limiting groove. The pushing member is drively connected to the limiting rod, and the pushing member is at least used to drive the limiting rod to a position spaced apart from the limiting groove.
[0006] The mating component includes a fixing part and a limiting part. The fixing part is used to fix the component to the functional component. The mating component has a locked position and an unlocked position. In the locked position, the limiting part is located in the limiting groove. In the unlocked position, the limiting part is spaced apart from the limiting groove. In the locked position, when the limiting rod is located in the limiting groove, the limiting rod abuts against the limiting part to restrict the mating component from moving from the locked position to the unlocked position.
[0007] Optionally, the pusher is spaced apart from the limiting rod in a direction perpendicular to the movement of the limiting rod. The pusher has a push rod with a first abutment portion and the limiting rod has a second abutment portion. A transmission plate is sleeved on the push rod and the limiting rod. One side of the transmission plate abuts against the first abutment portion and the other side abuts against the second abutment portion.
[0008] Optionally, the pushing element is a push-pull electromagnet, and the moving iron core of the push-pull electromagnet is a push rod.
[0009] Optionally, the mounting bracket includes a first plate, a second plate, and a third plate. The first plate is used to mount on the drone body, the second plate is detachably mounted on the first plate, and the third plate is detachably mounted on the third plate. The pushing member is disposed on the second plate, and the limiting groove is disposed on the third plate.
[0010] Optionally, the second plate is provided with a first abutting plate and a second abutting plate, the first abutting plate and the second abutting plate are spaced apart in the horizontal direction, and the gap between the first abutting plate and the second abutting plate forms the limiting groove.
[0011] Optionally, the first plate, the second plate, and the third plate are fixed by threaded fasteners.
[0012] Optionally, in the locked position, the mating component is located above the bottom wall of the limiting groove.
[0013] Optionally, the mounting bracket is made of metal.
[0014] A drone includes a drone body, a payload, and a drone payload locking device as described above. The payload is movably mounted on the drone body, the mating component is mounted on the payload, the mounting bracket is fixed to the drone body, and the drone body or the drone payload locking device is provided with an electronic control device. The pushing component is electrically connected to the electronic control device.
[0015] This utility model's technical solution involves setting a locking mechanism and cooperating components. The locking mechanism includes a mounting frame, a pushing component, and a limiting rod. The mounting frame has a limiting groove, and the limiting rod is slidably mounted on the mounting frame and can slide into the limiting groove. The cooperating components have a fixing part and a limiting part, which fix the mounting frame to the UAV. The cooperating components are fixed to the functional components through the fixing part, and the fixing structure has a locking position and an unlocking position. In the locking position, the limiting part is located in the limiting groove. In the unlocking position, the limiting part is spaced apart from the limiting groove. When the limiting part is in the locking position and the limiting rod is in the limiting groove, the limiting rod abuts against the limiting part to restrict the cooperating components from moving from the locking position to the unlocking position, and the mission load is also limited. Before the drone is launched from the launch tube, the limiting rod can move into the limiting groove, restricting the movement of the mating components from the locked position to the unlocked position. At the moment of launch, the drone's launch speed is relatively high, and the fixed structure is limited, thus limiting the payload as well. This prevents damage to the angle adjustment structure between the payload and the drone body due to excessive load. After the drone completes launch and enters a stable flight state, the pushing component can push the limiting rod out of the limiting groove, allowing the limiting part to move out of the groove. The mating components can then move from the locked position to the unlocked position, enabling angle adjustment of the payload. Attached Figure Description
[0016] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art 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 the structures shown in these drawings without creative effort.
[0017] Figure 1 This is a schematic diagram of the structure of an embodiment of the UAV mission payload locking device of this utility model;
[0018] Figure 2 for Figure 1 A schematic diagram of the structure of the mating components moving from the locked position to the unlocked position;
[0019] Figure 3 for Figure 1 Structural diagram of the pusher and the limiting rod;
[0020] Figure 4 for Figure 1 A schematic diagram of a structure in which the mating component is installed on a functional component and located in the locking position;
[0021] Figure 5 for Figure 4 A schematic diagram of the structure in which the connecting parts move to the unlocking position.
