CN110450986A - Foldable inflating device and its application method suitable for spacecraft - Google Patents
Foldable inflating device and its application method suitable for spacecraft Download PDFInfo
- Publication number
- CN110450986A CN110450986A CN201910749254.6A CN201910749254A CN110450986A CN 110450986 A CN110450986 A CN 110450986A CN 201910749254 A CN201910749254 A CN 201910749254A CN 110450986 A CN110450986 A CN 110450986A
- Authority
- CN
- China
- Prior art keywords
- foldable inflating
- spacecraft
- foldable
- cover
- support frame
- 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.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims description 17
- 230000009477 glass transition Effects 0.000 claims description 12
- 239000000463 material Substances 0.000 claims description 9
- 229920001187 thermosetting polymer Polymers 0.000 claims description 7
- 238000013007 heat curing Methods 0.000 abstract description 10
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 description 6
- 230000000694 effects Effects 0.000 description 3
- 238000001816 cooling Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000010408 film Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
- 239000010409 thin film Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/52—Protection, safety or emergency devices; Survival aids
Abstract
The present invention provides a kind of foldable inflating devices suitable for spacecraft, including foldable inflating cover and foldable inflating cover support frame, the foldable inflating cover support mounting ring is located at foldable inflating cover periphery, the foldable inflating cover can be supported, the foldable inflating cover is cylindric inflatable cover, the foldable inflating cover is adapted the foldable inflating cover with spacecraft and the foldable inflating cover support frame matches, and can be located in the outer surface of spacecraft.The application of folding helical design and heat cure inflated supporting pipe of the invention can realize the medium-and-large-sized cylinder of spacecraft such as: the high storage of hood is collapsed than folding, and expansion rear pillar face has high rigidity, high conformal ability；The high rigidity of heat cure inflated supporting pipe does not need the holding of the pressure difference in pipe, and without the fixed gathering of external force, folding convenient, gathering is small in size, without other structures such as joints, high reliablity is unfolded, and compare the features such as conventional hood greatly alleviates weight.
Description
Technical field
The present invention relates to spacecraft structures and mechanism, are related to a kind of foldable inflating device suitable for spacecraft, specifically relate to
And a kind of spacecraft is stored with high rigidity cylinder hood height than folding and inflating expanded device and its application method.
Background technique
With the development of spacecraft technology, large-scale cylinder such as: hood is increasingly extensive in spaceborne application, to ruler
The requirement of rigidity is increasingly increased after very little and expansion but conventional tucked way storage is than small, and unfolding mechanism weight is big, and joint mostly can
It is reduced by property, therefore is not suitable for applying on following spacecraft.
Application No. is the Chinese invention patent of CN201710571616.8, to disclose a kind of deployable large-scale inflation in space thin
Film shading cover structure, the hood pedestal including being fixed in space camera pedestal, and along the gathering cylinder of hood pedestal distribution, In
It collapses and is cased with inflation tube framework on cylinder, further include adjustment of the tensioning on inflation tube framework surface for inflation tube framework expansion control
Rope-bar, and be bonded in and constitute the shading film that the rope net of hood is reinforced on the outside of inflation tube framework；It is set on hood pedestal
There is gasing tank that is corresponding with inflation tube framework and being connected to；Wherein, the gasing tank on hood pedestal and gathering cylinder are according to the positive side n shape
The mode of vertex position radially successively inwardly arranged is fixedly connected with hood pedestal.But the structure does not conform to compared with design
Reason, later maintenance are inconvenient.
Above technical problem is more inflating expanded than method for folding and high rigidity to spaceborne large-scale cylinder height storage
Propose demand.For this purpose, from product simplicity and practicability, a kind of present invention spacecraft high rigidity cylinder hood
Height storage is than folding and inflating expanded device and its application method.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide a kind of foldable inflating devices suitable for spacecraft
And its application method.
A kind of foldable inflating device suitable for spacecraft provided according to the present invention, including foldable inflating cover and folding are filled
Gas hood support frame, the foldable inflating cover support mounting ring are located at foldable inflating cover periphery, can be to the foldable inflating cover
It is supported,
The foldable inflating cover and the foldable inflating cover support frame match, and can be located at the appearance in spacecraft
Face.
