Limiting device and launching simulation device
By using the limiting mechanism and elastic element in the limiting device, the problems of complex structure and safety hazards of unmanned aerial vehicle launch devices are solved, achieving stable locking and safe release of unmanned aerial vehicles, simplifying operation and reducing costs.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- NAVAL AVIATION UNIV
- Filing Date
- 2025-08-29
- Publication Date
- 2026-07-24
AI Technical Summary
Existing unmanned aerial vehicle launch devices are complex in structure and expensive, and cannot maintain a locked state when power is cut off or hydraulic oil is lacking, posing a safety hazard.
The device employs a limiting device, including first and second limiting mechanisms. The locking and releasing of the unmanned aerial vehicle is achieved by utilizing the elastic force of the first elastic element. The release of the unmanned aerial vehicle can be achieved by manually operating the first limiting element to apply force. The structure is simple and the operation is labor-saving.
It achieves stable locking and safe release of unmanned aerial vehicles, simplifies operating procedures, reduces the complexity and cost of the device, and ensures experimental safety.
Smart Images
Figure CN224553931U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of locking mechanism technology, and in particular to a limiting device and a launch simulation device. Background Technology
[0002] An unmanned aerial vehicle (UAV) launcher is a device used to support and launch UAVs. However, UAV launchers are high-end precision equipment. To facilitate public understanding of the UAV launch process and to observe the UAV ejection process in UAV launch research, it is necessary to conduct a physical simulation of the UAV launch process.
[0003] The existing patent (CN110068248A) discloses an automatic release device for launch pads that uses hydraulic oil to drive a piston to achieve locking. This device requires components such as an oil pump and a solenoid valve, which are complex in structure and costly. Furthermore, it cannot maintain the locking state when there is a power outage or a lack of hydraulic oil, posing a safety hazard. Utility Model Content
[0004] The purpose of this invention is to provide a limiting device and a launch simulation device to solve the problems existing in the prior art, making the simulation device simple in structure, easy to operate, and able to ensure experimental safety.
[0005] To achieve the above objectives, this utility model provides the following solution:
[0006] This utility model provides a limiting device for an unmanned aerial vehicle (UAV) launch simulator, including a base and at least one first limiting mechanism. Each first limiting mechanism includes a first limiting element and a first elastic element. One end of the first elastic element abuts against the lower end of the first limiting element, and the other end abuts against the base. The first limiting element is capable of reciprocating between a first position and a second position. The first limiting element has a limiting portion. Under the elastic force of the first elastic element, the first limiting element is in the first position, so that the limiting portion can restrict the movement of the UAV. When the first limiting element is subjected to force and moves towards the base, it can compress the first elastic element and move to the second position. When the first limiting element is in the second position, the limiting portion can disengage from the UAV to release the UAV.
[0007] In some embodiments, the limiting part is a limiting hole provided on the first limiting element. When the first limiting element is in a first position, the limiting hole can engage with the lower part of the limiting groove on the unmanned aerial vehicle. When the first limiting element is in a second position, the limiting hole separates from the limiting groove on the unmanned aerial vehicle and allows the unmanned aerial vehicle to move through it along its launch direction. The moving direction of the first limiting element is perpendicular to the launch direction of the unmanned aerial vehicle.
[0008] In some embodiments, the limiting device further includes a crossbeam and at least one second limiting mechanism. The second limiting mechanism includes a second limiting element and a second elastic element. Both the first limiting element and the second limiting element are fixedly connected to the crossbeam. The second limiting element is vertically movably connected to the base. One end of the second elastic element abuts against the lower end of the second limiting element, and the other end abuts against the base. The crossbeam is able to move closer to the base under force and drive the first limiting element to move closer to the base.
