Low-altitude aircraft cabin stabilizing module
By designing the cabin stability module of the low-altitude aircraft, the automatic balance of the cabin center of gravity is achieved by using the lateral and longitudinal stabilization mechanisms and trimming components, the problem of existing low-altitude aircraft falling under the influence of external forces is solved, and the stability and practicality of the cabin is improved.
Patent Information
- Application Number
- CN202421837359.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-07-31
- Publication Date
- 2025-05-30
- Estimated Expiration
- 2034-07-31
AI Technical Summary
Existing low-altitude aircraft lack effective balance control devices, which leads to easy drops under the influence of external forces, and the installation of complex balance control devices has been abandoned due to their high price.
A low-altitude aircraft cabin stability module is designed, including two sets of transverse stabilization mechanisms and a set of longitudinal stabilization mechanisms, and the automatic trimming and stability of the cabin center of gravity is achieved through the trimming assembly.
Through the setting of the trimming components, effective trimming of the cabin center of gravity is achieved, maintaining the cabin stability is improved, and the practicality of the equipment is avoided.
Smart Images
Figure CN222921781U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of freight aircraft, in particular to a cabin stability module for a low-altitude aircraft. Background Technique
[0002] When an aircraft is flying, its fuselage, wings or propellers will change their flight states, such as tilting, due to external forces. In order to adjust its flight state, a balance adjustment system in the fuselage is often used. For large aircraft, such as helicopters, relatively complex adjustment control systems are adopted, and the central control system is used for automatic adjustment. The structures of such control systems are relatively complex and are not suitable for small low-altitude unmanned aircraft.
[0003] At present, general low-altitude aircraft are manufactured with relatively simple mechanical structures. For example, they directly drive the propeller to rotate through a motor to make it climb, and do not consider the falling phenomenon caused by external forces during their flight. Therefore, few current unmanned aircraft are equipped with relevant balance control devices. And the use of balance control devices with relatively complex structures will be abandoned due to high prices and other reasons. Content of the Utility Model
[0004] The purpose of the utility model is to provide a cabin stability module for a low-altitude aircraft to solve the problems raised in the above background technique.
[0005] To achieve the above purpose, the utility model provides the following technical solution:
[0006] A cabin stability module for a low-altitude aircraft includes two groups of horizontally stable mechanisms arranged in parallel and a longitudinal stable mechanism connected between the two groups of horizontally stable mechanisms. The longitudinal stable mechanism is perpendicular to the two groups of horizontally stable mechanisms. The longitudinal stable mechanism includes a group of fixed rods, both ends of the fixed rods are fixedly connected with first mounting brackets, both ends of the first mounting brackets are fixedly connected with second mounting brackets, and a group of fixed rods are also fixedly connected between the second mounting brackets. A trimming block is slidably connected to the fixed rods, and a trimming assembly for adjusting the position of the trimming block is connected to the trimming block.
[0007] As a further scheme of the utility model: The trimming assembly includes a first fixed bracket fixedly connected to the first mounting bracket and the second mounting bracket. A magnet rod is fixedly connected between the first fixed brackets. A copper tube is slidably connected to the magnet rod, and push plates are fixedly connected to both ends of the copper tube.
[0008] As a further solution of the utility model: A fixed cylinder is fixedly connected to the first fixing frame. A fixed block is fixedly connected inside the fixed cylinder. A telescopic rod is slidably connected inside the fixed block. One end of the telescopic rod passes through the fixed cylinder and is fixedly connected to the first fixing frame with a contact head. The contact head cooperates with the push plate. A stop block fixedly connected to the telescopic rod is arranged between the first fixing frame and the fixed block. A spring sleeved on the telescopic rod is arranged between the stop block and the fixed block.
[0009] As a further solution of the utility model: The other end of the telescopic rod passes through the fixed block and is fixedly connected to an installation seat. A reflector is fixedly connected to the installation seat. A laser rangefinder is fixedly connected to the bottom of the fixed cylinder. The laser rangefinder cooperates with the reflector.
[0010] As a further solution of the utility model: A second fixing frame is fixedly connected to the first mounting frame and the second mounting frame. A hydraulic cylinder is fixedly connected to the second fixing frame. A hydraulic block is slidably connected inside the hydraulic cylinder. A driving rod is fixedly connected between the hydraulic blocks. A connecting frame is fixedly connected to the driving rod. The connecting frame is fixedly connected to the trimming block.
[0011] As a further solution of the utility model: One end of a hydraulic oil pipe is connected to the hydraulic cylinder, and the other end of the hydraulic oil pipe is connected to a hydraulic pump.