Further, the foldable inflating cover is adapted with spacecraft, and the foldable inflating cover is cylindric inflatable cover.
Further, the foldable inflating cover support frame is support tube, and the support tube is along the foldable inflating cover
Short transverse is inclined at the periphery of the foldable inflating cover with helix parameter.
Further, the foldable inflating cover is made of flexible shading material.
Further, the foldable inflating cover support frame is made of thermosetting material.
Correspondingly, the invention also discloses a kind of application methods of foldable inflating device suitable for spacecraft, including such as
Lower step:
Step 1, on the ground, foldable inflating cover support frame is heated to glass transition temperature or more, inflation to be folded
When the softening of cover support frame can fold, gathering is folded；
Step 2, after spacecraft is entered the orbit, foldable inflating cover support frame is heated to glass transition temperature or more again,
It is when inflatable cover support frame softening to be folded can roll over exhibition, its is inflating expanded；
Step 3, again that foldable inflating cover support frame is cold after the foldable inflating cover support frame in step 2 is fully deployed
But to below glass transition temperature.
Further, in the step 1, the folding of foldable inflating cover support frame is collapsed along helix parameter rotary folding
It collapses.
Further, height h and folding in the step 1, after foldable inflating cover support frame folds gathering, after collapsing
The diameter of inflatable cover support frame, helix parameter are related.
Further, the foldable inflating cover support frame is support tube, and the support tube is along the foldable inflating cover
Short transverse is inclined at the periphery of the foldable inflating cover with helix parameter.
Further, the foldable inflating cover support frame is made of thermosetting material.
Compared with prior art, the present invention have it is following the utility model has the advantages that
(1) the foldable inflating device proposed by the present invention suitable for spacecraft, by simply folding spiral in the device
Line design and the application of heat cure inflated supporting pipe can realize the medium-and-large-sized cylinder of spacecraft such as: the high storage ratio of hood
It folds and collapses, expansion rear pillar face has high rigidity, high conformal ability；
(2) the foldable inflating device proposed by the present invention suitable for spacecraft, the high rigidity of heat cure inflated supporting pipe is not
The pressure difference in pipe is needed to keep (expanding in place rear gas can be discharged at any time, and rigidity will not be by gas leakage effect), this device is not necessarily to
External force is fixed to be collapsed, and folding convenient, gathering is small in size, without other structures such as joints, high reliablity is unfolded, and compare routine
Hood greatly alleviates the features such as weight.
(2) application method of the foldable inflating device proposed by the present invention suitable for spacecraft, method is simple, and work can
It leans on, stablize, used without complicated step, that is, foldable gathering or expansion, realization is provide with spacecraft, layman
Also it can operate, it is easy to operate.
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 the gathering structural schematic diagram of the foldable inflating device suitable for spacecraft of the invention；
Fig. 2 is fully deployed structural schematic diagram for the foldable inflating device suitable for spacecraft of the invention.
Wherein, corresponding appended drawing reference in figure are as follows: 1- foldable inflating cover, 2- foldable inflating cover support frame.
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.
Embodiment 1
The embodiment of the invention provides a kind of foldable inflating devices suitable for spacecraft, including foldable inflating cover 1 and folding
Folded inflatable cover support frame 2,2 ring of foldable inflating cover support frame are located at 1 periphery of foldable inflating cover, can be to the folding
Inflatable cover 1 is supported,
The foldable inflating cover 1 and the foldable inflating cover support frame 2 match, and can be located at the appearance in spacecraft
Face.
The foldable inflating cover 1 is adapted with spacecraft, and the foldable inflating cover 1 is cylindric inflatable cover.
The foldable inflating cover support frame 2 be support tube, the support tube along the foldable inflating cover 1 short transverse
The periphery of the foldable inflating cover 1 is inclined at helix parameter.
The foldable inflating cover 1 is made of flexible shading material.