[0022] Explanation of icon numbers:
[0023] label name label name 10 Locking mechanism 1211 First landing section 11 Mounting rack 13 Limit bar 111 First plate 131 Second landing section 112 Second plate 14 Transmission plate 113 Third plate 20 mating parts 1131 Limiting groove 21 Fixing part 1132 First contact plate 22 Limiting part 1133 Second abutment plate 30 Functional components 12 Push component 40 drone mount 121 push rod
[0024] The realization of the purpose, functional features and advantages of this utility model will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation
[0025] 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.
[0026] It should be noted that if the embodiments of this utility model involve directional indicators (such as up, down, left, right, front, back, etc.), the directional indicators are only used to explain the relative positional relationship and movement of the components in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indicators will also change accordingly.
[0027] Furthermore, if the embodiments of this utility model involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the word "and / or" throughout the text means including three parallel solutions. For example, "A and / or B" includes solution A, solution B, or a solution that simultaneously satisfies A and B. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed by this utility model.
[0028] This utility model proposes a drone mission payload locking device.
[0029] In the embodiments of this utility model, such as 1 to Figure 5As shown, the UAV mission payload locking device includes a locking mechanism 10 and a cooperating component 20. The locking mechanism 10 includes a mounting frame 11, a pusher 12, and a limiting rod 13. The pusher 12 is mounted on the mounting frame 11, which has a limiting groove 1131. The groove wall of the limiting groove 1131 has a through hole. The limiting rod 13 is slidably mounted on the mounting frame 11 and can slide through the through hole into the limiting groove 1131, or slide to a position spaced apart from the limiting groove 1131. The pusher 12 is drively connected to the limiting rod 13. The pusher 12 is at least used for driving... The movable limit rod 13 is spaced apart from the limit groove 1131; the mating component 20 is provided with a fixing part 21 and a limiting part 22. The fixing part 21 is used to fix it to the functional component 30. The mating component 20 has a locked position and an unlocked position. In the locked position, the limiting part 22 is located in the limit groove 1131. In the unlocked position, the limiting part 22 is spaced apart from the limit groove 1131. In the locked position, when the limiting rod 13 is located in the limit groove 1131, the limiting rod 13 abuts against the limiting part 22 to restrict the mating component 20 from moving from the locked position to the unlocked position.
[0030] Specifically, the mounting bracket 11 is used to fix the UAV body. The lower end of the UAV body is provided with a movable mission payload. The mating component 20 is fixed to the mission payload. The UAV body or the UAV mission payload locking device is provided with an electronic control device. The pusher 12 is electrically connected to the electronic control device. Before the UAV body is launched through the launch tube, the mating component 20 is in the locked position. By sliding the limit rod 13 into the limit groove 1131, the limit part 22 is limited, so that the mating component 20 cannot move from the limit position to the unlock position. After the UAV is launched through the launch tube and before it flies smoothly, the limit rod 13 will limit the limit part 22, so that the mission payload cannot move, avoiding a large load on the adjustment structure between the UAV body and the mission payload. When the UAV body enters a stable flight state, the electronic control device controls the pusher 12 to push the limit rod 13 at the limit hole, so that the limit part 22 can move to the unlock position, so that the adjustment structure can adjust the angle of the mission payload.
[0031] This utility model's technical solution involves setting a locking mechanism 10 and a cooperating component 20. The locking mechanism 10 includes a mounting frame 11, a pushing component 12, and a limiting rod 13. The mounting frame 11 has a limiting groove 1131, and the limiting rod 13 is slidably mounted on the mounting frame 11 and can slide into the limiting groove 1131. The cooperating component 20 has a fixing part 21 and a limiting part 22, which fix the mounting frame 11 to the UAV. The cooperating component 20 is fixed to the functional component 30 through the fixing part 21, and the fixing structure has a locking position and an unlocking position. In the locking position, the limiting part 22 is located in the limiting groove 1131. In the unlocking position, the limiting part 22 is spaced apart from the limiting groove 1131. When the limiting part 22 is in the locking position and the limiting rod 13 is in the limiting groove 1131, the limiting rod 13 abuts against the limiting part 22 to restrict the cooperating component 20 from moving from the locking position to the unlocking position, and the mission load is also limited.
