CN210653681U

CN210653681U - Aircraft engine protective cover

Info

Publication number: CN210653681U
Application number: CN201921744629.1U
Authority: CN
Inventors: 高杰
Original assignee: Spring Airlines Technology Development Jiangsu Co ltd
Current assignee: Spring Airlines Technology Development Jiangsu Co ltd
Priority date: 2019-10-17
Filing date: 2019-10-17
Publication date: 2020-06-02
Anticipated expiration: 2029-10-17

Abstract

The utility model discloses an aircraft engine protection casing, the rain cover comprises a cover body, the cover body is connected by end shield and one end the first cover and the second cover of end shield opening end enclose to close and form, the bottom both sides of first cover respectively with the top both sides detachably of second cover is connected, second cover is kept away from the one end of end shield is sealed, first cover is kept away from the one end of end shield is uncovered, the opening department of first cover is equipped with and is used for tightening up this open binding off mechanism. The utility model discloses simple structure installs and removes convenient and fast, can prevent effectively that sand blown by the wind from invading the engine.

Description

Aircraft engine protective cover

Technical Field

The utility model relates to an aircraft engine protection device, concretely relates to aircraft engine protection casing.

Background

The aircraft engine is a highly complex and precise thermal machine, and is used as the heart of an aircraft, not only as the power for flying the aircraft, but also as an important driving force for promoting the development of aviation industry. At present, in areas with serious wind and sand, because an aircraft engine has a large volume, a large amount of wind and sand are scraped into an engine cabin during the parking of the aircraft, the cleaning is very inconvenient, and if the wind and sand cannot be cleaned, the normal and safe operation of the aircraft is difficult to ensure. The utility model discloses a prevent sand blown by the wind invasion engine and design.

SUMMERY OF THE UTILITY MODEL

To the defect among the prior art, the utility model provides a simple structure installs and removes convenient and fast, can effectively prevent the aircraft engine protection casing of sand blown by the wind invasion engine, effectively reduces the clearance degree of difficulty of aircraft engine to the sand blown by the wind, guarantees that the aircraft is normal, safe work.

The utility model provides an above-mentioned technical problem adopted technical scheme as follows:

the utility model provides an aircraft engine protection casing, includes the cover body, the cover body is connected by end shield and one end the first cover and the second cover of end shield opening end enclose to close and form, the bottom both sides of first cover respectively with the top both sides detachably of second cover is connected, second cover is kept away from the one end of end shield is sealed, first cover is kept away from the one end of end shield is uncovered, the opening department of first cover is equipped with and is used for tightening up this open binding off mechanism.

The beneficial effects of the utility model are embodied in: the closing mechanism is loosened, the cover body is unfolded after the connection of the upper half cover and the lower half cover is disassembled, the end cover is sleeved on the front portion of the aircraft engine, one end, far away from the end cover, of the upper half cover is pulled to move to the position of an aircraft hanger along the length extending direction of the aircraft engine, the opening end of the upper half cover is tightened to the position of the aircraft hanger by the tightening closing mechanism, one end, far away from the end cover, of the lower half cover is pulled to move to the tail portion of the aircraft engine along the length extending direction of the aircraft engine, the tail portion of the aircraft engine is tightly sleeved at the sealing position of the lower half cover, and finally the upper half cover and the lower half cover are connected.

Furthermore, two sides of the bottom of the upper half cover are respectively detachably connected with two sides of the top of the lower half cover through zippers.

The beneficial effect of adopting the further technical scheme is that: the upper half cover and the lower half cover are convenient to disassemble and assemble, and the disassembling and assembling efficiency of the protective cover is improved.

Further, the binding off mechanism includes binding off meshbelt, eye-splice A and supplies the meshbelt soft cannula that the binding off meshbelt passed, meshbelt soft cannula follows first uncovered edge setting of cover, the both ends of binding off meshbelt are connected respectively the son end and the mother end of eye-splice A.

The beneficial effect of adopting the further technical scheme is that: through the length of receiving and releasing the binding off meshbelt and being connected with eye-splice A, can the uncovered of the first half cover of elasticity, promote the efficiency of receiving and releasing of binding off mechanism, and then promote the efficiency of installing and removing of this protection casing.