The foldable inflating cover support frame 2 is made of thermosetting material.
Embodiment 2
On the basis of embodiment 1, the present invention also provides a kind of uses of foldable inflating device suitable for spacecraft
Method includes the following steps:
Step 1, on the ground, foldable inflating cover support frame is heated to glass transition temperature or more, inflation to be folded
When the softening of cover support frame can fold, gathering is folded；
Step 2, after spacecraft is entered the orbit, foldable inflating cover support frame is heated to glass transition temperature or more again,
It is when inflatable cover support frame softening to be folded can roll over exhibition, its is inflating expanded；
Step 3, again that foldable inflating cover support frame is cold after the foldable inflating cover support frame in step 2 is fully deployed
But to below glass transition temperature.
In the step 1, the folding of foldable inflating cover support frame is collapsed collapses along helix parameter rotary folding.
Height h and foldable inflating cover branch in the step 1, after foldable inflating cover support frame folds gathering, after collapsing
The diameter of support, helix parameter are related.
The foldable inflating cover support frame be support tube, the support tube along the short transverse of the foldable inflating cover with
Helix parameter is inclined at the periphery of the foldable inflating cover.
The foldable inflating cover support frame is made of thermosetting material.
More specifically, in the device: firstly, being thermally cured inflated supporting pipe on ground is heated to glass transition temperature
More than, keep its softening foldable, and collapse along the helix rotary folding by design, height h and heat cure after gathering
Inflated supporting pipe diameter and helix parameter etc. are related, can effectively be changed by design and collapse envelope size, hot after cooling
There is solidification inflated supporting pipe high rigidity rounding state can be kept as shown in Figure 2；
There is heat cure inflated supporting pipe high rigidity can keep rounding state after cooling, and reaching can collapse without external force
Purpose.
After spacecraft is entered the orbit, when being thermally cured inflated supporting pipe again and being heated to glass transition temperature or more, thermosetting
Change the state that support tube becomes the Low rigidity of telescopic again, and it is inflating expanded to be thermally cured support tube, and process is unfolded such as
Fig. 1 to as shown in Fig. 2, be thermally cured again after being fully deployed inflated supporting pipe be reduced to glass transition temperature hereinafter, this
When, heat cure inflated supporting pipe rigidity with higher, while the rigidity of the hood is greatly improved；Plane has after expansion
There are high rigidity, high conformal ability, and the high rigidity of heat cure inflated supporting pipe does not need the holding of the pressure difference in pipe, that is, gas after being unfolded
Body can be discharged at any time, and rigidity will not be by gas leakage effect.
To sum up, the foldable inflating device proposed by the present invention suitable for spacecraft, by simply folding spiral shell in the device
Spin line design and the application of heat cure inflated supporting pipe can realize the medium-and-large-sized cylinder of spacecraft such as: the high storage of hood
It is collapsed than folding, expansion rear pillar face has high rigidity, high conformal ability, and collapses envelope size；
The high rigidity of heat cure inflated supporting pipe does not need the holding of the pressure difference in pipe, and (expanding in place rear gas can arrange at any time
Out, rigidity is not by gas leakage effect), which collapses it is not necessary that external force is fixed, folding convenient, collapse it is small in size, no joint etc. other
Structure is unfolded high reliablity, and compares the features such as conventional hood greatly alleviates weight.
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 foldable inflating device suitable for spacecraft, which is characterized in that including foldable inflating cover (1) and foldable inflating cover
Support frame (2), foldable inflating cover support frame (2) ring are located at foldable inflating cover (1) periphery, can fill to the folding
Gas hood (1) is supported,
The foldable inflating cover (1) and the foldable inflating cover support frame (2) match, and can be located at the appearance in spacecraft
Face.
2. the foldable inflating device according to claim 1 suitable for spacecraft, which is characterized in that the foldable inflating cover
(1) it is adapted with spacecraft, the foldable inflating cover (1) is cylindric inflatable cover.
3. the foldable inflating device according to claim 1 suitable for spacecraft, which is characterized in that the foldable inflating cover
Support frame (2) is support tube, and the support tube is obliquely installed along the short transverse of the foldable inflating cover (1) with helix parameter
In the periphery of the foldable inflating cover (1).
