CN107387528A - A kind of airspace engine protective cover - Google Patents
A kind of airspace engine protective cover Download PDFInfo
- Publication number
- CN107387528A CN107387528A CN201710657503.XA CN201710657503A CN107387528A CN 107387528 A CN107387528 A CN 107387528A CN 201710657503 A CN201710657503 A CN 201710657503A CN 107387528 A CN107387528 A CN 107387528A
- Authority
- CN
- China
- Prior art keywords
- protective cover
- circlip
- auricle
- shaft
- head cap
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000001681 protective effect Effects 0.000 title claims abstract description 28
- 238000003466 welding Methods 0.000 claims abstract description 20
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 13
- 239000010959 steel Substances 0.000 claims abstract description 13
- 238000000034 method Methods 0.000 abstract description 5
- 230000008569 process Effects 0.000 abstract description 5
- 238000011017 operating method Methods 0.000 abstract description 2
- 230000009471 action Effects 0.000 description 1
- 238000010297 mechanical methods and process Methods 0.000 description 1
- 230000005226 mechanical processes and functions Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B35/00—Screw-bolts; Stay-bolts; Screw-threaded studs; Screws; Set screws
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B77/00—Component parts, details or accessories, not otherwise provided for
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Snaps, Bayonet Connections, Set Pins, And Snap Rings (AREA)
Abstract
The invention discloses a kind of spacecraft to start machine protective cover; including protecting cover body; soket head cap screw is connected with the auricle of the protection cover body; circlip for shaft, spring and plain washer are sequentially provided with from top to bottom between the soket head cap screw and auricle; the spring upper end carries out electric welding connection with circlip for shaft; lower end carries out electric welding connection with plain washer, is connected on the outside of the circlip for shaft by steel wire or hairspring with auricle.Steel wire or hairspring one end and the side electric welding connection of circlip for shaft, the other end and auricle electric welding connection.The protective cover of the present invention solves the problems, such as that conventional engine machine protective cover fastener in disassembly process is omitted or dropped, and simplify the operating procedure of disassembling and assembling engine protective cover using fastener and protection cover body integral structure.
Description
Technical field
The present invention designs a kind of spacecraft component field, specifically a kind of airspace engine protective cover.
Background technology
At present spacecraft engine during ground general assembly is always surveyed, it is necessary to repeated multiple times disassembling and assembling engine protective cover, tradition
Start machine protective cover in disassembly process, face the dismounting of fastener, in actual mechanical process, often occur that fastener is lost
The situation leaked or dropped, serious situation can cause to damage to spaceborne equipment.
The content of the invention
In order to solve the above technical problems, the invention provides a kind of airspace engine protective cover, the protective cover is fastener
With protecting cover body integral type protective cover, avoid that in disassembly process fastener omits or drop the occurrence of.
The purpose of the present invention is achieved through the following technical solutions：A kind of spacecraft starts machine protective cover, including protective cover
Body, it is described protection cover body auricle on be connected with soket head cap screw, from upper between the soket head cap screw and auricle
Circlip for shaft, spring and plain washer are down sequentially provided with, the spring upper end carries out electric welding connection with circlip for shaft,
Lower end carries out electric welding connection with plain washer, is connected on the outside of the circlip for shaft by steel wire or hairspring with auricle.
Preferably, the circlip for shaft carries out electric welding connection with steel wire or hairspring.
Preferably, the steel wire or hairspring carry out electric welding connection with auricle.
Preferably, opened hole on the auricle, lead to according on the screwed hole digit design auricle on engine support body
The number in hole and the number of soket head cap screw.
Preferably, the nut of the soket head cap screw is provided with the annular groove to match with circlip for shaft.
Preferably, each soket head cap screw can quantify to implement screw-down torque according to related specifications, so that spring can
Pretightning force is compressed for fixed provide of soket head cap screw.
Compared with prior art, the invention has the advantages that：
The protective cover of the present invention solves conventional engine machine protective cover using fastener and protection cover body integral structure
The problem of fastener is omitted or dropped in disassembly process, and simplify the operating procedure of disassembling and assembling engine protective cover.
