Aviation double-margin electric mechanism

Abstract

The utility model relates to the technical field of electric mechanisms, and discloses an aviation double-margin electric mechanism which comprises a supporting frame, the inner wall of the top end of the supporting frame is connected with an electric mechanism in a sliding mode, the bottom end of the electric mechanism is fixedly connected with a limiting disc, and a containing hole is formed in the supporting frame. A limiting assembly is fixedly connected to the middle of the bottom end of the interior of the containing hole, four limiting blocks are fixedly connected to the bottom end of the interior of the containing hole, fixing rods are fixedly connected to the interiors of the limiting blocks, the fixing rods are sleeved with strong springs, and moving blocks are slidably connected to the interiors of the limiting blocks; and the interior of one side of the moving block is rotationally connected with a connecting rod. According to the utility model, through the resilience force of the strong spring and the damper, the force borne by the electric mechanism can be uniformly absorbed, the damage of parts caused by the vibration of the electric mechanism is avoided, and the overall reliability is further improved.

Description

Technical Field

[0001] The utility model relates to the technical field of electric mechanisms, in particular to an aviation double-redundancy electric mechanism. Background Art

[0002] Aviation refers to the activities of air navigation through aircraft, including civil aviation and military aviation. With the advancement of science and technology, aviation technology continues to develop, and the performance requirements for aircraft are also increasing. In modern aircraft, double-redundancy electric mechanisms are widely used due to their high reliability and high adaptability. They can work in two different modes, namely double-redundancy mode and single-redundancy mode. This versatility enables the aircraft to maintain efficient control performance under different flight conditions.

[0003] In the prior art, some aircraft will suffer from different degrees of vibration and impact at different flight stages. These external factors will generate additional vibration loads on the electric mechanism, and the motor mechanism will be damaged due to components caused by vibration and impact, thereby reducing the reliability of the system. Therefore, in view of the above shortcomings, an aviation dual-redundancy electric mechanism is proposed. Utility Model Content

[0004] The purpose of the utility model is to solve the shortcomings existing in the prior art and to propose an aviation dual-redundancy electric mechanism, aiming to improve the problem in the prior art that motor mechanism components may be damaged due to vibration and impact.

[0005] To achieve the above-mentioned objectives, the utility model provides the following technical solutions: an aviation dual-redundancy electric mechanism, comprising a support frame, an electric mechanism is slidably connected to the inner wall of the top end of the support frame, the bottom end of the electric mechanism is fixedly connected to a limiting plate, a receiving hole is provided inside the support frame, a limiting component is fixedly connected to the middle of the inner bottom end of the receiving hole, four limit blocks are fixedly connected to the inner bottom end of the receiving hole, a fixed rod is fixedly connected to the inside of the limit block, a strong spring is sleeved on the outside of the fixed rod, a moving block is slidably connected to the inside of the limit block, a connecting rod is rotatably connected to one side of the moving block, an expansion block is rotatably connected to the adjacent side of every two connecting rods, and a long hole is provided on the top of the limit block.

[0006] Furthermore, a support plate is fixedly connected to the rear end of the support frame, a ventilation hole is opened on the front side of the support plate, a water tank is fixedly connected to the bottom end of the support plate, a water pump is fixedly connected to the right end of the support plate, a circulation pipe is fixedly connected to the top end of the water pump, a circulation pipe is fixedly connected to the left end of the circulation pipe, two fans are fixedly connected to the inside of the support plate, and two filter plates are fixedly connected to the right end of the support plate.

[0007] Furthermore, the limiting assembly comprises a receiving block, the bottom end of the receiving block is fixedly connected to the inner bottom end of the receiving hole, and a damper is fixedly connected to the interior of the receiving block.

[0008] Furthermore, the outer portion of the limiting plate is slidably connected to the inner portion of the accommodating hole, and the top end of the expansion block is fixedly connected to the bottom end of the limiting plate.

[0009] Furthermore, the outer portion of the moving block is slidably connected to the inner portion of the long hole, and the inner portion of the moving block is slidably connected to the outer portion of the fixing rod.

[0010] Furthermore, one end of the strong spring is fixedly connected to one side of the interior of the limiting block, and the other end of the strong spring is fixedly connected to one side of the moving block.

[0011] Furthermore, the bottom end of the damper is fixedly connected to the middle of the inner bottom end of the accommodating hole, and the top end of the damper is fixedly connected to the bottom end of the limiting plate.

[0012] Furthermore, the outside of the circulation pipe is fixedly connected to the inside of the support plate, and the bottom end of the circulation pipe is fixedly connected to the left end of the support plate.

[0013] The utility model has the following beneficial effects:

[0014] 1. In the present invention, the force applied to the electric mechanism can be uniformly absorbed by the rebound force of the strong spring and the damper, thereby avoiding damage to components caused by vibration of the electric mechanism and improving the overall reliability.