Furthermore, the mesh belt soft sleeve is made of cloth and is sewn and fixed on the edge of the opening of the upper half cover.

The beneficial effect of adopting the further technical scheme is that: the binding off braid can smoothly pass through the braid soft sleeve, and the reliability of connection of the braid soft sleeve and the opening edge of the upper half cover is ensured.

Further, the end cover, the upper half cover and the lower half cover are all made of oxford cloth.

The beneficial effect of adopting the further technical scheme is that: make this protection casing possess excellent waterproof performance and structural strength.

Further, the surfaces of the end shield, the upper half shield and the lower half shield are plated with flame-retardant coatings.

The beneficial effect of adopting the further technical scheme is that: the protective cover has excellent fireproof performance.

Further, a tightening mechanism for tightening the cover body is arranged between the upper half cover and the lower half cover.

The beneficial effect of adopting the further technical scheme is that: the reliability of the cover body sleeved on the aircraft engine is improved.

Further, tightening mechanism includes a plurality of tightening braid groups and with each tighten up the eye-splice B that the braid group cooperation was used, tighten up the braid group and tighten up the braid by first tightening up the braid and constitute with the second, the one end that first tightening up the braid and the second tightened up the braid is connected respectively first cover and second cover, and the other end is connected corresponding eye-splice B's son end and female end respectively.

The beneficial effect of adopting the further technical scheme is that: the connection length of the first tightening woven belt or the second tightening woven belt and the eye-splice B is shortened, so that the tightening mechanism can tighten or loosen the cover body, the operation is convenient and quick, and the tightening of the cover body is stable and reliable.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the technical solutions in the prior art will be briefly described below. Throughout the drawings, like elements or portions are generally identified by like reference numerals. In the drawings, elements or portions are not necessarily drawn to scale.

Fig. 1 is a schematic structural diagram of an embodiment of the present invention.

In the attached drawing, 1-end cover, 2-lower half cover, 3-upper half cover, 4-soft sleeve of woven tape, 5-eye-splice A, 6-closing woven tape, 7-zipper, 8-second tightening woven tape, 9-eye-splice B, 10-first tightening woven tape.

Detailed Description

Embodiments of the present invention will be described in detail below with reference to the accompanying drawings. The following examples are only for illustrating the technical solutions of the present invention more clearly, and therefore are only examples, and the protection scope of the present invention is not limited thereby.

It is to be noted that unless otherwise specified, technical or scientific terms used herein shall have the ordinary meaning as understood by those skilled in the art to which the present invention belongs.

As shown in fig. 1, an aircraft engine protection cover, which comprises a cover body, the cover body is enclosed by end shield 1 and the first cover 3 and the second cover 2 that one end is connected with the open end of end shield 1 and closes and forms, the bottom both sides of first cover 3 are connected with the top both sides detachably of second cover 2 through zip fastener 7 respectively, the one end that end shield 1 was kept away from to second cover 2 is sealed, the one end that end shield 1 was kept away from to first cover 3 is uncovered, the opening department of first cover 3 is equipped with and is used for tightening up this uncovered binding off mechanism, binding off mechanism is including binding off meshbelt 6, eye-splice A5 and the meshbelt soft cannula 4 that supplies binding off meshbelt 6 to pass, meshbelt soft cannula 4 sets up along the uncovered edge of first cover 3, the son end and the female end of eye-splice A5 are connected respectively to the.

A tightening mechanism for tightening the cover body is arranged between the upper half cover 3 and the lower half cover 2, the tightening mechanism comprises a plurality of tightening braid sets and buckles B9 matched with the tightening braid sets, each tightening braid set comprises a first tightening braid 10 and a second tightening braid 8, one ends of the first tightening braid 10 and the second tightening braid 8 are respectively connected with the upper half cover 3 and the lower half cover 2, and the other ends of the first tightening braid 10 and the second tightening braid 8 are respectively connected with the male end and the female end of the corresponding buckle B9.