Brief description of the drawings
Fig. 1 is the structural representation that a kind of spacecraft of the embodiment of the present invention starts machine protective cover.
Fig. 2 is the company of soket head cap screw, circlip, spring, plain washer and steel wire or hairspring in the embodiment of the present invention
Connect structural representation.
Embodiment
With reference to specific embodiment, the present invention is described in detail.Following examples will be helpful to the technology of this area
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill to this area
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection domain.
As shown in figure 1, the embodiments of the invention provide a kind of spacecraft to start machine protective cover, including protection cover body 1, institute
State and be connected with soket head cap screw 3 on the auricle of protection cover body 1, as shown in Fig. 2 the soket head cap screw 3 and auricle it
Between be sequentially provided with circlip for shaft 4, spring 5 and plain washer 6 from top to bottom, the upper end of spring 5 is entered with circlip for shaft 4
Row electric welding connection, lower end and plain washer 6 carry out electric welding connection, the outside of circlip for shaft 4 by steel wire or hairspring 2 with
Auricle is connected.Steel wire or the one end of hairspring 2 and the side electric welding connection of circlip for shaft 4, the other end and auricle electric welding connection.
Opened hole on the auricle, according to the number of through hole on the screwed hole digit design auricle on engine support body
And the number of soket head cap screw 3, the nut of the soket head cap screw 3 are provided with the annular groove to match with circlip for shaft 4,
Each soket head cap screw 3 can quantify to implement screw-down torque according to related specifications, so that spring 5 can be soket head cap screw 3
Fixed provide compress pretightning force.
This specific implementation starts machine protective cover in disassembly process, it is not necessary to carries fastener, it is only necessary to carries and interior six
The inner hexagon spanner that angle screw 3 matches, start machine protective cover during ground is deposited, hexagonal in each can be incited somebody to action with plain nut
Screw 3 is temporarily fixed on the through hole on protection cover body auricle.
This specific implementation is completed to assemble by following steps：
1st, the nut of soket head cap screw 3 is slotted according to circlip for shaft 3 with notch；
2nd, circlip for shaft 3 is installed on the nut of soket head cap screw 3；
3rd, circlip for shaft 4 is carried out into spot welding with spring 5 to be connected；
4th, spring 5 is carried out into spot welding with plain washer 6 to be connected；
5th, circlip for shaft 4 is carried out into spot welding with steel wire or hairspring 2 to be connected；
6th, steel wire or hairspring 2 are carried out into spot welding with the protection auricle of cover body 1 to be connected；
So far, airspace engine protective cover assembling finishes.
The specific embodiment of the present invention is described above.It is to be appreciated that the invention is not limited in above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring the substantive content of the present invention.
Claims (6)
1. a kind of spacecraft starts machine protective cover, including protection cover body, it is characterised in that on the auricle of the protection cover body
Soket head cap screw is connected with, circlip for shaft, bullet are sequentially provided with from top to bottom between the soket head cap screw and auricle
Spring and plain washer, the spring upper end carry out electric welding connection with circlip for shaft, and lower end carries out electric welding connection, institute with plain washer
State and be connected on the outside of circlip for shaft by steel wire or hairspring with auricle.
2. a kind of spacecraft as claimed in claim 1 starts machine protective cover, it is characterised in that the circlip for shaft and steel
Silk or hairspring carry out electric welding connection.
3. a kind of spacecraft as claimed in claim 1 starts machine protective cover, it is characterised in that the steel wire or hairspring and ear
Piece carries out electric welding connection.
4. spacecraft according to claim 1 starts machine protective cover to design, it is characterised in that opened hole on the auricle,
According to the number of through hole and the number of soket head cap screw on the screwed hole digit design auricle on engine support body.
5. spacecraft according to claim 1 starts machine protective cover to design, it is characterised in that the soket head cap screw 3
Nut is provided with the annular groove to match with circlip for shaft.