[0015] 2. In the utility model, by starting the fan, the cold air around the circulation pipe is dispersed through the ventilation holes to achieve heat dissipation of the electric mechanism. Through effective heat dissipation, the performance stability of the electric mechanism under various flight conditions can be maintained, thereby improving the reliability of the system. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 A three-dimensional diagram of an aviation double-redundancy electric mechanism proposed by the utility model;

[0017] Figure 2 This is a schematic diagram of the filter plate structure of an aviation dual-redundancy electric mechanism proposed by the utility model;

[0018] Figure 3 This is a schematic diagram of the support frame structure of an aviation dual-redundancy electric mechanism proposed by the utility model;

[0019] Figure 4 This is a schematic diagram of the expansion block structure of an aviation dual-redundancy electric mechanism proposed by the utility model;

[0020] Figure 5 The utility model is a schematic diagram of a support plate structure of an aviation dual-redundancy electric mechanism.

[0021] Legend:

[0022] 1. Support frame; 2. Electric mechanism; 3. Limit plate; 4. Accommodating block; 5. Damper; 6. Limit block; 7. Fixed rod; 8. Strong spring; 9. Moving block; 10. Connecting rod; 11. Expansion block; 12. Long hole; 13. Accommodating hole; 14. Support plate; 15. Ventilation hole; 16. Water tank; 17. Water pump; 18. Circulation pipe; 19. Circuit pipe; 20. Fan; 21. Filter plate. DETAILED DESCRIPTION

[0023] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0024] Reference Figure 1 , Figure 3 and Figure 4, an embodiment of the utility model is provided: an aviation double-margin electric mechanism, comprising a support frame 1, an electric mechanism 2 is slidably connected to the inner wall of the top end of the support frame 1, allowing the electric mechanism 2 to slide up and down inside the support frame 1, and the bottom end of the electric mechanism 2 is fixedly connected to a limiting plate 3 for limiting the moving range of the electric mechanism 2 in the support frame 1 to prevent it from falling off, and a receiving hole 13 is opened inside the support frame 1 to provide additional receiving space, and a limiting component is fixedly connected to the middle of the inner bottom end of the receiving hole 13, and the limiting component includes a receiving block 4, and the bottom end of the receiving block 4 is fixedly connected to the inner bottom end of the receiving hole 13, and the inside of the receiving block 4 is fixedly connected to a damper 5. The function of the damper 5 is to reduce the vibration and impact of the electric mechanism 2, and to provide a limiting function to prevent shaking, and the top end of the damper 5 is fixedly connected to the bottom end of the limiting plate 3, and the bottom end of the damper 5 is fixedly connected to the middle of the inner bottom end of the receiving hole 13, and the inner bottom end of the receiving hole 13 is fixedly connected to four limiting Block 6 not only provides support for subsequent limiting, but also provides support for subsequent components. The interior of the limiting block 6 is fixedly connected to a fixed rod 7 for providing additional support. The exterior of the fixed rod 7 is sleeved with a strong spring 8 for providing spring force and rebound force. The interior of the limiting block 6 is slidably connected to a moving block 9 for force transmission. One end of the strong spring 8 is fixedly connected to one side of the interior of the limiting block 6, and the other end of the strong spring 8 is fixedly connected to one side of the moving block 9. The interior of the moving block 9 is slidably connected to the outside of the fixed rod 7. One side of the moving block 9 is internally rotatably connected to a connecting rod 10 for force transmission. The adjacent sides of the two connecting rods 10 are externally rotatably connected to an expansion block 11 to provide additional space. The top of the expansion block 11 is fixedly connected to the bottom end of the limiting disk 3. A long hole 12 is provided at the top of the limiting block 6. The exterior of the moving block 9 is slidably connected to the interior of the long hole 12. This design is used to provide movement space for the moving block 9, and the exterior of the limiting disk 3 is slidably connected to the interior of the accommodating hole 13.

[0025] Reference Figure 1 , Figure 2 and Figure 5, the rear end of the support frame 1 is fixedly connected with a support plate 14 to provide additional support, and a ventilation hole 15 is opened on the front side of the support plate 14 to promote air circulation. The bottom end of the support plate 14 is fixedly connected with a water tank 16 for storing cooling liquid. The right end of the support plate 14 is fixedly connected with a water pump 17. The function of the water pump 17 is to drive the cooling liquid. The top of the water pump 17 is fixedly connected with a circulation pipe 18. This design is to transport the coolant into the interior of the circulation pipe 18. The left end of the circulation pipe 18 is fixedly connected with a patrol pipe 19. The patrol pipe 19 is a pipe for the coolant after circulation to the water tank 16. The outside of the circulation pipe 18 is fixedly connected to the inside of the support plate 14, and the bottom end of the patrol pipe 19 is fixedly connected to the left end of the support plate 14. Two fans 20 are fixedly connected to the inside of the support plate 14 to accelerate air flow and improve heat dissipation efficiency. Two filter plates 21 are fixedly connected to the right end of the support plate 14 to prevent dust and impurities from contacting the fan 20, so as to ensure the cleanliness and efficient operation of the cooling system.