[0009] In some embodiments, the limiting device further includes a force-applying component, which includes a rod, a support rod, and a transmission mechanism. The support rod has a first end and a second end in the vertical direction, respectively. The first end is fixed to the base, and the height of the second end is higher than that of the crossbeam. The rod has a third end and a fourth end in the first direction, respectively. The third end and the second end are rotatably connected about a first axis. The transmission mechanism is disposed between the rod and the crossbeam. The upper end of the transmission mechanism is rotatably connected to the rod about a second axis, and the lower end is movable on the crossbeam. The support rod has a groove that presses down on the fourth end. The lower end of the transmission mechanism is movable in the groove. The distance between the fourth end and the second axis is greater than the distance between the first axis and the second axis. The direction of movement of the lower end of the transmission mechanism in the groove is parallel to the first direction.
[0010] In some embodiments, both the first limiting mechanism and the second limiting mechanism are provided in two sets. One end of the crossbeam along the first direction is provided with one first limiting mechanism and one second limiting mechanism, and the other end of the crossbeam along the first direction is provided with another first limiting mechanism and another second limiting mechanism. The end of the rod that is away from the second end is pressed down, and the first direction is perpendicular to the launch direction of the unmanned aerial vehicle.
[0011] In some embodiments, the transmission mechanism is provided with at least two pulleys at one end near the crossbeam, each pulley is distributed parallel to the crossbeam, the pulleys are fixedly connected to the transmission mechanism, and the pulleys are able to roll on the crossbeam.
[0012] In some embodiments, the first limiting element includes a limiting rod and a limiting gate. One end of the limiting rod is fixedly connected to the limiting gate, and the other end of the limiting rod is fixedly connected to the crossbeam. A sliding rod is fixedly connected to the base. The crossbeam can slide vertically on the sliding rod. The first elastic element is sleeved on the sliding rod. The bottom of the limiting gate abuts against the first elastic element. The limiting gate has the limiting hole. When the crossbeam moves downward, it can drive the limiting gate to move and squeeze the first elastic element, thereby causing the unmanned aerial vehicle to disengage from the limiting part.
[0013] In some embodiments, the second limiting element includes a positioning bracket and a connecting column. The positioning column is fixedly connected to the base, and the second elastic element is sleeved on the positioning column. The second elastic element abuts against the positioning bracket, and the positioning bracket can slide vertically on the positioning column. The connecting column is fixedly installed on the positioning bracket and is fixedly connected to the crossbeam.
[0014] In some embodiments, a guide frame is also provided on the rod body, one end of the guide frame is fixed on the crossbeam, and a guide groove is provided on the guide frame, allowing the rod body to move up and down in the guide groove.
[0015] This utility model also provides an unmanned aerial vehicle (UAV) launch simulation device, including two slide rails and a limiting device for an UAV launch simulation device as described in any of the above. The slide rails are fixed on the base, and the two ends of the UAV are slidably connected to the two slide rails respectively.
[0016] The present invention achieves the following technical advantages over the prior art:
[0017] This invention provides a limiting device and a launch simulation device. The device incorporates a first elastic element. Under the elastic force of this element, the limiting portion of the first limiting element restricts the movement of the unmanned aerial vehicle (UAV). When the first limiting element is subjected to force and pressed towards the base, the limiting portion of the first limiting element disengages from the UAV, releasing the UAV. Therefore, this device can lock the UAV using the elastic force of the first elastic element, and release the UAV by manually applying force to the first limiting element. It features a simple structure, requires minimal effort to operate, and ensures experimental safety. Attached Figure Description
[0018] 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.
[0019] Figure 1 This is a schematic diagram of the launch simulation device in one embodiment of the present invention;
[0020] Figure 2 This is a schematic diagram of the structure of an unmanned aerial vehicle in one embodiment of the present invention.
[0021] Wherein: 1-base; 2-crossbeam; 3-rod; 4-positioning seat; 5-positioning column; 6-positioning bracket; 7-limiting gate; 8-first elastic element; 9-sliding rod; 10-support rod; 11-pin; 12-transmission mechanism; 13-guide frame; 14-handle; 15-limiting rod; 16-second elastic element; 19-pulley; 20-slide groove; 21-connecting column; 22-limiting hole; 23-unmanned aerial vehicle. Detailed Implementation
[0022] 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.
