CN214577375U

CN214577375U - Engine protection device for small aircraft falling

Info

Publication number: CN214577375U
Application number: CN202120972772.7U
Authority: CN
Inventors: 吴亚伦
Original assignee: Individual
Current assignee: Individual
Priority date: 2021-05-08
Filing date: 2021-05-08
Publication date: 2021-11-02
Anticipated expiration: 2031-05-08

Abstract

The utility model discloses an engine protection device for the falling of a small aircraft, which comprises a bottom plate and a protection box, wherein the bottom plate is arranged at the bottom of the protection box, a heat dissipation mechanism is arranged in the bottom plate, the protection mechanism is arranged on the periphery of the inner wall of the protection box and on the bottom surface of an inner cavity, first through holes are arranged on the periphery of the protection box in an array manner, the first through holes are communicated with the protection box, a square frame plate is arranged on the periphery top of the protection box, bolts are arranged at four corners of the bottom of the square frame plate, the tail ends of the bolts penetrate through the square frame plate, the heat dissipation mechanism comprises a fan, a mounting groove, a wind guide hole, a second through hole and a fixing component, the utility model has simple structure and reasonable design, when the small aircraft falls, the engine in the protection box can be subjected to shock absorption protection, and when the engine is protected by the heat dissipation mechanism, the engine can be better cooled, and the practicality is strong.

Description

Engine protection device for small aircraft falling

Technical Field

The utility model relates to an engine protection device for small aircraft falls belongs to aircraft technical field.

Background

For small aircraft, the engine often faces various problems when using, wherein need protect with the engine guard shield in the engine position of aircraft usually, when small aircraft takes place to fall, better protect the engine, can reduce the damage degree of engine to when using protection device to protect the engine, will make it not influence the radiating effect of engine, for this reason, provide an engine protection device that is used for small aircraft to fall.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an engine protection device for small aircraft falls to solve the problem that proposes among the above-mentioned background art.

In order to achieve the above object, the utility model provides a following technical scheme:

the utility model provides an engine protection device for small aircraft falls, includes bottom plate and protective housing, the bottom plate sets up in the protective housing bottom, be provided with heat dissipation mechanism in the bottom plate, protective housing inner wall all around and the inner chamber bottom surface all be provided with protection mechanism, first through-hole has all been seted up to the array all around to the protective housing, just first through-hole link up the protective housing, the protective housing top all around is provided with square frame board, square frame board bottom four corners is provided with the bolt, the bolt tail end runs through square frame board.

Further, the heat dissipation mechanism comprises a fan, a mounting groove, a groove, air guide holes, second through holes and a fixing component, the mounting groove is formed in the top of the bottom plate, the fan is arranged in the mounting groove, the groove is formed in the bottom plate and is formed in the bottom of the mounting groove, the air guide holes are formed in the periphery of the bottom plate at equal intervals, the air guide holes are communicated with the groove, the second through holes are formed in the bottom of the protection box in an array mode, and the fan is connected with the bottom plate through the fixing component.

Further, fixed subassembly includes fixed slot, fixed plate, gim peg, connecting plate and handle, the fixed slot symmetry is seted up in the bottom plate front side, just the fixed slot is linked together with the mounting groove, the connecting plate sets up in the fan front side, just the connecting plate is in the mounting groove, the fixed plate symmetry sets up in the connecting plate both sides, just the fixed plate agrees with and sets up in the fixed slot, the gim peg sets up in the fixed plate front side, just the gim peg tail end runs through fixed plate and bottom plate threaded connection, the handle sets up in the connecting plate front side.

Further, the length of the groove is smaller than that of the mounting groove.

Further, protection mechanism includes protection shield and attenuator, the protection shield sets up around the protective housing inner wall and inner chamber bottom surface, the attenuator sets up between protection shield and protective housing, just the attenuator both ends are connected with protection shield and protective housing respectively.

Furthermore, a third through hole is formed in the protection plate in an array mode.

