CN207000833U - A kind of Varying-thickness big flow metal diaphragm formula tank diaphragm of spacecraft - Google Patents
A kind of Varying-thickness big flow metal diaphragm formula tank diaphragm of spacecraft Download PDFInfo
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- CN207000833U CN207000833U CN201720703336.3U CN201720703336U CN207000833U CN 207000833 U CN207000833 U CN 207000833U CN 201720703336 U CN201720703336 U CN 201720703336U CN 207000833 U CN207000833 U CN 207000833U
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Abstract
The utility model provides a kind of Varying-thickness big flow metal diaphragm formula tank diaphragm of spacecraft；Including transitional taper angle, spherical crown section, arc section, cone shell of column and pre-flanging section, the pre-flanging section is in smoothing junction by transitional taper angle and cone shell of column, and cone shell of column upper end is also connected smoothly with arc section and spherical crown section successively；A diameter of 444mm of tank diaphragm bottom, the thickness t of tank diaphragm changes with the downward height h in the top of spherical crown section, required pressure is less than uniform thickness diaphragm during Varying-thickness diaphragm rollover, and switching process is more stable, i.e. thickness design can reduce the upset pressure difference of diaphragm, both the stability of upset pressure difference can be ensured, big flow job requirement can be met again.On the premise of the utility model can realize effectively upset ensureing diaphragm, meet big flow job requirement, improve its discharge efficiency, and reduce manufacturing cost and experimental cost suitable for promoting the use of.
Description
Technical field
The utility model belongs to flight equipment manufacturing technology field, and in particular to a kind of Varying-thickness big flow of spacecraft
Metal diaphragm formula tank diaphragm.
Background technology
Diaphragm propellant tank be current space system using relatively advanced liquid propellant tank, particularly metal every
Film tank can realize the long-term filling storage of propellant particularly oxidant, adaptable wide, filling storage period length, sealing
Property it is good, barycenter is stable, suppresses liquid fuel rocks, hot combustion gas supercharging, discharge efficiency can be used high and in state of weightlessness almost
The features such as interference-free acceleration influences, it is to solve the key that liquid fuel is filled, accurately controls and stored for a long time in advance, and shows
Work improve the spacecraft life-span, precision and transmitting mobility, therefore be widely used in often become rail, pose adjustment frequently, machine
In the strong spacecraft of dynamic property.
The key technology of metal diaphragm tank is the characteristic of barrier film in itself, metal diaphragm have intensity is high, corrosion resistance is strong,
Good, the lighter quality of permeability resistance, the advantages that simple manufacturing process and multiple deformation process are controllable, it is the master of diaphragm propellant tank
Want diaphragm material.
Metal diaphragm is generally divided into two kinds of aluminum and titanium system at present, the mechanical performance of aluminium membranes at high temperature than relatively low,
The welding of thin-walled aluminium is more difficult, and compared with aluminium membranes, titanium barrier film not only has good inoxidizability and corrosion resistance,
And high-temperature behavior is with the obvious advantage under combustion gas pressurized constraint, thin walled welds are relatively easy to.The deformation of metal diaphragm is by very big
Limitation, particularly metal diaphragm experiment typically can only once deform, it is difficult to repeat test, this causes metal diaphragm tank setting
Meter, calculate, technique and the upper difficulty of experiment and costly.
Utility model content
In order to solve the above technical problems, the utility model provides a kind of Varying-thickness big flow metal diaphragm of spacecraft
Formula tank diaphragm, the Varying-thickness big flow metal diaphragm formula tank diaphragm of the spacecraft can not only improve the efficiency of upset, full
The job requirement of pedal system big flow, and the possibility of failure can be effectively reduced, and manufacturing cost is reduced, it is existing to overcome
Some technical deficiencies.
The utility model is achieved by the following technical programs.
A kind of Varying-thickness big flow metal diaphragm formula tank diaphragm of spacecraft provided by the utility model；Including transition
Cone angle, spherical crown section, arc section, cone shell of column and pre-flanging section, the pre-flanging section is in smoothing junction by transitional taper angle and cone shell of column,
Cone shell of column upper end is also connected smoothly with arc section and spherical crown section successively；A diameter of 444mm of tank diaphragm bottom, tank film
The thickness t of piece changes with the downward height h in the top of spherical crown section, specially works as：
During h=0~45mm, t=1.2mm,
During 45 mm ＜ h≤63 mm, the mm of t=1.15,
During 63 mm ＜ h≤81 mm, the mm of t=1.10,
During 81 mm ＜ h≤99 mm, the mm of t=1.05,
During 99 mm ＜ h≤117 mm, the mm of t=1.00,
During 117 mm ＜ h≤135 mm, the mm of t=0.95,
During 135 mm ＜ h≤153 mm, the mm of t=0.90,
During 153 mm ＜ h≤171 mm, the mm of t=0.85,
During h 171 mm of ＞, the mm of t=0.80.