[0023] 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.
[0024] Example 1
[0025] This utility model provides a limiting device for an unmanned aerial vehicle launch simulation device, such as... Figure 1-2As shown, the device includes a base 1 and at least one first limiting mechanism. Each first limiting mechanism includes a first limiting element and a first elastic element 8. One end of the first elastic element 8 abuts against the lower end of the first limiting element, and the other end abuts against the base 1. The first limiting element can reciprocate between a first position and a second position. The first limiting element has a limiting portion. Under the elastic force of the first elastic element 8, the first limiting element is in the first position, so that the limiting portion can restrict the movement of the unmanned aerial vehicle 23. When the first limiting element is subjected to force and moves towards the base 1, it can squeeze the first elastic element 8 and move to the second position. When the first limiting element is in the second position, the limiting portion can disengage from the unmanned aerial vehicle 23 to release the unmanned aerial vehicle 23. In this embodiment, by setting the first elastic element 8, under the elastic force of the first elastic element 8, the limiting portion of the first limiting element can restrict the movement of the unmanned aerial vehicle 23. When the first limiting element is subjected to force and squeezes the first elastic element 8 towards the base 1, the limiting portion of the first limiting element can disengage from the unmanned aerial vehicle 23 to release the unmanned aerial vehicle 23. Therefore, the device can lock the unmanned aerial vehicle 23 through the elastic force of the first elastic element 8, and release the unmanned aerial vehicle 23 by manually applying force to the first limiting element. It has a simple structure, requires little effort to operate, and ensures experimental safety. The first elastic element 8 can be a spring, but is not limited to this.
[0026] In some embodiments of this example, the limiting part is a limiting hole 22 provided on the first limiting element. When the first limiting element is in the first position, the limiting hole 22 can engage with the lower part of the limiting groove on the unmanned aerial vehicle (UAV) 23. When the first limiting element is in the second position, the limiting hole 22 separates from the limiting groove on the UAV 23, allowing the UAV 23 to move through along its launch direction. The moving direction of the first limiting element is perpendicular to the launch direction of the UAV 23. The limiting element can restrict the lower part of the limiting groove of the UAV 23 by the weight of the UAV 23 itself and the elastic force of the first elastic element 8, achieving stable engagement without the need for a complex locking device. At the same time, the UAV 23 can be released simply by driving the first limiting element to move in a direction perpendicular to the engagement, causing the limiting hole 22 to disengage from the lower part of the limiting groove. The action stroke is short and the response is fast. Moreover, during reset, the limiting hole can automatically fall back to the engagement position through the first elastic element 8, simplifying the operation procedure and making the device structure simple and easy to operate.
[0027] In some embodiments of this example, the limiting device further includes a crossbeam 2 and at least one second limiting mechanism. The second limiting mechanism includes a second limiting element and a second elastic element 16. Both the first and second limiting elements are fixedly connected to the crossbeam 2. The second limiting element is vertically movably connected to the base 1. One end of the second elastic element 16 abuts against the lower end of the second limiting element, and the other end abuts against the base 1. When the crossbeam 2 is subjected to force, it can move closer to the base 1 and drive the first limiting element to move closer to the base 1. The second limiting element and the first limiting element form a multi-point support structure, which can prevent the crossbeam 2 from tilting or swaying due to relying solely on the first limiting mechanism, ensuring that the movement direction of the crossbeam 2 always remains vertical, improving the limiting accuracy of the first limiting element. At the same time, the second limiting mechanism can further distribute the load of the crossbeam 2, reduce the bending deformation of the crossbeam 2, and extend the service life of the entire limiting device. The second elastic element 16 can be a spring, but is not limited to this.
