Case for airborne electronic equipment

Abstract

The utility model discloses a case for airborne electronic equipment, and relates to the technical field of airborne electronic equipment. The box comprises a box body, an inner container and a small circulating pump, cover plates are installed at the upper end, the front side and the rear side of the box body through fixing bolts, the inner container for containing electronic equipment is arranged in the box body, and sliding blocks matched with sliding rails on the two sides in the box body are fixedly installed on the two sides of the inner container. According to the utility model, the dual structures of the box body and the inner container play a role in buffering and protecting the electronic equipment arranged in the inner container, and when an airplane takes off or falls to the ground and vibrates, the impact force in the vertical direction is buffered and protected through the damping rod, the reset spring and the second damping grease layer; impact force in the horizontal direction is protected through the first damping grease layer and the polyurethane buffer strips, and due to the fact that the buffer structures of the device are all arranged in the box body, the space of an airplane body is not occupied.

Description

Technical Field

[0001] The utility model belongs to the field of airborne electronic equipment, and in particular relates to a chassis for airborne electronic equipment. Background Art

[0002] Airborne electronic equipment is an important part of an aircraft. During use, it will be subject to vibration and impact from factors such as the aircraft engine itself, external airflow, takeoff and landing, etc. If its own anti-seismic ability is poor, it is easy to malfunction during use due to the above vibration and impact, thus affecting the performance of the aircraft.

[0003] At present, the vibration reduction method for airborne electronic equipment generally adopts whole-machine vibration reduction. A shock-absorbing device is installed between the bottom of the box and the aircraft mounting plate, and the mounting plate is then connected to the aircraft body. In order to prevent collisions between airborne electronic equipment, the installation distance between devices needs to be increased. The shock-absorbing device of this method needs to support the entire weight of the airborne electronic equipment. There are shortcomings such as large size of the shock-absorbing device and large equipment installation space. In view of this, the present utility model is specially proposed. Utility Model Content

[0004] The technical problem to be solved by the utility model is to overcome the deficiencies of the prior art and provide a chassis for airborne electronic equipment.

[0005] In order to solve the above technical problems, the basic concept of the technical solution adopted by the utility model is:

[0006] A chassis for airborne electronic equipment comprises a box body, an inner tank and a small circulation pump, wherein the upper end and the front and rear sides of the box body are both provided with a cover plate through fixing bolts, the inner tank for placing the electronic equipment is provided inside the box body, and both sides of the inner tank are fixedly provided with sliders adapted to the slide rails on both sides of the box body;

[0007] The four corners of the inner liner are provided with cavities for installing small damping rods, the telescopic end of each small damping rod passes through the lower end of the inner liner and is fixed to the T-shaped block at the bottom end of the box body, and the telescopic end of each small damping rod is sleeved with a return spring on the outside, and the two ends of the return spring are in contact between the T-shaped block and the inner liner;

[0008] An inner protective cover is fixedly installed on the upper end of the inner tank by screws, a functional area for installing a small circulation pump is separated inside the inner tank by a partition, a buffer seat is fixed at the bottom of the inner tank, and strip grooves for plugging in special-shaped plates are evenly spaced at the upper end of the buffer seat, and the number of the strip grooves is consistent with the number of protruding ends at the bottom of the special-shaped plate, a first damping grease layer is coated between the strip grooves and the protruding ends of the special-shaped plate, the special-shaped plate is fixedly installed on the lower end of the carrier plate, the upper end of the carrier plate is fixed to the electronic equipment by screws, and a cooling cover is attached to the outside of the electronic equipment.

[0009] Optionally, sealing rings are fixed to the inner walls of the three cover plates, an anti-disassembly cap is fixed to the end of each fixing bolt, and an anti-slip gasket is sleeved on the lower end of the end of each fixing bolt.

[0010] Optionally, the bottom of the inner tank is rectangular and fixed with four plug rods, each of which passes through the inside of a cylindrical sleeve connected to the bottom end of the shell, and a second damping grease layer is coated between the inner wall of the cylindrical sleeve and the outer wall of the plug rod.