Preferably, the webbing soft sleeve 4 is made of cloth and is sewn and fixed on the open edge of the upper half cover 3.

Preferably, the end shield 1, the upper half shield 3 and the lower half shield 2 are all made of oxford cloth.

Preferably, the surfaces of the end shield 1, the upper half shield 3 and the lower half shield 2 are all plated with a flame retardant coating.

The use method comprises the following steps:

lengthening the connection length of the closing-in woven belt 6 and the eye-splice A5 to loosen the opening of the upper half cover 3, separating the connection of the male end and the female end of the eye-splice A5 and the connection of the male end and the female end of each eye-splice B9, unfolding the cover body after unzipping the zipper 7 between the upper half cover 3 and the lower half cover 2, sleeving the end cover 1 on the front part of the aircraft engine, pulling one end of the upper half cover 3 away from the end cover 1 to the aircraft hanger position along the aircraft engine length extension direction, pulling the closing-in woven belt 6 to make the opening of the upper half cover 3 surround the aircraft hanger and then insert the male end and the female end of the eye-splice A5, retracting the connection length of the closing-in woven belt 6 and the eye-splice A5 to tighten the opening of the upper half cover 3 at the aircraft hanger position, then pulling one end of the lower half cover 2 away from the end cover 1 to make the aircraft engine length extension direction along the aircraft engine tail, and tightly sleeving the zipper 7 between the upper half cover 3 and the lower half cover 2 by pulling the sealing part, finally, the connection of the male end and the female end of each buckle B9 is inserted, and the connection length of the first tightening woven tape 10 or the second tightening woven tape 8 and the buckle B9 is shortened to tighten the cover body.

Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; such modifications and substitutions do not substantially depart from the scope of the embodiments of the present invention, and are intended to be covered by the claims and the specification.

Claims

1. An aircraft engine protective cover, characterized in that: including the cover body, the cover body is connected by end shield (1) and one end the first half cover (3) of end shield (1) opening end and second half cover (2) enclose to close and form, the bottom both sides of first half cover (3) respectively with the top both sides detachably of second half cover (2) connects, second half cover (2) are kept away from the one end of end shield (1) seals, first half cover (3) are kept away from the one end of end shield (1) is uncovered, the opening department of first half cover (3) is equipped with and is used for tightening up this uncovered binding off mechanism.

2. An aircraft engine protective cover according to claim 1, wherein: the two sides of the bottom of the upper half cover (3) are respectively detachably connected with the two sides of the top of the lower half cover (2) through zippers (7).

3. An aircraft engine protective cover according to claim 1, wherein: the binding off mechanism includes binding off meshbelt (6), eye-splice A (5) and supplies the soft sleeve pipe of meshbelt (4) that binding off meshbelt (6) passed, soft sleeve pipe of meshbelt (4) are followed the uncovered edge setting of first half cover (3), the both ends of binding off meshbelt (6) are connected respectively the son end and the mother end of eye-splice A (5).

4. An aircraft engine protective cover according to claim 3, wherein: the mesh belt soft sleeve (4) is made of cloth and is sewn and fixed on the edge of the opening of the upper half cover (3).

5. An aircraft engine protective cover according to claim 1, wherein: the end cover (1), the upper half cover (3) and the lower half cover (2) are all made of oxford cloth.

6. An aircraft engine protective cover according to claim 1, wherein: the surfaces of the end shield (1), the upper half shield (3) and the lower half shield (2) are plated with flame-retardant coatings.

7. An aircraft engine protective cover according to any one of claims 1 to 6, wherein: and a tightening mechanism for tightening the cover body is arranged between the upper half cover (3) and the lower half cover (2).

8. An aircraft engine protective cover according to claim 7, wherein: tightening mechanism includes a plurality of tightening braid group and with each tighten up eye-splice B (9) that the cooperation of braid group used, tighten up the braid group and tighten up meshbelt (8) by first tightening up meshbelt (10) and second and constitute, the one end that first tightening up meshbelt (10) and second tightened up meshbelt (8) is connected respectively first cover (3) and second cover (2), and the other end is connected the son end and the female end of corresponding eye-splice B (9) respectively.