[0028] In some embodiments of this example, the limiting device further includes a force-applying component, which includes a rod 3, a support rod 10, and a transmission mechanism 12. The two ends of the support rod 10 in the vertical direction are a first end and a second end, respectively. The first end is fixed on the base 1, and the height of the second end is higher than that of the crossbeam 2. The two ends of the rod 3 along the first direction are a third end and a fourth end, respectively. The third end and the second end are rotatably connected around the first axis. The transmission mechanism 12 is disposed between the rod 3 and the crossbeam 2. The upper end of the transmission mechanism 12 is rotatably connected to the rod 3 around the second axis, and the lower end can move on the crossbeam 2. A groove is provided on the support rod 10. When the fourth end is pressed down, the lower end of the transmission mechanism 12 can move in the groove. The distance between the fourth end and the second axis is greater than the distance between the first axis and the second axis. The movement direction of the lower end of the transmission mechanism 12 in the groove is parallel to the first direction. The handle 14 on the lower lever 3 transmits force to the crossbeam 2 via the transmission mechanism 12. The crossbeam 2 then applies the force to the first and second limiting mechanisms. Since the distance from the handle 14 to the second axis is greater than the distance between the first and second axes, i.e., through the lever principle, the operator can control the first and second limiting mechanisms with a smaller force, reducing the operator's labor intensity and improving work efficiency. The lever 3 and the support rod 10 can be rotatably connected via a pin 11, but are not limited to this.
[0029] In some embodiments of this example, two sets of the first limiting mechanism and the second limiting mechanism are provided. One end of the crossbeam 2 along the first direction is provided with a first limiting mechanism and a second limiting mechanism, and the other end of the crossbeam 2 along the first direction is provided with another first limiting mechanism and another second limiting mechanism. The end of the pressing rod 3 away from the second end is perpendicular to the launch direction of the unmanned aerial vehicle 23 in the first direction. Both the first and second limiting mechanisms are distributed along the first direction, allowing a single force application on the rod 3 to simultaneously release both first limiting mechanisms, thus releasing the unmanned aerial vehicle 23. Furthermore, the two first and two second limiting mechanisms are symmetrically arranged around the second axis, effectively forming four symmetrical force points on the crossbeam 2. External forces are evenly distributed to each limiting mechanism through the crossbeam 2, preventing any single limiting element from bearing excessive load and experiencing localized wear, deformation, or even breakage, thereby extending the device's service life. Simultaneously, the limiting elements provide uniform clamping or support to the unmanned aerial vehicle 23, preventing lateral displacement or tilting during the limiting state and ensuring it is stably positioned in the preset location before launch, laying the foundation for accurate subsequent launches and guaranteeing the accuracy of the launch position. The transmission mechanism 12 moves parallel to the crossbeam 2, making the force transmission path more balanced, further dispersing the forces on the crossbeam 2 and base 1, reducing localized stress concentration, and extending the overall service life of the device.
[0030] In some embodiments of this example, at least two pulleys 19 are provided at one end of the transmission mechanism 12 near the crossbeam 2. Each pulley 19 is distributed parallel to the first direction and is fixedly connected to the transmission mechanism 12. The pulleys 19 can roll on the crossbeam 2. The rolling of the pulleys on the crossbeam 2 makes the relative movement between the transmission mechanism 12 and the crossbeam 2 smoother and the force transmission more stable. This ensures that the first and second limiting mechanisms at both ends of the crossbeam 2 can rise and fall synchronously, avoiding limit deviation or release jamming of the unmanned aerial vehicle 23 due to unilateral action lag, and improving the response speed of the limiting device.
[0031] In some embodiments of this example, the first limiting element includes a limiting rod 15 and a limiting gate 7. One end of the limiting rod 15 is fixedly connected to the limiting gate 7, and the other end of the limiting rod 15 is fixedly connected to the crossbeam 2. A sliding rod 9 is fixedly connected to the base 1. The crossbeam 2 can slide vertically on the sliding rod 9. A first elastic element 8 is sleeved on the sliding rod 9. The bottom of the limiting gate 7 abuts against the first elastic element 8. The limiting gate 7 has a limiting hole 22. When the crossbeam 2 moves downward, it can drive the limiting gate 7 to move and squeeze the first elastic element 8, thereby causing the unmanned aerial vehicle 23 to disengage from the limiting part. The direction of movement of the limiting gate 7 is strictly limited to the direction perpendicular to the base 1 to ensure that the limiting hole 22 is always aligned with the limiting groove of the unmanned aerial vehicle 23, avoiding misalignment between the limiting hole and the limiting part due to lateral offset, thereby ensuring the accuracy of the launch. The sliding rod 9 guides the crossbeam 2 and the limiting gate 7, which can counteract the lateral force generated during operation, prevent the limiting gate 7 from tilting or jamming, and ensure the accuracy of operation.