[0011] Optionally, a plurality of groups of guide rods are symmetrically fixed to the lower end of the loading plate, and each group of guide rods is symmetrically arranged with respect to the central axis of the special-shaped plate, the number of guide rods in each group is two, and the lower ends of the guide rods pass through guide grooves opened at the upper end of the connecting buffer seat.

[0012] Optionally, the data wire of the electronic device can pass through the inner shell and the box body through a first reserved hole and a second reserved hole, the first reserved hole is opened at the front end of the inner shell, and a wire harness is fixedly installed at the front end of the inner shell by screws, and the front end surface of the wire harness is provided with C-shaped grooves for inserting the data wires at equal intervals, the second reserved hole is opened at the side end of the box body, and a cross-hole membrane for fixing the data wires is provided inside the second reserved hole.

[0013] Optionally, a groove for installing a polyurethane buffer strip is formed on the side wall of the loading plate.

[0014] Optionally, three heat-conducting plates for fitting the surface of the electronic equipment are fixedly mounted on the inner wall of the cooling hood, and a cooling cavity for the coolant to enter is opened inside the wall of the cooling hood. The upper end of the cooling cavity passes through the partition through a delivery pipe and is connected to the delivery end of a small circulating pump. The negative pressure end of the small circulating pump passes through a pipeline to the interior of the coolant tank, and one side of the coolant tank passes through the partition through a circulation pipe and is connected to the lower end of the cooling cavity. The small circulating pump and the coolant tank are both fixedly mounted inside the inner tank through a box body.

[0015] After adopting the above technical solution, the utility model has the following beneficial effects compared with the prior art. Of course, any product implementing the utility model does not necessarily need to achieve all the advantages described below at the same time:

[0016] The utility model plays a role of buffering and protecting the electronic equipment installed in the inner tank through the dual structure of the box body and the inner tank. When the aircraft takes off or lands and generates vibration, the impact force in the vertical direction will be buffered and protected by the damping rod, the return spring and the second damping fat layer, and the impact force in the horizontal direction will be protected by the first damping fat layer and the polyurethane buffer strip. In addition, since the buffer structure of the device is arranged inside the box body, it will not occupy the space of the aircraft body. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The drawings described below are only some embodiments. For those skilled in the art, other drawings can be obtained based on these drawings without creative work.

[0018] In the figure:

[0019] Figure 1 This is a schematic diagram of the main cross-sectional structure of the utility model;

[0020] Figure 2 This is a structural diagram of the combined parts of the inner tank, cooling cover and small circulation pump in the utility model;

[0021] Figure 3 It is a structural diagram of the combined parts of the cooling cover and the heat conducting plate in the utility model;

[0022] Figure 4 It is a structural diagram of the combined parts of the buffer seat, the guide groove and the strip groove in the utility model;

[0023] Figure 5 This is a structural diagram of the combined parts of the loading plate and the special-shaped plate in the utility model;

[0024] Figure 6 for Figure 1 Schematic diagram of the structure of the A part;

[0025] Figure 7 for Figure 1 Schematic diagram of the structure of the B part;

[0026] Figure 8 for Figure 1 Schematic diagram of the structure of the C part;

[0027] Fig. 9 for Figure 2 Schematic diagram of the D part structure.

[0028] In the accompanying drawings, the components represented by the reference numerals are listed as follows:

[0029] 1. Box body; 2. Fixing bolt; 3. Cover plate; 4. Inner tank; 5. Slide rail; 6. Slider; 7. Small damping rod; 8. T-block; 9. Reset spring; 10. Inner protective cover; 11. Small circulation pump; 12. Buffer seat; 13. Special-shaped plate; 14. Strip groove; 15. First damping grease layer; 16. Carrier plate; 17. Cooling cover; 18. Sealing ring; 19. Anti-skid washer; 20. Plug-in rod; 21. Cylindrical sleeve; 22. Second damping grease layer; 23. Guide rod; 24. Guide groove; 25. First reserved hole; 26. Second reserved hole; 27. Beam line; 28. Cross-hole membrane; 29. ​​Polyurethane buffer strip; 30. Heat conduction plate; 31. Cooling cavity; 32. Delivery pipe; 33. Circulation pipe; 34. Coolant tank; 35. Box body. DETAILED DESCRIPTION

[0030] The utility model is now described in further detail with reference to the accompanying drawings.