The utility model has the advantages that:

1. through protection mechanism, when small aircraft falls, can carry out the shock attenuation protection for the engine in the protective housing to through heat dissipation mechanism, when using the device to protect the engine, can be better dispel the heat to the engine.

2. Through setting up the third through-hole, guarantee the mobility of air in the protective housing, make the length of recess be less than the length of mounting groove, make the better flow of air in the recess, the practicality is strong.

Drawings

The accompanying drawings are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention, and together with the description serve to explain the invention and not to limit the invention.

FIG. 1 is a view of an engine protection device for a crash of a small aircraft according to the present invention;

FIG. 2 is a view of the engine protection device for a crash of a small aircraft of the present invention;

FIG. 3 is a view of the engine protection device for a crash of a small aircraft of the present invention;

FIG. 4 is a view of the engine protection device for a crash of a small aircraft of the present invention;

reference numbers in the figures: 1. a base plate; 2. a protective box; 3. a first through hole; 4. a square frame plate; 5. a bolt; 6. a fan; 7. mounting grooves; 8. a groove; 9. a wind guide hole; 10. a second through hole; 11. fixing grooves; 12. a fixing plate; 13. a fixing bolt; 14. a connecting plate; 15. a handle; 16. a protection plate; 17. a damper; 18. a third via.

Detailed Description

The preferred embodiments of the present invention will be described in conjunction with the accompanying drawings, and it will be understood that they are presented herein only to illustrate and explain the present invention, and not to limit the present invention.

Referring to fig. 1-4, the present invention provides a technical solution: the utility model provides an engine protection device for small aircraft falls, includes bottom plate 1 and protective housing 2, bottom plate 1 sets up in protective housing 2 bottom, be provided with heat dissipation mechanism in the bottom plate 1, protective housing 2 inner wall all around and the inner chamber bottom surface all is provided with protection mechanism, first through-hole 3 has all been seted up to protective housing 2 array all around, just first through-hole 3 link up protective housing 2, protective housing 2 top all around is provided with

square frame plate

4, 4 bottom four corners of square frame plate are provided with bolt 5, bolt 5 tail ends run through square frame plate 4.

Specifically, as shown in fig. 2 to 4, the heat dissipation mechanism includes a fan 6, a mounting groove 7, a groove 8, an air guide hole 9, a second through hole 10, and a fixing component, the mounting groove 7 is provided at the top of the bottom plate 1, the fan 6 is disposed in the mounting groove 7, the groove 8 is provided in the bottom plate 1, the groove 8 is disposed at the bottom of the mounting groove 7, the air guide holes 9 are respectively provided at the periphery of the bottom plate 1 at equal intervals, the air guide holes 9 are communicated with the groove 8, the second through hole 10 is arranged at the bottom of the protection box 2 in an array manner, the fan 6 is connected with the bottom plate 1 through the fixing component, and when the device is used for protecting the engine, the engine can be better cooled.

Specifically, as shown in fig. 3 and 4, the fixing assembly includes a fixing groove 11, a fixing plate 12, a fixing bolt 13, a connecting plate 14 and a handle 15, the fixing groove 11 is symmetrically opened at the front side of the bottom plate 1, the fixing groove 11 is communicated with the mounting groove 7, the connecting plate 14 is arranged at the front side of the fan 6, the connecting plate 14 is located in the mounting groove 7, the fixing plate 12 is symmetrically arranged at two sides of the connecting plate 14, the fixing plate 12 is engaged with the fixing groove 11, the fixing bolt 13 is arranged at the front side of the fixing plate 12, the tail end of the fixing bolt 13 penetrates through the fixing plate 12 to be in threaded connection with the bottom plate 1, and the handle 15 is arranged at the front side of the connecting plate 14 to fixedly connect the fan 6 and the bottom plate 1.

Specifically, as shown in fig. 2, the length of the groove 8 is smaller than that of the mounting groove 7, so that air in the groove 8 can flow better.