[0032] In some embodiments of this example, the second limiting element includes a positioning bracket 6 and a connecting column 21. A positioning column 5 is fixedly connected to the base 1, and a second elastic element 16 is sleeved on the positioning column 5. The second elastic element 16 abuts against the positioning bracket 6, allowing the positioning bracket 6 to slide vertically on the positioning column 5. The connecting column 21 is fixedly mounted on the positioning bracket 6 and is fixedly connected to the crossbeam 2. The positioning column 5 is fixed to the base 1 via a positioning seat 4. The positioning column 5 ensures that the positioning bracket 6 slides vertically on the positioning column 5, thereby ensuring that the crossbeam 2 rises and falls smoothly in the vertical direction. This avoids misalignment between the limiting gate 7 and the unmanned aerial vehicle 23 due to the tilting of the crossbeam 2, ensuring the accuracy of the launch. At the same time, the elastic force of the second elastic element 16 can push the positioning bracket 6 upward, applying an upward preload to the crossbeam 2 through the connecting column 21. This, together with the first elastic element 8, ensures that the crossbeam 2 and the limiting hole 22 of the first limiting mechanism are tightly engaged with the limiting groove of the unmanned aerial vehicle 23, enhancing the stability of the limiting and preventing accidental disengagement due to external forces.
[0033] In some embodiments of this example, a guide frame 13 is also provided on the rod 3. One end of the guide frame 13 is fixed to the crossbeam 2, and a guide groove is provided on the guide frame 13, allowing the rod 3 to move up and down within the guide groove. The guide groove of the guide frame 13 and the rod 3 form a sliding fit, ensuring that the rod 3 can only move in a straight line along the guide groove in the up and down direction. This avoids the force transmission direction deviation caused by the swaying of the rod 3, reduces the risk of uneven force distribution at both ends of the crossbeam 2, and thus ensures the synchronous operation of the first and second limiting mechanisms.
[0034] Example 2
[0035] This embodiment provides an unmanned aerial vehicle (UAV) launch simulation device, including two slide rails and a limiting device for UAV launch simulation devices as described in Embodiment 1. The slide rails are fixed to a base 1, and the two ends of the UAV 23 are slidably connected to the two slide rails respectively. This embodiment uses a first elastic element 8. Under the elastic force of the first elastic element 8, the limiting portion of the first limiting element restricts the movement of the UAV 23. When the first limiting element is subjected to force and presses against the first elastic element 8 towards the base 1, the limiting portion of the first limiting element disengages from the UAV 23, releasing the UAV 23. Therefore, this device can lock the UAV 23 through the elastic force of the first elastic element 8, and release the UAV 23 by manually applying force to the first limiting element. It has a simple structure, requires little effort to operate, and ensures experimental safety. The first elastic element 8 can be a spring, but is not limited to this.
[0036] 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. A limiting device, characterized in that: It includes a base and at least one first limiting mechanism. Each first limiting mechanism includes a first limiting element and a first elastic element. One end of the first elastic element abuts against the lower end of the first limiting element, and the other end abuts against the base. The first limiting element is capable of reciprocating between a first position and a second position. The first limiting element has a limiting portion. Under the elastic force of the first elastic element, the first limiting element is in the first position so that the limiting portion can restrict the movement of the unmanned aerial vehicle. When the first limiting element is subjected to force and moves toward the base, it can compress the first elastic element and move to the second position. When the first limiting element is in the second position, the limiting part can disengage from the unmanned aerial vehicle to release the unmanned aerial vehicle.