[0031] See also Figures 1 to 9 The utility model provides a technical solution: a chassis for airborne electronic equipment, comprising a box body 1, an inner tank 4 and a small circulation pump 11, a cover plate 3 is installed on the upper end and front and rear sides of the box body 1 through fixing bolts 2, an inner tank 4 for placing electronic equipment is provided inside the box body 1, and sliders 6 adapted to the slide rails 5 on both sides of the box body 1 are fixedly installed on both sides of the inner tank 4;

[0032] The four corners of the inner liner 4 are provided with cavities for installing small damping rods 7. The telescopic end of each small damping rod 7 passes through the lower end of the inner liner 4 and is fixed to the T-shaped block 8 at the bottom end of the box body 1. The telescopic end of each small damping rod 7 is sleeved with a return spring 9. The two ends of the return spring 9 are in contact between the T-shaped block 8 and the inner liner 4.

[0033] An inner protective cover 10 is fixedly installed on the upper end of the inner tank 4 by screws, and a functional area for installing a small circulation pump 11 is separated inside the inner tank 4 by a partition. A buffer seat 12 is fixed at the bottom of the inner tank 4, and strip grooves 14 for plugging in special-shaped plates 13 are evenly spaced at the upper end of the buffer seat 12. The number of strip grooves 14 is consistent with the number of protruding ends at the bottom of the special-shaped plates 13. A first damping grease layer 15 is applied between the strip grooves 14 and the protruding ends of the special-shaped plates 13. The special-shaped plates 13 are fixedly installed on the lower end of the carrier plate 16, and the upper end of the carrier plate 16 is fixed to the electronic device by screws, and the outside of the electronic device is attached. There is a cooling cover 17. Considering that the vibration reduction method of airborne electronic equipment generally adopts the whole machine vibration reduction, a shock absorbing device is installed between the bottom of the box body 1 and the aircraft mounting plate, and the mounting plate is connected to the aircraft body. In order to prevent collision between airborne electronic equipment, the installation distance between the equipment needs to be increased. The shock absorbing device of this method needs to support the entire weight of the airborne electronic equipment, and there are disadvantages such as large volume of the shock absorbing device and large equipment installation space. The utility model plays a buffering and protective role for the electronic equipment installed in the inner liner 4 through the double structure of the box body 1 and the inner liner 4. When the aircraft takes off or lands and generates vibration, the vertical The impact force in the vertical direction will be buffered and protected by the damping rod, the return spring 9 and the second damping grease layer 22, and the impact force in the horizontal direction will be protected by the first damping grease layer 15 and the polyurethane buffer strip 29. In addition, since the buffer structures of the device are arranged inside the box 1, they will not occupy the space of the aircraft body. When the aircraft lands and generates a vertical impact force, the buffer spring absorbs the elastic potential energy generated by the landing vibration and then releases the elastic potential energy. In the process of releasing the elastic potential energy of the buffer spring, the telescopic end of the small damping rod 7 and the second damping grease layer 22 suppress the elastic potential energy released by the spring. In order to achieve the buffering effect, when the aircraft lands and generates a horizontal impact force, the special-shaped plate 13 at the lower end of the carrier plate 16 will move horizontally in the buffer seat 12 to suppress the horizontal impact force, that is, when each protruding end of the special-shaped plate 13 moves in the strip groove 14, it will be buffered by the first damping grease layer 15 inside the strip groove 14. During the horizontal movement of the carrier plate 16, it will be guided by the guide rod 23 at the lower end of the carrier plate 16. When the shaking amplitude is large and causes the carrier plate 16 to collide with the wall of the inner liner 4, the polyurethane buffer strip 29 will be used to buffer and protect the carrier plate 16.

[0034] Among them, the inner walls of the three cover plates 3 are fixed with sealing rings 18, the end of each fixing bolt 2 is fixed with an anti-dismantling cap, and the lower end of the end of each fixing bolt 2 is sleeved with an anti-slip gasket 19. The anti-dismantling cap is provided to protect the fixing bolt 2.