[0012] Compared with the prior art, the beneficial effects of the utility model are as follows: Through the setting of the trimming component, the utility model pushes the trimming block to the other side, so as to push the trimming block to the side with lighter mass, thereby trimming the weight on the side with lighter weight of the cabin body, keeping the center of gravity of the cabin body at the center of the cabin body, and then keeping the cabin body stable. And the utility model also automatically trims and stabilizes the cabin body in multiple directions through the mutual cooperation of the lateral stabilizing mechanism and the longitudinal stabilizing mechanism, improving the practicability of the equipment. Description of the Drawings
[0013] Figure 1 It is a schematic structural diagram of a cabin body stabilizing module of a low-altitude aircraft in the utility model.
[0014] Figure 2 It is a schematic structural diagram of a lateral stabilizing mechanism in a cabin body stabilizing module of a low-altitude aircraft in the utility model.
[0015] Figure 3 It is a schematic structural diagram of a longitudinal stabilizing mechanism in a cabin body stabilizing module of a low-altitude aircraft in the utility model.
[0016] In the figure: 1 - fixed rod, 2 - first mounting bracket, 3 - trimming block, 4 - first fixing bracket, 5 - fixed cylinder, 6 - fixing block, 7 - telescopic rod, 8 - stop block, 9 - spring, 10 - contact, 11 - magnet rod, 12 - copper tube, 13 - push plate, 14 - mounting seat, 15 - reflector, 16 - laser rangefinder, 17 - second fixing bracket, 18 - hydraulic cylinder, 19 - hydraulic block, 20 - drive rod, 21 - connecting bracket, 22 - hydraulic pump, 23 - hydraulic oil pipe, 24 - second mounting bracket. Specific implementation mode
[0017] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.
[0018] Refer to Figures 1 to 3 , in the embodiment of the present invention, a low-altitude aircraft cabin stability module includes two groups of horizontally arranged horizontal stability mechanisms and a group of vertical stability mechanisms connected between the two groups of horizontal stability mechanisms. The vertical stability mechanism is perpendicular to the two groups of horizontal stability mechanisms. The vertical stability mechanism includes a group of fixed rods 1. Both ends of the fixed rod 1 are fixedly connected with a first mounting bracket 2. Both ends of the first mounting bracket 2 are fixedly connected with a second mounting bracket 24. A group of fixed rods 1 are also fixedly connected between the second mounting brackets 24. A trimming block 3 is slidably connected to the fixed rod 1. A trimming assembly for adjusting the position of the trimming block 3 is connected to the trimming block 3. When the cabin tilts, the trimming block 3 will move towards the heavier side under the action of gravity. And in this present invention, through the setting of the trimming assembly, the trimming block 3 is pushed to the other side, so as to push the trimming block 3 towards the lighter side in terms of mass, thereby trimming the weight on the lighter side of the cabin, keeping the center of gravity of the cabin at the center of the cabin, and further keeping the cabin stable.
[0019] In a case of this embodiment, please refer to Figures 1 to 3, the trimming component includes a first fixing frame 4 fixedly connected to the first mounting frame 2 and the second mounting frame 24. A magnet rod 11 is fixedly connected between the first fixing frames 4. A copper tube 12 is slidably connected to the magnet rod 11. Push plates 13 are fixedly connected to both ends of the copper tube 12. A fixing cylinder 5 is fixedly connected to the first fixing frame 4. A fixing block 6 is fixedly connected inside the fixing cylinder 5. A telescopic rod 7 is slidably connected inside the fixing block 6. One end of the telescopic rod 7 passes through the fixing cylinder 5 and is fixedly connected to the first fixing frame 4 with a contact 10. The contact 10 cooperates with the push plate 13. A stop block 8 fixedly connected to the telescopic rod 7 is arranged between the first fixing frame 4 and the fixing block 6. A spring 9 sleeved on the telescopic rod 7 is arranged between the stop block 8 and the fixing block 6. The other end of the telescopic rod 7 passes through the fixing block 6 and is fixedly connected to a mounting seat. A reflector 15 is fixedly connected to the mounting seat 14. A laser rangefinder 16 is fixedly connected to the bottom of the fixing cylinder 5. The laser rangefinder 16 cooperates with the reflector 15. A second fixing frame 17 is fixedly connected to the first mounting frame 2 and the second mounting frame 24. A hydraulic cylinder 18 is fixedly connected to the second fixing frame 17. A hydraulic block 19 is slidably connected inside the hydraulic cylinder 18. A driving rod 20 is fixedly connected between the hydraulic blocks 19. A connecting frame 21 is fixedly connected to the driving rod 20. The connecting frame 21 is fixedly connected to the trimming block 3. One end of a hydraulic oil pipe 23 is connected to the hydraulic cylinder 18, and the other end of the hydraulic oil pipe 23 is connected to a hydraulic pump 22. When the cabin tilts, the copper tube 12 slides towards the heavier side under the action of gravity. At this time, the copper tube 12 slides on the magnet rod 11. At this time, a magnetic field is generated during the sliding process of the copper tube 12. At this time, according to Lenz's law, the copper tube 12 will be subjected to the resistance generated by the magnetic field, thereby realizing the slow sliding of the copper tube 12. The copper tube 12 drives the push plate 13 to push the contact 10. The contact 10 drives the telescopic rod 7 to contract into the fixing cylinder 5. The fixing rod 1 compresses the spring 9 through the stop block 8. At the same time, the telescopic rod 7 drives the reflector 15 to move through the mounting seat 14. At this time, the mutual distance between the reflector 15 and the laser rangefinder 16 changes. At this time, the laser rangefinder 16 controls the hydraulic pump 22 to inject hydraulic oil into the hydraulic cylinder 18 on the side where the distance between the reflector 15 and the laser rangefinder 16 decreases. At this time, the hydraulic block 19 drives the driving rod 20 to extend under the push of the hydraulic oil. The driving rod 20 drives the trimming block 3 to move through the connecting frame 21, thereby realizing the automatic trimming of the cabin.