2. The limiting device according to claim 1, characterized in that: The limiting part is a limiting hole provided on the first limiting element. When the first limiting element is in the first position, the limiting hole can be engaged with the lower part of the limiting groove on the unmanned aerial vehicle. When the first limiting element is in the second position, the limiting hole is separated from the limiting groove on the unmanned aerial vehicle and the unmanned aerial vehicle can move through it along its launch direction. The moving direction of the first limiting element is perpendicular to the launch direction of the unmanned aerial vehicle.
3. The limiting device according to claim 2, characterized in that: It also includes a crossbeam and at least one second limiting mechanism. The second limiting mechanism includes a second limiting element and a second elastic element. Both the first limiting element and the second limiting element are fixedly connected to the crossbeam. The second limiting element is vertically movably connected to the base. One end of the second elastic element abuts against the lower end of the second limiting element, and the other end abuts against the base. The crossbeam can move closer to the base under force and drive the first limiting element to move closer to the base.
4. The limiting device according to claim 3, characterized in that: It also includes a force-applying component, which comprises a rod, a support rod, and a transmission mechanism. The support rod has a first end and a second end in the vertical direction, respectively. The first end is fixed to the base, and the height of the second end is higher than that of the crossbeam. The rod has a third end and a fourth end in the first direction, respectively. The third end and the second end are rotatably connected around a first axis. The transmission mechanism is disposed between the rod and the crossbeam. The upper end of the transmission mechanism is rotatably connected to the rod around a second axis, and the lower end can move on the crossbeam. The support rod has a sliding groove that presses down on the fourth end. The lower end of the transmission mechanism can move in the sliding groove. The distance between the fourth end and the second axis is greater than the distance between the first axis and the second axis. The direction of movement of the lower end of the transmission mechanism in the sliding groove is parallel to the first direction.
5. The limiting device according to claim 4, characterized in that: Both the first limiting mechanism and the second limiting mechanism are provided in two sets. One end of the crossbeam along the first direction is provided with one first limiting mechanism and one second limiting mechanism, and the other end of the crossbeam along the first direction is provided with another first limiting mechanism and another second limiting mechanism. The rod is pressed down at the end away from the second end. The first direction is perpendicular to the launch direction of the unmanned aerial vehicle.
6. The limiting device according to claim 4, characterized in that: The transmission mechanism is provided with at least two pulleys at one end near the crossbeam. Each pulley is distributed parallel to the crossbeam, and the pulleys are fixedly connected to the transmission mechanism. The pulleys are able to roll on the crossbeam.
7. The limiting device according to claim 6, characterized in that: The first limiting element includes a limiting rod and a limiting gate. One end of the limiting rod is fixedly connected to the limiting gate, and the other end of the limiting rod is fixedly connected to the crossbeam. A sliding rod is fixedly connected to the base. The crossbeam can slide vertically on the sliding rod. The first elastic element is sleeved on the sliding rod. The bottom of the limiting gate abuts against the first elastic element. The limiting gate has the limiting hole. When the crossbeam moves downward, it can drive the limiting gate to move and squeeze the first elastic element, thereby causing the unmanned aerial vehicle to detach from the limiting part.
8. The limiting device according to claim 3, characterized in that: The second limiting element includes a positioning bracket and a connecting column. The positioning column is fixedly connected to the base, and the second elastic element is sleeved on the positioning column. The second elastic element abuts against the positioning bracket, and the positioning bracket can slide vertically on the positioning column. The connecting column is fixedly installed on the positioning bracket and is fixedly connected to the crossbeam.
9. The limiting device according to claim 7, characterized in that: The rod is also equipped with a guide frame, one end of which is fixed to the crossbeam. The guide frame has a guide groove, and the rod can move up and down in the guide groove.
10. A launch simulation device, characterized in that: It includes two slide rails and a limiting device as described in any one of claims 1-9, wherein the slide rails are fixed to the base, and the two ends of the unmanned aerial vehicle are respectively slidably connected to the two slide rails.