CN110185700A - Space flight dynamic sealing type crankshaft - Google Patents
Space flight dynamic sealing type crankshaft Download PDFInfo
- Publication number
- CN110185700A CN110185700A CN201910314971.6A CN201910314971A CN110185700A CN 110185700 A CN110185700 A CN 110185700A CN 201910314971 A CN201910314971 A CN 201910314971A CN 110185700 A CN110185700 A CN 110185700A
- Authority
- CN
- China
- Prior art keywords
- dynamic sealing
- space flight
- crank
- sealing type
- type crankshaft
- 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.)
- Withdrawn
Links
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
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C3/00—Shafts; Axles; Cranks; Eccentrics
- F16C3/04—Crankshafts, eccentric-shafts; Cranks, eccentrics
- F16C3/06—Crankshafts
- F16C3/08—Crankshafts made in one piece
-
- 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
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C2204/00—Metallic materials; Alloys
- F16C2204/60—Ferrous alloys, e.g. steel alloys
- F16C2204/62—Low carbon steel, i.e. carbon content below 0.4 wt%
-
- 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
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C2204/00—Metallic materials; Alloys
- F16C2204/60—Ferrous alloys, e.g. steel alloys
- F16C2204/70—Ferrous alloys, e.g. steel alloys with chromium as the next major constituent
- F16C2204/72—Ferrous alloys, e.g. steel alloys with chromium as the next major constituent with nickel as further constituent, e.g. stainless steel
-
- 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
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C2223/00—Surface treatments; Hardening; Coating
- F16C2223/02—Mechanical treatment, e.g. finishing
-
- 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
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C2223/00—Surface treatments; Hardening; Coating
- F16C2223/10—Hardening, e.g. carburizing, carbo-nitriding
- F16C2223/14—Hardening, e.g. carburizing, carbo-nitriding with nitriding
-
- 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
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C2326/00—Articles relating to transporting
- F16C2326/47—Cosmonautic vehicles, i.e. bearings adapted for use in outer-space
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Ocean & Marine Engineering (AREA)
- Mechanical Engineering (AREA)
- Shafts, Cranks, Connecting Bars, And Related Bearings (AREA)
- Solid-Phase Diffusion Into Metallic Material Surfaces (AREA)
Abstract
The present invention provides a kind of space flight dynamic sealing type crankshafts, are made of tow-away zone and input area two large divisions, including rear axle, crank and crank throw；Input area includes: leading portion axis, dynamic sealing face, internal spline and centring hole.Crankshaft external diameter is small, light-weight, meets space flight miniaturization use demand；It is made of 2Cr13, it is corrosion-resistant, it is wear-resistant, meet space environment lower long-life use demand；Design has front end axis and a rear axle, and when duplex bearing supported design guarantee use axially and radially beats small；Crank throw is handled using glow discharge nitriding, improves points hardness, promotes wearability；Milled processed and glow discharge nitriding are passed through in dynamic sealing face, have high-wearing feature and reliable leakproofness；Internal spline connection type realizes large torque input；Front end axis interior design has centring hole, promotes accuracy of alignment.
Description
Technical field
The present invention relates to space industries, and in particular, to a kind of space flight dynamic sealing type crankshaft.
Background technique
The various engineering goods that space technology uses at present are limited by spacecraft size, the crankshaft suitable for ground environment
Generally do not have sealability, weight and volume is larger, can not be suitable for space industry.Therefore it develops a kind of suitable for space flight
The crankshaft of the mini zone sealing structure of product very it is necessary to.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide a kind of space flight dynamic sealing type crankshafts.
A kind of space flight dynamic sealing type crankshaft provided according to the present invention, including revolution area assembly, input area assembly；Revolution
Area assembly is closely connect with input area assembly, is processed integrally formed.
Preferably, the revolution area assembly, input area assembly are made of 2Cr13.
Preferably, the revolution area assembly includes rear axle, crank and crank throw；
Crank includes the first crank portion, the second crank portion, and one end of crank throw connects the side of the first crank portion, crank throw it is another
One end connects the side of the second crank portion；
Rear axle is connected with the other side of the first crank portion；The other side of second crank portion is connect with input area assembly.