[0035] Among them, the bottom of the inner liner 4 is rectangular and fixed with four plug-in rods 20, each of which passes through the inside of a cylindrical sleeve 21 connected to the bottom end of the shell, and a second damping grease layer 22 is coated between the inner wall of the cylindrical sleeve 21 and the outer wall of the plug-in rod 20. By arranging the plug-in rod 20 to cooperate with the cylindrical sleeve 21 and the second damping grease layer 22, a buffering protection effect is played between the inner liner 4 and the box body 1. When the box body 1 is subjected to longitudinal impact force, it can not only be buffered by the small damping rod 7 in cooperation with the buffer spring, but also by the second damping grease layer 22 attached between the cylindrical sleeve 21 and the plug-in rod 20.

[0036] Among them, a plurality of groups of guide rods 23 are symmetrically fixed to the lower end of the carrier plate 16, and each group of guide rods 23 is symmetrically arranged with respect to the central axis of the special-shaped plate 13, and the number of each group of guide rods 23 is two, and the lower ends of the guide rods 23 pass through the guide grooves 24 opened at the upper end of the connecting buffer seat 12. By setting the guide rods 23 and the guide grooves 24, a guiding effect is played on the movement of the carrier plate 16 when it is subjected to a horizontal impact, so that the movement of the carrier plate 16 will move in the direction of the guide rods and the guide grooves 24.

[0037] Among them, the data wire of the electronic device can pass through the inner liner 4 and the box body 1 through the first reserved hole 25 and the second reserved hole 26. The first reserved hole 25 is opened at the front end of the inner liner 4, and the front end of the inner liner 4 is fixed with a wiring harness 27 by screws. The front end surface of the wiring harness 27 is evenly spaced with C-shaped grooves for inserting the data wires. The second reserved hole 26 is opened at the side end of the box body 1, and a cross-hole membrane 28 for fixing the data wire is provided inside the second reserved hole 26. By setting the first reserved hole 25 and the second reserved hole 26, it is convenient to pass the data wire of the electronic device through the outside of the box body 1 to connect with the airborne control system when installing the electronic device.

[0038] The side wall of the loading plate 16 is provided with a groove for installing the polyurethane buffer strip 29 , and the polyurethane buffer strip 29 is provided to prevent the side wall of the loading plate 16 from contacting and colliding with the side wall of the inner container 4 due to excessive vibration amplitude.

[0039] Among them, three heat conducting plates 30 for fitting the surface of the electronic equipment are fixedly installed on the inner wall of the cooling cover 17, and a cooling cavity 31 for the coolant to enter is opened inside the wall of the cooling cover 17. The upper end of the cooling cavity 31 passes through the partition through the delivery pipe 32 and is connected to the delivery end of the small circulation pump 11. The negative pressure end of the small circulation pump 11 passes through the inside of the coolant tank 34 through the pipeline, and one side of the coolant tank 34 passes through the partition through the circulation pipe 33 and is connected to the lower end of the cooling cavity 31. The small circulation pump 11 and the coolant tank 34 are both fixedly installed inside the inner tank 4 through the box body 35. The electronic equipment is cooled by arranging the cooling cover 17, the coolant tank 34 and the small circulation pump 11. The temperature generated by the electronic equipment during operation will be transferred to the cooling cover 17 through the heat conducting plate 30. At this time, the cooling cavity 31 inside the cooling cover 17 uses the circulating coolant to take away the generated heat, avoiding the double closed structure of the chassis and the inner tank 4 affecting the heat dissipation of the electronic equipment.

[0040] The present invention is not limited to the above-mentioned implementation modes. Anyone should be aware of the structural changes made under the inspiration of the present invention. Any technical solution that is the same or similar to the present invention falls within the protection scope of the present invention. The technology, shape, and structure that are not described in detail in the present invention are all known technologies.