The transitional taper angle is 3 ° -8 °.
The spherical crown section, arc section and cone shell of column are that inner surface radius is consistent, outer surface Varying-thickness structure.
The beneficial effects of the utility model are：The presence of pre-flanging can obviously reduce the rigidity of diaphragm herein, make diaphragm
First along upset herein rather than in other region local bucklings.Cone shell of column inclination angle can reduce local buckling to integrally-built shadow
Ring.The design of Varying-thickness significantly reduces bias of the diaphragm in the upset later stage, ensure that the barycenter of tank is stable, diaphragm summit
Length travel change is closer to linearly, ensure being emitted in controllable scope for propellant.Varying-thickness diaphragm rollover when institute
The pressure needed is less than uniform thickness diaphragm, and switching process is more stable, i.e., thickness design can reduce the upset pressure difference of diaphragm, both can be with
Ensure the stability of upset pressure difference, big flow job requirement can be met again.The utility model can realize have ensureing diaphragm
On the premise of effect upset, meet big flow job requirement, both increased the volume of tank, improve its discharge efficiency again, and drop
Low manufacturing cost and experimental cost, have fairly obvious advantage, suitable for promoting the use of compared to existing design.
Brief description of the drawings
Fig. 1 is structural representation of the present utility model；
Fig. 2 is the structural representation of specific embodiment；
Fig. 3 is enlarged diagram at transitional taper angle of the present utility model；
In figure：1- transitional taper angles, 2- spherical crown sections, 3- arc sections, 4- cone shell of columns, 5- pre-flanging sections.
Embodiment
Be described further below the technical solution of the utility model, but claimed scope be not limited to it is described.
A kind of Varying-thickness big flow metal diaphragm formula tank diaphragm of spacecraft as illustrated in fig. 1 and 2；Bored including transition
Angle 1, spherical crown section 2, arc section 3, cone shell of column 4 and pre-flanging section 5, the pre-flanging section 5 are flat by transitional taper angle 1 and cone shell of column 4
Slip, cone shell of column 4 upper end are also connected smoothly with arc section 3 and spherical crown section 2 successively；Tank diaphragm bottom it is a diameter of
444mm, the thickness t of tank diaphragm change with the downward height h in the top of spherical crown section 2, specially worked as：
During h=0~45mm, t=1.2mm,
During 45 mm ＜ h≤63 mm, the mm of t=1.15,
During 63 mm ＜ h≤81 mm, the mm of t=1.10,
During 81 mm ＜ h≤99 mm, the mm of t=1.05,
During 99 mm ＜ h≤117 mm, the mm of t=1.00,
During 117 mm ＜ h≤135 mm, the mm of t=0.95,
During 135 mm ＜ h≤153 mm, the mm of t=0.90,
During 153 mm ＜ h≤171 mm, the mm of t=0.85,
During h 171 mm of ＞, the mm of t=0.80.
The transitional taper angle 1 is 3 ° -8 °.
The spherical crown section 2, arc section 3 and cone shell of column 4 are that inner surface radius is consistent, outer surface Varying-thickness structure.
Structure, material, type face parameter, thickness distribution and load mode of tank diaphragm of the present utility model etc. can influence
It overturns performance, and the structure of wherein diaphragm is one of principal element for influenceing upset performance.Metal diaphragm tank is in tank gold
The metallic membrane that design matches with housing type face in category housing, extrudes diaphragm by gases at high pressure when system works, causes film
Piece is deformed according to specific rule, overturn, and propellant is discharged, required fuel and oxidation when providing work for engine
Agent, and realize the management and supply of propellant and oxidant.Such a diaphragm is mainly by pre-flanging 5, cone shell of column 4, arc section 3, ball
The part of section 2 four composition is preced with, and bores shell of column 4 with pre-flanging 5 with transitional taper angle 1, whole metallic membrane is in nearly hemispherical dome structure.
In order to mitigate diaphragm overall weight, and meet the volume requirements of tank, on the premise of smoothly upset is ensured, thus it is right
Whole diaphragm carries out thickness design, and thickness change has certain rule.It is gradually to subtract i.e. from spherical crown section 2 to the cone thickness of shell of column 4
Small, upset failure caused by eccentric phenomena can be mitigated.Arc section 3 of the position in metallic membrane of eccentric upset occurs, therefore
Need to use thickness design at the arc section 3 of diaphragm.Using external waviness configuration diaphragm, its diaphragm structure has sensitivity
The advantages that height, linearity.