Specifically, as shown in fig. 1 and 2, the protection mechanism includes a protection plate 16 and a damper 17, the protection plate 16 is disposed on the periphery of the inner wall of the protection box 2 and on the bottom surface of the inner cavity, the damper 17 is disposed between the protection plate 16 and the protection box 2, and two ends of the damper 17 are respectively connected with the protection plate 16 and the protection box 2, so that when the small aircraft falls, the engine in the protection box 2 can be protected by shock absorption.

Specifically, as shown in fig. 1, third through holes 18 are formed in the protective plate 16 in an array manner, so as to ensure the flowability of air in the protective box 2.

The utility model discloses the theory of operation: use square framed panel 4 and bolt 5, install protection box 2 fixedly, when using the engine, be fan 6 power supply through external power supply, open fan 6, through first through-hole 3, second through-hole 10, recess 8 and wind-guiding hole 9, heat discharge in the protection box 2, better dispel the heat to the engine, and when small aircraft takes place to fall, through protection mechanism, can be better protect the engine, set up third through-hole 18, guarantee the mobility of air in the protection box 2, make the length of recess 8 be less than the length of mounting groove 7, make the better flow of the air in the recess 8.

The above is the preferred embodiment of the present invention, and the technical personnel in the field of the present invention can also change and modify the above embodiment, therefore, the present invention is not limited to the above specific embodiment, and any obvious improvement, replacement or modification made by the technical personnel in the field on the basis of the present invention all belong to the protection scope of the present invention.

Claims

1. An engine protection device for the crash of small aircraft, comprising a base plate (1) and a protection box (2), characterized in that: the protection box is characterized in that the bottom plate (1) is arranged at the bottom of the protection box (2), a heat dissipation mechanism is arranged in the bottom plate (1), the inner wall of the protection box (2) is provided with a protection mechanism all around and the bottom surface of the inner cavity, first through holes (3) are formed in the protection box (2) in an array mode all around, the first through holes (3) are communicated with the protection box (2), the top of the protection box (2) all around is provided with square frame plates (4), bolts (5) are arranged at four corners of the bottom of each square frame plate (4), and tail ends of the bolts (5) run through the square frame plates (4).

2. The engine protection device for a small aircraft crash of claim 1, wherein: the heat dissipation mechanism comprises a fan (6), a mounting groove (7), a groove (8), air guide holes (9), second through holes (10) and a fixing component, wherein the mounting groove (7) is formed in the top of the bottom plate (1), the fan (6) is arranged in the mounting groove (7), the groove (8) is formed in the bottom plate (1), the groove (8) is formed in the bottom of the mounting groove (7), the air guide holes (9) are respectively formed in the periphery of the bottom plate (1) at equal intervals, the air guide holes (9) are communicated with the groove (8), the second through holes (10) are arranged at the bottom of the protection box (2) in an array mode, and the fan (6) is connected with the bottom plate (1) through the fixing component.

3. The engine protection device for a small aircraft crash of claim 2, wherein: fixed subassembly includes fixed slot (11), fixed plate (12), gim peg (13), connecting plate (14) and handle (15), bottom plate (1) front side is seted up to fixed slot (11) symmetry, just fixed slot (11) are linked together with mounting groove (7), connecting plate (14) set up in fan (6) front side, just connecting plate (14) are in mounting groove (7), fixed plate (12) symmetry sets up in connecting plate (14) both sides, just fixed plate (12) agree with and set up in fixed slot (11), gim peg (13) set up in fixed plate (12) front side, just gim peg (13) tail end runs through fixed plate (12) and bottom plate (1) threaded connection, handle (15) set up in connecting plate (14) front side.

4. The engine protection device for a small aircraft crash of claim 2, wherein: the length of the groove (8) is smaller than that of the mounting groove (7).

5. The engine protection device for a small aircraft crash of claim 1, wherein: protection mechanism includes protection shield (16) and attenuator (17), protection shield (16) set up around protective housing (2) inner wall and inner chamber bottom surface, attenuator (17) set up between protection shield (16) and protective housing (2), just attenuator (17) both ends are connected with protection shield (16) and protective housing (2) respectively.

6. The engine protection device for a small aircraft crash of claim 5, wherein: and third through holes (18) are formed in the protective plate (16) in an array manner.