[0020] The foregoing has shown and described the basic principles, main features and advantages of the present utility model. For those skilled in the art, it is obvious that the present utility model is not limited to the details of the above-mentioned exemplary embodiments, and without departing from the spirit or basic features of the present utility model, the present utility model can be implemented in other specific forms. Therefore, from any point of view, the embodiments should be regarded as exemplary and non-restrictive. The scope of the present utility model is defined by the appended claims rather than the above description. Therefore, it is intended to embrace all changes that fall within the meaning and scope of the equivalent elements of the claims in the present utility model. Any reference signs in the claims should not be construed as limiting the claims involved.
[0021] The foregoing is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present utility model shall be included in the protection scope of the present utility model.
Claims
1. A low-altitude aircraft cabin stabilization module, characterized in that: It includes two groups of parallelly arranged lateral stabilization mechanisms and a group of longitudinal stabilization mechanisms connected between the two groups of lateral stabilization mechanisms, the longitudinal stabilization mechanism and the two groups of lateral stabilization mechanisms are perpendicular to each other, the longitudinal stabilization mechanism includes a group of fixing rods, both ends of the fixing rods are fixedly connected to the first mounting frames, both ends of the first mounting frames are fixedly connected to the second mounting frames, and a group of fixing rods is also fixedly connected between the second mounting frames, the fixing rods are slidably connected to balancing blocks, and the balancing blocks are connected to balancing components for adjusting the position of the balancing blocks.
2. A low-altitude aircraft cabin stabilization module according to claim 1, characterized in that: The balancing assembly comprises a first fixing frame fixedly connected to the first mounting frame and the second mounting frame, a magnet rod is fixedly connected between the first fixing frames, a copper tube is slidably connected to the magnet rod, and push plates are fixedly connected to both ends of the copper tube.
3. A low-altitude aircraft cabin stabilization module according to claim 2, characterized in that: A fixing cylinder is fixedly connected to the first fixing frame, a fixing block is fixedly connected inside the fixing cylinder, a telescopic rod is slidably connected inside the fixing block, one end of the telescopic rod passes through the fixing cylinder and is fixedly connected to the first fixing frame with a contact, the contact and the push plate cooperate with each other, a stopper fixedly connected to the telescopic rod is arranged between the first fixing frame and the fixing block, and a spring sleeved on the telescopic rod is arranged between the stopper and the fixing block.
4. A low-altitude aircraft cabin stabilization module according to claim 3, characterized in that: The other end of the telescopic rod passes through the fixing block and is fixedly connected with a swivel seat, the mounting seat is fixedly connected with a reflector, the bottom of the fixing cylinder is fixedly connected with a laser rangefinder, and the laser rangefinder and the reflector cooperate with each other.
5. A low-altitude aircraft cabin stabilization module according to claim 2, characterized in that: The first mounting frame and the second mounting frame are fixedly connected with a second fixing frame, the second fixing frame is fixedly connected with a hydraulic cylinder, a hydraulic block is slidably connected in the hydraulic cylinder, a driving rod is fixedly connected between the hydraulic blocks, a connecting frame is fixedly connected to the driving rod, and the connecting frame is fixedly connected to the balancing block.
6. A low-altitude aircraft cabin stabilization module according to claim 5, characterized in that: The hydraulic cylinder is connected to one end of a hydraulic oil pipe, and the other end of the hydraulic oil pipe is connected to a hydraulic pump.