4. the foldable inflating device according to claim 2 suitable for spacecraft, which is characterized in that the foldable inflating cover
(1) it is made of flexible shading material.
5. the foldable inflating device according to claim 1 suitable for spacecraft, which is characterized in that the foldable inflating cover
Support frame (2) is made of thermosetting material.
6. a kind of application method of the foldable inflating device suitable for spacecraft, which comprises the steps of:
Step 1, on the ground, foldable inflating cover support frame is heated to glass transition temperature or more, inflatable cover branch to be folded
When support softening can fold, gathering is folded；
Step 2, after spacecraft is entered the orbit, foldable inflating cover support frame is heated to glass transition temperature or more again, wait roll over
It is when folded inflatable cover support frame softening can roll over exhibition, its is inflating expanded；
Step 3, after the foldable inflating cover support frame in step 2 is fully deployed, foldable inflating cover support frame is cooled to again
Below glass transition temperature.
7. the application method of the foldable inflating device according to claim 6 suitable for spacecraft, which is characterized in that described
In step 1, the folding of foldable inflating cover support frame is collapsed collapses along helix parameter rotary folding.
8. the application method of the foldable inflating device according to claim 7 suitable for spacecraft, which is characterized in that described
In step 1, after foldable inflating cover support frame folds gathering, diameter, the spiral shell of height h and foldable inflating cover support frame after collapsing
Spin line parameter is related.
9. the application method of the foldable inflating device according to claim 8 suitable for spacecraft, which is characterized in that described
Foldable inflating cover support frame is support tube, and the support tube is tilted along the short transverse of the foldable inflating cover with helix parameter
The periphery of the foldable inflating cover is set.
10. the application method of the foldable inflating device according to claim 9 suitable for spacecraft, which is characterized in that institute
Foldable inflating cover support frame is stated to be made of thermosetting material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910749254.6A CN110450986B (en) | 2019-08-14 | 2019-08-14 | Folding inflation device suitable for spacecraft and use method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910749254.6A CN110450986B (en) | 2019-08-14 | 2019-08-14 | Folding inflation device suitable for spacecraft and use method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110450986A true CN110450986A (en) | 2019-11-15 |
| CN110450986B CN110450986B (en) | 2021-02-19 |
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| CN201910749254.6A Active CN110450986B (en) | 2019-08-14 | 2019-08-14 | Folding inflation device suitable for spacecraft and use method thereof |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112373730A (en) * | 2020-12-09 | 2021-02-19 | 西北工业大学 | Device and method for capturing satellite reverse rope net |
| CN112591155A (en) * | 2020-12-15 | 2021-04-02 | 兰州空间技术物理研究所 | Evaluation method for inflatable unfolding structure of flexible ball spacecraft |
| CN114524112A (en) * | 2022-03-11 | 2022-05-24 | 中国科学院长春光学精密机械与物理研究所 | Spacecraft dust cover and manufacturing method and using method thereof |
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| US20120146880A1 (en) * | 2010-12-08 | 2012-06-14 | Deutsches Zentrum Fuer Luft- Und Raumfahrt E.V | Self-Deploying Helical Antenna |
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| CN112373730A (en) * | 2020-12-09 | 2021-02-19 | 西北工业大学 | Device and method for capturing satellite reverse rope net |
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| CN112591155A (en) * | 2020-12-15 | 2021-04-02 | 兰州空间技术物理研究所 | Evaluation method for inflatable unfolding structure of flexible ball spacecraft |
| CN114524112A (en) * | 2022-03-11 | 2022-05-24 | 中国科学院长春光学精密机械与物理研究所 | Spacecraft dust cover and manufacturing method and using method thereof |
| CN114524112B (en) * | 2022-03-11 | 2024-02-09 | 中国科学院长春光学精密机械与物理研究所 | Spacecraft dust cover and manufacturing method and using method thereof |
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| CN110450986B (en) | 2021-02-19 |
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