[0026] Working principle: first, when the whole is shaking, this will make the electric mechanism 2 slide, and then the shaking of the electric mechanism 2 will drive the limit plate 3 to slide in the accommodating hole 13, and then the sliding of the limit plate 3 will drive the expansion block 11 to move downward, and then the movement of the expansion block 11 will drive the connecting rod 10 to move, and then the movement of the connecting rod 10 will drive the moving block 9 to slide inside the long hole 12, and the moving block 9 will also slide outside the fixed rod 7, and then the strong spring 8 will be squeezed, and then the strong spring 8 will generate a rebound force under the squeezing, which provides the first layer of shock absorption when the electric mechanism 2 slides. The damper 5 is driven to move, which is the secondary shock absorption provided to the limit plate 3. This design is to disperse the force received to the strong spring 8 and the damper 5 respectively, so as to realize uniform absorption of the force. Then, when the electric mechanism 2 is working, heat is generated. At this time, the fan 20 is started. Under the instigation of the fan 20, the cold air around the circulation pipe 18 is blown from the ventilation hole 15 to the direction of the electric mechanism 2. Then, in the circulation pipe 18, the water pump 17 draws the coolant inside the water tank 16 into the circulation pipe 18, and then returns to the inside of the water pump 17 from the circulation pipe 18 through the patrol pipe 19. This can not only provide a good heat dissipation effect, but also realize the water circulation of the coolant, thereby reducing the economic cost.

[0027] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. An aviation dual-redundancy electric mechanism, comprising a support frame (1), characterized in that: The inner wall at the top of the support frame (1) is slidably connected to an electric mechanism (2), the bottom end of the electric mechanism (2) is fixedly connected to a limiting plate (3), a receiving hole (13) is provided inside the support frame (1), a limiting assembly is fixedly connected to the middle of the bottom end of the receiving hole (13), four limiting blocks (6) are fixedly connected to the bottom end of the receiving hole (13), a fixed rod (7) is fixedly connected to the inside of the limiting block (6), a strong spring (8) is sleeved on the outside of the fixed rod (7), a moving block (9) is slidably connected to the inside of the limiting block (6), a connecting rod (10) is rotatably connected to one side of the moving block (9), an expansion block (11) is rotatably connected to the adjacent sides of the two connecting rods (10), and a long hole (12) is provided on the top of the limiting block (6).

2. The aviation dual-redundancy electric mechanism according to claim 1, characterized in that: The rear end of the support frame (1) is fixedly connected to a support plate (14), a ventilation hole (15) is provided on the front side of the support plate (14), a water tank (16) is fixedly connected to the bottom end of the support plate (14), a water pump (17) is fixedly connected to the right end of the support plate (14), a circulation pipe (18) is fixedly connected to the top end of the water pump (17), a circulation pipe (19) is fixedly connected to the left end of the circulation pipe (18), two fans (20) are fixedly connected to the inside of the support plate (14), and two filter plates (21) are fixedly connected to the right end of the support plate (14).

3. The aviation dual-redundancy electric mechanism according to claim 1, characterized in that: The limiting assembly comprises a receiving block (4), the bottom end of the receiving block (4) being fixedly connected to the inner bottom end of the receiving hole (13), and a damper (5) being fixedly connected to the interior of the receiving block (4).

4. The aviation dual-redundancy electric mechanism according to claim 1, characterized in that: The outside of the limiting plate (3) is slidably connected to the inside of the accommodating hole (13), and the top end of the expansion block (11) is fixedly connected to the bottom end of the limiting plate (3).

5. The aviation dual-redundancy electric mechanism according to claim 1, characterized in that: The outside of the moving block (9) is slidably connected to the inside of the long hole (12), and the inside of the moving block (9) is slidably connected to the outside of the fixing rod (7).

6. The aviation dual-redundancy electric mechanism according to claim 1, characterized in that: One end of the strong spring (8) is fixedly connected to one side of the interior of the limit block (6), and the other end of the strong spring (8) is fixedly connected to one side of the moving block (9).

7. The aviation dual-redundancy electric mechanism according to claim 3, characterized in that: The bottom end of the damper (5) is fixedly connected to the middle of the inner bottom end of the accommodating hole (13), and the top end of the damper (5) is fixedly connected to the bottom end of the limiting plate (3).

8. The aviation dual-redundancy electric mechanism according to claim 2, characterized in that: The outside of the circulation pipe (18) is fixedly connected to the inside of the support plate (14), and the bottom end of the circulation pipe (19) is fixedly connected to the left end of the support plate (14).

Images