6. spacecraft according to claim 1 starts machine protective cover to design, it is characterised in that each soket head cap screw can root
Quantify to implement screw-down torque according to related specifications, so that spring can compress pretightning force for fixed provide of soket head cap screw.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710657503.XA CN107387528A (en) | 2017-08-03 | 2017-08-03 | A kind of airspace engine protective cover |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710657503.XA CN107387528A (en) | 2017-08-03 | 2017-08-03 | A kind of airspace engine protective cover |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107387528A true CN107387528A (en) | 2017-11-24 |
Family
ID=60343170
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710657503.XA Pending CN107387528A (en) | 2017-08-03 | 2017-08-03 | A kind of airspace engine protective cover |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107387528A (en) |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE389325C (en) * | 1924-02-05 | Voigt & Haeffner Akt Ges | Spring-loaded screw locking device for adjusting screws with non-round head | |
| JPH09273532A (en) * | 1996-04-05 | 1997-10-21 | Nitsuko Corp | Cover installation device for box |
| JP2003113828A (en) * | 2001-10-01 | 2003-04-18 | Ishikawajima Harima Heavy Ind Co Ltd | Bolt-dispersion preventing device |
| US20030210968A1 (en) * | 2002-05-13 | 2003-11-13 | Harold Miyamura | Fastener assembly |
| KR20050039997A (en) * | 2003-10-27 | 2005-05-03 | 한국항공우주산업 주식회사 | Bolt to prevent loss |
| CN201507525U (en) * | 2009-09-08 | 2010-06-16 | 华为技术有限公司 | Anti-drop screw kit |
| JP4532955B2 (en) * | 2004-03-25 | 2010-08-25 | テンパール工業株式会社 | Screwed member |
| CN104416622A (en) * | 2013-09-11 | 2015-03-18 | 山彦股份有限公司 | Structure for preventing falling of fastening nut, and fastening nut anchor member |
| CN106015266A (en) * | 2016-06-24 | 2016-10-12 | 天津雷沃动力有限公司 | Looseness-prevention connecting structure with controllable pretightening force of engine cylinder head cover |
| CN206054496U (en) * | 2016-09-27 | 2017-03-29 | 上海爱瑞德五金有限公司 | A kind of anti-fall adjusting screw |
-
2017
- 2017-08-03 CN CN201710657503.XA patent/CN107387528A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE389325C (en) * | 1924-02-05 | Voigt & Haeffner Akt Ges | Spring-loaded screw locking device for adjusting screws with non-round head | |
| JPH09273532A (en) * | 1996-04-05 | 1997-10-21 | Nitsuko Corp | Cover installation device for box |
| JP2003113828A (en) * | 2001-10-01 | 2003-04-18 | Ishikawajima Harima Heavy Ind Co Ltd | Bolt-dispersion preventing device |
| US20030210968A1 (en) * | 2002-05-13 | 2003-11-13 | Harold Miyamura | Fastener assembly |
| KR20050039997A (en) * | 2003-10-27 | 2005-05-03 | 한국항공우주산업 주식회사 | Bolt to prevent loss |
| JP4532955B2 (en) * | 2004-03-25 | 2010-08-25 | テンパール工業株式会社 | Screwed member |
| CN201507525U (en) * | 2009-09-08 | 2010-06-16 | 华为技术有限公司 | Anti-drop screw kit |
| CN104416622A (en) * | 2013-09-11 | 2015-03-18 | 山彦股份有限公司 | Structure for preventing falling of fastening nut, and fastening nut anchor member |
| CN106015266A (en) * | 2016-06-24 | 2016-10-12 | 天津雷沃动力有限公司 | Looseness-prevention connecting structure with controllable pretightening force of engine cylinder head cover |
| CN206054496U (en) * | 2016-09-27 | 2017-03-29 | 上海爱瑞德五金有限公司 | A kind of anti-fall adjusting screw |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20171124 |
|
| RJ01 | Rejection of invention patent application after publication |