Claims

1. A chassis for airborne electronic equipment, comprising a chassis (1), an inner tank (4) and a small circulation pump (11), characterized in that: The upper end and the front and rear sides of the box body (1) are both mounted with a cover plate (3) via fixing bolts (2); an inner container (4) for placing electronic equipment is provided inside the box body (1); and sliding blocks (6) adapted to the sliding rails (5) on both sides of the box body (1) are fixedly mounted on both sides of the inner container (4); The four corners of the inner liner (4) are provided with cavities for installing small damping rods (7), the telescopic end of each small damping rod (7) passes through the lower end of the inner liner (4) and is fixed to a T-shaped block (8) at the bottom end of the box body (1), and the telescopic end of each small damping rod (7) is sleeved with a return spring (9) on the outside, and the two ends of the return spring (9) are in contact between the T-shaped block (8) and the inner liner (4); An inner protective cover (10) is fixedly mounted on the upper end of the inner tank (4) by means of screws. A functional area for mounting a small circulation pump (11) is separated inside the inner tank (4) by means of a partition. A buffer seat (12) is fixed at the bottom of the inner tank (4). Strip grooves (14) for plugging in special-shaped plates (13) are formed at equal intervals on the upper end of the buffer seat (12). The number of the strip grooves (14) is the same as the number of protruding ends at the bottom of the special-shaped plates (13). A first damping grease layer (15) is applied between the strip grooves (14) and the protruding ends of the special-shaped plates (13). The special-shaped plates (13) are fixedly mounted on the lower end of a carrier plate (16). The upper end of the carrier plate (16) is fixed to an electronic device by means of screws. A cooling cover (17) is attached to the outside of the electronic device.

2. The chassis for airborne electronic equipment according to claim 1, characterized in that: The inner walls of the three cover plates (3) are all fixed with sealing rings (18), the end of each fixing bolt (2) is fixed with an anti-disassembly cap, and the lower end of the end of each fixing bolt (2) is sleeved with an anti-slip gasket (19).

3. The chassis for airborne electronic equipment according to claim 1, characterized in that: The bottom of the inner liner (4) is rectangular and fixed with four plug-in rods (20), each plug-in rod (20) passes through the inside of a cylindrical sleeve (21) connected to the bottom end of the shell, and a second damping grease layer (22) is coated between the inner wall of the cylindrical sleeve (21) and the outer wall of the plug-in rod (20).

4. The chassis for airborne electronic equipment according to claim 1, characterized in that: A plurality of groups of guide rods (23) are symmetrically fixed to the lower end of the loading plate (16), and each group of guide rods (23) is symmetrically arranged with respect to the central axis of the special-shaped plate (13). The number of guide rods (23) in each group is two, and the lower ends of the guide rods (23) pass through guide grooves (24) provided at the upper end of the connecting buffer seat (12).

5. The chassis for airborne electronic equipment according to claim 1, characterized in that: The data wire of the electronic device can pass through the inner shell (4) and the box body (1) through a first reserved hole (25) and a second reserved hole (26); the first reserved hole (25) is provided at the front end of the inner shell (4); and a wire harness (27) is fixedly mounted at the front end of the inner shell (4) by screws; the front end surface of the wire harness (27) is provided with C-shaped grooves for inserting the data wires at equal intervals; the second reserved hole (26) is provided at the side end of the box body (1); and a cross-hole film (28) for fixing the data wires is provided inside the second reserved hole (26).

6. The chassis for airborne electronic equipment according to claim 1, characterized in that: The side wall of the object carrier plate (16) is provided with a groove for installing a polyurethane buffer strip (29).

7. The chassis for airborne electronic equipment according to claim 1, characterized in that: The inner wall of the cooling cover (17) is fixedly mounted with three heat conducting plates (30) for contacting the surface of the electronic device. A cooling cavity (31) for the coolant to enter is provided inside the wall of the cooling cover (17). The upper end of the cooling cavity (31) passes through a baffle through a delivery pipe (32) and is connected to the delivery end of a small circulation pump (11). The negative pressure end of the small circulation pump (11) passes through a pipeline to the inside of a coolant tank (34). One side of the coolant tank (34) passes through a baffle through a circulation pipe (33) and is connected to the lower end of the cooling cavity (31). The small circulation pump (11) and the coolant tank (34) are both fixedly mounted inside the inner tank (4) through a box body (35).

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