[0032] Before the drone is launched through the launch tube, the limiting rod 13 can be moved into the limiting groove 1131 to restrict the mating component 20 from moving from the locked position to the unlocked position. When the drone is launched through the launch tube, the launch speed of the drone is relatively fast, so the fixed structure is limited, and the mission load is also limited, thereby avoiding damage to the angle adjustment structure between the mission load and the drone body due to large load.
[0033] After the UAV completes launch and enters a stable flight state, the pusher 12 can push the limit rod 13 out of the limit groove 1131, so that the limit part 22 can move out of the limit groove 1131, and the cooperating component 20 can move from the locked position to the unlocked position, and the mission payload can be adjusted in angle.
[0034] In some embodiments, the pusher 12 is spaced apart from the limit rod 13 in a direction perpendicular to the movement of the limit rod 13. The pusher 12 has a push rod 121, which has a first abutment portion 1211. The limit rod 13 has a second abutment portion 131. The push rod 121 and the limit rod 13 are fitted with a transmission plate 14. One side of the transmission plate 14 abuts against the first abutment portion 1211, and the other side abuts against the second abutment portion 131. Specifically, when it is necessary to move the limiting rod 13 to the spaced limiting groove 1131, the pushing member 12 pushes the rod 121. The pushing rod 121 pushes the transmission plate 14 through the first abutting surface, causing the transmission plate 14 to move. The transmission plate 14 pushes the second abutting part 131, thereby causing the limiting rod 13 to move to the spaced ...
[0035] In some embodiments, the pusher 12 is a push-pull electromagnet, and the moving iron core of the push-pull electromagnet is a push rod 121. Specifically, the push-pull electromagnet has a faster response speed, which allows the limiting rod 13 to move more quickly. Furthermore, the moving iron core is provided with an elastic element, which has elastic deformation to keep the moving iron core in an extended state. When the moving iron core is extended, the elastic element will limit the moving iron core, thus keeping the limiting rod 13 in a state spaced apart from the limiting groove 1131. This prevents the limiting rod 13 from moving into the limiting groove 1131 and affecting the mating component 20 when the UAV is flying smoothly.
[0036] In some embodiments, the mounting bracket 11 includes a first plate 111, a second plate 112, and a third plate 113. The first plate 111 is mounted on the drone body, the second plate 112 is detachably mounted on the first plate 111, and the third plate 113 is detachably mounted on the third plate 113. A pusher 12 is disposed on the second plate 112, and a limiting groove 1131 is disposed on the third plate 113. Specifically, the first plate 111, the second plate 112, and the third plate 113 are detachably assembled together to form the mounting bracket 11, which facilitates storage of the mounting bracket 11 when not in use. Moreover, this avoids directly molding the entire mounting bracket 11 during the molding process. Furthermore, when the pusher 12 or the limiting rod 13 is damaged, the third plate 113 or the second plate 112 can be directly disassembled for repair or replacement, avoiding the need to disassemble the entire mounting bracket 11, making it more convenient for users.
[0037] In some embodiments, the second plate 112 is provided with a first abutment plate 1132 and abutment plate 1133, which are spaced apart in the horizontal direction, and the gap between the first abutment plate 1132 and the second abutment plate 1133 forms a limiting groove 1131. Specifically, by setting the first abutment plate 1132 and the second abutment plate 1133 to form the limiting groove 1131 in this way, compared with forming the limiting groove 1131 directly on the second plate 112, the second plate 112 can be thinner and its weight reduced.
[0038] In some embodiments, the first plate 111, the second plate 112, and the third plate 113 are fixed together by threaded fasteners. Specifically, this allows for easy assembly of the first plate 111, the second plate 112, and the third plate 113 together, and provides a relatively secure fixation while also facilitating disassembly. Alternatively, in other embodiments, snap-fit and slot structures are used to fix the first plate 111, the second plate 112, and the third plate 113.
[0039] In some embodiments, in the locked position, the mating component 20 is located above the bottom wall of the limiting groove 1131. Specifically, when the mating component 20 moves from the locked position to the unlocked position, it moves upwards. This allows the mating component 20 to be installed at the lower rear end of the task load, so that when the rear end of the task load moves upwards, the front end of the task load adjusts its angle downwards. Compared to placing the locking mechanism 10 at the front end of the task load, this avoids the mating component 20 interfering with the functional area of the front end of the task load.