Preferably, the input area assembly includes leading portion axis, dynamic sealing face, internal spline and centring hole；
One end of leading portion axis with revolution area assembly connect, the other end of leading portion axis is connect with dynamic sealing face, leading portion axis it is another
One end is inserted into dynamic sealing face；
In dynamic sealing face, the axial direction of leading portion axis is provided with centring hole, the end of centring hole connects internal spline.
Preferably, the crank throw is handled using glow discharge nitriding, to improve points hardness and wearability.
Preferably, the dynamic sealing face is handled by milled processed and glow discharge nitriding, to improve hardness and roughness.
Preferably, the internal spline uses small outside diameter structure.
Preferably, the centring hole is arranged inside the axis of front end, centering can be connected, to improve accuracy of alignment.
Preferably, the top setting internal spline of the leading portion axis connects, to realize that large torque inputs.
Preferably, the centring hole, internal spline are set as engraved structure, can reduce weight.
Compared with prior art, the present invention have it is following the utility model has the advantages that
1, crankshaft can be directly made up of machining using integrated fabrication design, and crankshaft external diameter is small, light-weight, full
Sufficient space flight minimizes use demand；
2, it is made of 2Cr13, realizes corrosion-resistant, wear-resistant property；Crank throw and dynamic sealing ensure that using glow discharge nitriding
The hardness in face, further increases antiwear characteristic；
3, front end axis is designed as internal spline connection structure, and is provided centrally with centring hole, meets large torque input demand, together
Shi Tisheng accuracy of alignment mitigates weight.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
Fig. 1 is space flight dynamic sealing type crankshaft structure schematic diagram；
Fig. 2 is space flight dynamic sealing type crankshaft spline schematic diagram.
In the figure, it is marked as 1-rear axle, 2-cranks, 3-crank throws, 4-front end axis, 5-dynamic sealing faces, 6-internal splines,
7-centring hole.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, several changes and improvements can also be made.These belong to the present invention
Protection scope.
A kind of space flight dynamic sealing type crankshaft provided according to the present invention, including revolution area assembly, input area assembly；
Revolution area assembly is closely connect with input area assembly, and processing is integrally formed, and integrated design can directly pass through machinery
It is processed into.
Specifically, the revolution area assembly, input area assembly are made of 2Cr13, corrosion-resistant, wear-resistant, to meet sky
Between environment lower long-life use demand.
Specifically, the revolution area assembly includes rear axle 1, crank 2 and crank throw 3；
Crank 2 includes the first crank portion, the second crank portion, and one end of crank throw 3 connects the side of the first crank portion, crank throw 3
The other end connect the second crank portion side；
Rear axle 1 is connected with the other side of the first crank portion；The other side of second crank portion is connect with input area assembly.
Specifically, the input area assembly includes leading portion axis 4, dynamic sealing face 5, internal spline 6 and centring hole 7；
One end of leading portion axis 4 is connect with revolution area assembly, and the other end of leading portion axis 4 is connect with dynamic sealing face 5, leading portion axis 4
The other end be inserted into dynamic sealing face 5；
In dynamic sealing face 5, the axial direction of leading portion axis 4 is provided with centring hole 7, the end of centring hole 7 connects internal spline 6.It is excellent
Selection of land, is provided with front end axis 4 and rear axle 1, and when duplex bearing supported design guarantee use axially and radially beats small.
Specifically, the crank throw 3 is handled using glow discharge nitriding, to improve points hardness and wearability.
Specifically, the dynamic sealing face 5 is handled by milled processed and glow discharge nitriding, high to improve hardness and roughness
Hardness ensure that high-wearing feature, high roughness ensure that the validity of dynamic sealing.
Specifically, the internal spline 6 uses small outside diameter structure, to realize that large torque inputs.Preferably, crankshaft of the invention
It is whole using small outer through structure, it is light-weight, to meet space flight miniaturization use demand.
Specifically, the centring hole 7 is arranged inside front end axis 4, centering can be connected, to improve accuracy of alignment, and energy
Enough losss of weight.