The radius of pre-flanging 5 is too small to cause upset stress excessive, and diaphragm structure intensity is possibly can not to be ensured steadily to overturn, and led
Cause the work requirements that can not meet its big flow；Pre-flanging radius is excessive, can reduce the volume of tank, leads to not satisfaction and sets
Meter requires, therefore need to design satisfactory pre-flanging radius.
Varying-thickness diaphragm is less than in the pressure needed for rollover in metal diaphragm formula tank diaphragm of the present utility model waits thick film
Piece, and switching process is more stable, i.e., thickness design can reduce the upset pressure difference of diaphragm, can both ensure to overturn the stabilization of pressure difference
Property, big flow job requirement can be met again.
Claims (3)
- A kind of 1. Varying-thickness big flow metal diaphragm formula tank diaphragm of spacecraft, it is characterised in that：Including transitional taper angle （1）, spherical crown section（2）, arc section（3）, cone shell of column（4）With pre-flanging section（5）, the pre-flanging section（5）Pass through transitional taper angle（1） With boring shell of column（4）Smooth connection, bore shell of column（4）Upper end also successively with arc section（3）With spherical crown section（2）It is connected smoothly；Storage A diameter of 444mm of case diaphragm bottom, the thickness t of tank diaphragm is with spherical crown section（2）The downward height h in top and change, have Body is to work as：During h=0~45mm, t=1.2mm,During 45 mm ＜ h≤63 mm, the mm of t=1.15,During 63 mm ＜ h≤81 mm, the mm of t=1.10,During 81 mm ＜ h≤99 mm, the mm of t=1.05,During 99 mm ＜ h≤117 mm, the mm of t=1.00,During 117 mm ＜ h≤135 mm, the mm of t=0.95,During 135 mm ＜ h≤153 mm, the mm of t=0.90,During 153 mm ＜ h≤171 mm, the mm of t=0.85,During h 171 mm of ＞, the mm of t=0.80.
- 2. the Varying-thickness big flow metal diaphragm formula tank diaphragm of spacecraft as claimed in claim 1, it is characterised in that：Institute State transitional taper angle（1）For 3 ° -8 °.
- 3. the Varying-thickness big flow metal diaphragm formula tank diaphragm of spacecraft as claimed in claim 1 or 2, its feature exist In：The spherical crown section（2）, arc section（3）With cone shell of column（4）For inner surface radius is consistent, outer surface Varying-thickness structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720703336.3U CN207000833U (en) | 2017-06-16 | 2017-06-16 | A kind of Varying-thickness big flow metal diaphragm formula tank diaphragm of spacecraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720703336.3U CN207000833U (en) | 2017-06-16 | 2017-06-16 | A kind of Varying-thickness big flow metal diaphragm formula tank diaphragm of spacecraft |
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| Publication Number | Publication Date |
|---|---|
| CN207000833U true CN207000833U (en) | 2018-02-13 |
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|---|---|---|---|
| CN201720703336.3U Expired - Fee Related CN207000833U (en) | 2017-06-16 | 2017-06-16 | A kind of Varying-thickness big flow metal diaphragm formula tank diaphragm of spacecraft |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108918248A (en) * | 2018-05-15 | 2018-11-30 | 北京空间技术研制试验中心 | Spacecraft propulsion agent Metal diaphragm tank fatigue life reliability calculation method |
| CN109204887A (en) * | 2018-09-06 | 2019-01-15 | 宁波天擎航天科技有限公司 | A kind of aerospace propellant tank |
| CN109573367A (en) * | 2018-11-09 | 2019-04-05 | 湖北三江航天江北机械工程有限公司 | The processing method of metal diaphragm tank and its metal diaphragm |
-
2017
- 2017-06-16 CN CN201720703336.3U patent/CN207000833U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108918248A (en) * | 2018-05-15 | 2018-11-30 | 北京空间技术研制试验中心 | Spacecraft propulsion agent Metal diaphragm tank fatigue life reliability calculation method |
| CN108918248B (en) * | 2018-05-15 | 2020-11-10 | 北京空间技术研制试验中心 | Method for calculating fatigue life reliability of spacecraft propellant metal diaphragm storage box |
| CN109204887A (en) * | 2018-09-06 | 2019-01-15 | 宁波天擎航天科技有限公司 | A kind of aerospace propellant tank |
| CN109573367A (en) * | 2018-11-09 | 2019-04-05 | 湖北三江航天江北机械工程有限公司 | The processing method of metal diaphragm tank and its metal diaphragm |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180213 Termination date: 20210616 |