[0040] In some embodiments, the mounting bracket 11 is made of metal. Specifically, when the mounting bracket 11 is made of metal, it has higher strength and greater stability. Furthermore, the mounting bracket 11 is made of aluminum alloy, which makes it lighter than metals such as stainless steel, reducing the load on the drone during flight. In other embodiments, the mounting bracket 11 can be made of plastic.
[0041] This utility model also proposes a drone, which includes a drone body, a mission payload, and a drone mission payload locking device. The specific structure of the drone mission payload locking device is as described in the above embodiments. Since this drone mission payload locking device adopts all the technical solutions of all the above embodiments, it has at least all the beneficial effects brought about by the technical solutions of the above embodiments, and will not be described in detail here. The mission payload includes a drone mount and a functional component 30. A drone mount 40 is rotatably mounted on the drone body, and the functional component 30 is rotatably mounted on the drone mount 40. The mating component 20 is mounted on the functional component 30. The mounting bracket 11 is fixed to the drone body. The drone body or the drone mission payload locking device is provided with an electronic control device, and the pushing component 12 is electrically connected to the electronic control device.
[0042] The above description is only a preferred embodiment of the present utility model and does not limit the patent scope of the present utility model. All equivalent structural transformations made under the inventive concept of the present utility model using the contents of the present utility model specification and drawings, or direct / indirect applications in other related technical fields, are included within the patent protection scope of the present utility model.
Claims
1. A UAV mission payload locking device, characterized in that, include: A locking mechanism includes a mounting bracket, a pusher, and a limiting rod. The pusher is disposed on the mounting bracket, which has a limiting groove. The groove wall of the limiting groove has a through hole. The limiting rod is slidably mounted on the mounting bracket and can slide through the through hole into the limiting groove or slide to a position spaced apart from the limiting groove. The pusher is kinetically connected to the limiting rod, and the pusher is at least used to drive the limiting rod to a position spaced apart from the limiting groove. as well as The mating component includes a fixing part and a limiting part. The fixing part is used to fix it to the functional component. The mating component has a locked position and an unlocked position. In the locked position, the limiting part is located in the limiting groove. In the unlocked position, the limiting part is spaced apart from the limiting groove. In the locked position, when the limiting rod is located in the limiting groove, the limiting rod abuts against the limiting part to restrict the mating component from moving from the locked position to the unlocked position.
2. The UAV mission payload locking device as described in claim 1, characterized in that, The pusher is spaced apart from the limiting rod in a direction perpendicular to the movement of the limiting rod. The pusher has a push rod with a first abutment portion and the limiting rod with a second abutment portion. A transmission plate is sleeved on the push rod and the limiting rod. One side of the transmission plate abuts against the first abutment portion and the other side abuts against the second abutment portion.
3. The UAV mission payload locking device as described in claim 2, characterized in that, The pushing component is a push-pull electromagnet, and the moving iron core of the push-pull electromagnet is a pushing rod.
4. The UAV mission payload locking device as described in claim 1, characterized in that, The mounting bracket includes a first plate, a second plate, and a third plate. The first plate is used to mount the drone body, the second plate is detachably mounted on the first plate, and the third plate is detachably mounted on the third plate. The pushing member is located on the second plate, and the limiting groove is located on the third plate.
5. The UAV mission payload locking device as described in claim 4, characterized in that, The second plate is provided with a first abutting plate and a second abutting plate, the first abutting plate and the second abutting plate are spaced apart in the horizontal direction, and the gap between the first abutting plate and the second abutting plate forms the limiting groove.
6. The UAV mission payload locking device as described in claim 4, characterized in that, The first plate, the second plate, and the third plate are fixed together by threaded fasteners.
7. The UAV mission payload locking device as described in claim 1, characterized in that, In the locked position, the mating component is located above the bottom wall of the limiting groove.
8. The UAV mission payload locking device as described in claim 1, characterized in that, The mounting bracket is made of metal.
9. A drone, characterized in that, The device includes a drone body, a mission payload, and a drone mission payload locking device as described in any one of claims 1 to 8. The mission payload is movably mounted on the drone body, the mating component is mounted on the mission payload, the mounting bracket is fixed to the drone body, and the drone body or the drone mission payload locking device is provided with an electronic control device. The pushing component is electrically connected to the electronic control device.