Specifically, the top setting internal spline of the leading portion axis 4 connects, to realize that large torque inputs.
Specifically, the centring hole 7, internal spline 6 are set as engraved structure, can reduce weight.
As shown in Figure 1, structure of the invention includes rear axle 1, crank 2 and crank throw 3；Input area includes: leading portion axis 4, moves
Sealing surface 5, internal spline 6 and centring hole 7, crankshaft are made of 2Cr13, realize corrosion-resistant, wear-resistant property；Glow discharge nitriding guarantees
The hardness of crank throw 3 and dynamic sealing face 5, further increases antiwear characteristic；Internal spline 6 and centring hole 7 are engraved structure, can
Mitigate weight.Crankshaft can be directly made up of machining using integrated fabrication design；Crankshaft external diameter is small, light-weight, meets
Space flight minimizes use demand；2Cr13 production, it is corrosion-resistant, it is wear-resistant；The duplex bearing supported design of front end axis 4 and rear axle 1,
Reduce bounce；Crank throw 3 is handled using glow discharge nitriding, improves wearability；Milled processed and glow discharge nitriding are passed through in dynamic sealing face 5,
Not only wear-resisting, but also there is excellent leakproofness；Front end axis 4 is designed as internal spline, meets large torque input demand；4 center of front end axis
Design has centring hole 7, promotes accuracy of alignment, mitigates weight.
In the specific implementation of preference, preferred the following contents, for example, rest part is equal in addition to internal spline 6 wouldn't be processed
It processes in place；Glow discharge nitriding processing individually is carried out to crank throw 3 and dynamic sealing face 5；Internal spline is processed by gear shapping machine；It is right
Dynamic sealing face 5 is ground, and guarantees sealing surface roughness；It tests to the roughness and glow discharge nitriding of sealing surface 5.
In the description of the present application, it is to be understood that term " on ", "front", "rear", "left", "right", " is erected at "lower"
Directly ", the orientation or positional relationship of the instructions such as "horizontal", "top", "bottom", "inner", "outside" is orientation based on the figure or position
Relationship is set, description the application is merely for convenience of and simplifies description, rather than the device or element of indication or suggestion meaning are necessary
It with specific orientation, is constructed and operated in a specific orientation, therefore should not be understood as the limitation to the application.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make a variety of changes or modify within the scope of the claims, this not shadow
Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (10)
1. a kind of space flight dynamic sealing type crankshaft, which is characterized in that including revolution area assembly, input area assembly；
Revolution area assembly is closely connect with input area assembly, is processed integrally formed.
2. space flight according to claim 1 dynamic sealing type crankshaft, which is characterized in that the revolution area assembly, input area
Component is made of 2Cr13.
3. space flight according to claim 1 dynamic sealing type crankshaft, which is characterized in that the revolution area assembly includes rear end
Axis (1), crank (2) and crank throw (3)；
Crank (2) includes the first crank portion, the second crank portion, and one end of crank throw (3) connects the side of the first crank portion, crank throw
(3) the other end connects the side of the second crank portion；
Rear axle (1) is connected with the other side of the first crank portion；The other side of second crank portion is connect with input area assembly.
4. space flight according to claim 1 dynamic sealing type crankshaft, which is characterized in that the input area assembly includes leading portion
Axis (4), dynamic sealing face (5), internal spline (6) and centring hole (7)；
One end of leading portion axis (4) is connect with revolution area assembly, and the other end of leading portion axis (4) is connect with dynamic sealing face (5), leading portion axis
(4) the other end is inserted into dynamic sealing face (5)；
It in dynamic sealing face (5), is provided with centring hole (7) along the axial direction of leading portion axis (4), the end of centring hole (7) connects internal spline
(6)。
5. space flight according to claim 3 dynamic sealing type crankshaft, which is characterized in that the crank throw (3) is seeped using ion
Nitrogen processing, to improve points hardness and wearability.
6. space flight according to claim 4 dynamic sealing type crankshaft, which is characterized in that the dynamic sealing face (5) is by grinding
Mill processing and glow discharge nitriding processing, to improve hardness and roughness.
7. space flight according to claim 4 dynamic sealing type crankshaft, which is characterized in that the internal spline (6) is using small outer
Gauge structure.
8. space flight according to claim 4 dynamic sealing type crankshaft, which is characterized in that the centring hole (7) is arranged preceding
It holds inside axis 4, centering can be connected, to improve accuracy of alignment.
9. space flight according to claim 4 dynamic sealing type crankshaft, which is characterized in that set at the top of the leading portion axis (4)
Internal spline connection is set, to realize that large torque inputs.
10. space flight according to claim 4 dynamic sealing type crankshaft, which is characterized in that the centring hole (7), internal spline
(6) it is set as engraved structure, can reduce weight.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910314971.6A CN110185700A (en) | 2019-04-18 | 2019-04-18 | Space flight dynamic sealing type crankshaft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910314971.6A CN110185700A (en) | 2019-04-18 | 2019-04-18 | Space flight dynamic sealing type crankshaft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110185700A true CN110185700A (en) | 2019-08-30 |
Family
ID=67714627
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910314971.6A Withdrawn CN110185700A (en) | 2019-04-18 | 2019-04-18 | Space flight dynamic sealing type crankshaft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110185700A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2626943A1 (en) * | 1988-02-04 | 1989-08-11 | Camara Alpha | Crankshaft with a stiffened crank pin |
| CN2557740Y (en) * | 2002-07-24 | 2003-06-25 | 杜述琳 | Crankshaft |
| JP2005155873A (en) * | 2003-11-28 | 2005-06-16 | Honda Motor Co Ltd | Crank shaft for four-cycle engine |
| CN1670389A (en) * | 2004-03-20 | 2005-09-21 | 安德烈亚斯.斯蒂尔两合公司 | Crankshaft |
| US20100107808A1 (en) * | 2008-08-01 | 2010-05-06 | Cummins Inc. | Method for increasing torsional fatigue strength in crankshafts |
| DE102012015445A1 (en) * | 2012-08-03 | 2014-02-06 | Daimler Ag | Rolling bearing-supported shaft comprises shaft body made of first material, comprising bearing points respectively having running surface for rolling bodies, which is applied as layer of thermally sprayed second material on shaft body |
| CN205533740U (en) * | 2016-02-15 | 2016-08-31 | 东风朝阳朝柴动力环保科技有限公司 | Diesel engine's bent axle assembly |
| CN107795635A (en) * | 2016-09-06 | 2018-03-13 | 福特环球技术公司 | Torsion vibration absorber and engine pack |
-
2019
- 2019-04-18 CN CN201910314971.6A patent/CN110185700A/en not_active Withdrawn
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2626943A1 (en) * | 1988-02-04 | 1989-08-11 | Camara Alpha | Crankshaft with a stiffened crank pin |
| CN2557740Y (en) * | 2002-07-24 | 2003-06-25 | 杜述琳 | Crankshaft |
| JP2005155873A (en) * | 2003-11-28 | 2005-06-16 | Honda Motor Co Ltd | Crank shaft for four-cycle engine |
| CN1670389A (en) * | 2004-03-20 | 2005-09-21 | 安德烈亚斯.斯蒂尔两合公司 | Crankshaft |
| US20100107808A1 (en) * | 2008-08-01 | 2010-05-06 | Cummins Inc. | Method for increasing torsional fatigue strength in crankshafts |
| DE102012015445A1 (en) * | 2012-08-03 | 2014-02-06 | Daimler Ag | Rolling bearing-supported shaft comprises shaft body made of first material, comprising bearing points respectively having running surface for rolling bodies, which is applied as layer of thermally sprayed second material on shaft body |
| CN205533740U (en) * | 2016-02-15 | 2016-08-31 | 东风朝阳朝柴动力环保科技有限公司 | Diesel engine's bent axle assembly |
| CN107795635A (en) * | 2016-09-06 | 2018-03-13 | 福特环球技术公司 | Torsion vibration absorber and engine pack |
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| 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 | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20190830 |
|
| WW01 | Invention patent application withdrawn after publication |