CN112591155A - Evaluation method for inflatable unfolding structure of flexible ball spacecraft - Google Patents
Evaluation method for inflatable unfolding structure of flexible ball spacecraft Download PDFInfo
- Publication number
- CN112591155A CN112591155A CN202011475547.9A CN202011475547A CN112591155A CN 112591155 A CN112591155 A CN 112591155A CN 202011475547 A CN202011475547 A CN 202011475547A CN 112591155 A CN112591155 A CN 112591155A
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- flexible ball
- spacecraft
- unfolding
- inflation
- flexible
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- 238000011156 evaluation Methods 0.000 title claims abstract description 10
- 238000000034 method Methods 0.000 claims abstract description 21
- 238000012544 monitoring process Methods 0.000 claims abstract description 20
- 238000012360 testing method Methods 0.000 claims description 28
- 230000008569 process Effects 0.000 claims description 11
- 239000000725 suspension Substances 0.000 claims description 8
- 229920000271 Kevlar® Polymers 0.000 claims description 5
- 239000004761 kevlar Substances 0.000 claims description 5
- 239000000463 material Substances 0.000 claims description 5
- 239000004677 Nylon Substances 0.000 claims description 4
- 229920001778 nylon Polymers 0.000 claims description 4
- 230000008859 change Effects 0.000 claims description 3
- 238000011161 development Methods 0.000 description 7
- 238000013461 design Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
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- 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
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
- B64G2007/005—Space simulation vacuum chambers
Abstract
The invention provides an evaluation method of an inflatable unfolding structure of a flexible ball spacecraft, which can evaluate the reasonability and reliability of the inflatable unfolding structure of the flexible ball spacecraft. The flexible ball spacecraft inflation and deployment method based on the flexible ball spacecraft monitoring can verify the inflation and deployment functions of the flexible ball spacecraft and further evaluate the inflation and deployment structure of the flexible ball spacecraft.
Description
Technical Field
The invention belongs to the technical field of flexible ball spacecrafts, and relates to a method for evaluating an inflatable unfolding structure of a flexible ball spacecraft.
Background
The flexible ball spacecraft is a flexible ball spacecraft of which an inflatable unfolding structure is spherical after being unfolded. The flexible ball spacecraft has a flexible unfolding structure, the flexible unfolding structure is stored in a satellite cabin in a folding mode through flexible materials, after a satellite enters an orbit, the flexible materials can be released and unfolded, the unfolded structure can be used as a solar cell panel, an antenna and the like of the satellite, the flexible ball spacecraft has the advantages of light weight, small launching volume and the like, and the flexible ball spacecraft is an important development direction of the technical development of the flexible ball spacecraft in the future. With the design and development of various flexible ball spacecrafts, the related test verification technology is also urgently required to be synchronously developed and improved, and at present, no method capable of evaluating the reasonability and reliability of the inflatable unfolding structure of the flexible ball spacecraft exists.
Disclosure of Invention
In view of the above, the invention provides an evaluation method for an inflatable unfolding structure of a flexible ball spacecraft, which can evaluate the rationality and reliability of the inflatable unfolding structure of the flexible ball spacecraft.
In order to achieve the purpose, the technical scheme of the invention is as follows:
the invention discloses a flexible ball spacecraft inflation unfolding structure evaluation method, which comprises the following steps:
step 1, selecting a test that the size and the vacuum degree of an internal space meet the requirements of a vacuum environmentThe equipment is used for developing an inflation and unfolding test of the flexible ball spacecraft; the inner space of the test equipment is of a size capable of accommodating the inflatable and unfolded flexible ball spacecraft; the vacuum degree of the test equipment is less than or equal to 6.65 multiplied by 10-3Pa；
and 3, carrying out an inflation unfolding test, monitoring the inflation unfolding process through video monitoring and air pressure monitoring, and evaluating the inflation unfolding structure of the flexible ball spacecraft according to the monitoring result.
The flexible ball spacecraft is fixed in the test equipment in a hanging mode, and the fixing material is Kevlar or a nylon rope.
Wherein, the suspension mode is four-point suspension.
The flexible ball spacecraft comprises a flexible ball unfolding structure and a spacecraft, wherein the flexible ball unfolding structure before unfolding is a cuboid structure and is in a folding and accommodating state, and after the flexible ball unfolding structure after unfolding is inflated, the flexible ball unfolding structure after unfolding is located on one side of the flexible ball unfolding structure before unfolding.
The video monitoring method comprises the following specific steps: arranging cameras around the flexible ball unfolding structure, and directly observing the unfolding process of the flexible ball spacecraft by a video means.
Wherein, the specific mode of atmospheric pressure monitoring is: and an air pressure sensor is arranged in the flexible ball unfolding structure, the internal pressure change of the sailball in the inflation unfolding process is monitored, and whether the flexible ball unfolding structure works normally or not is judged according to the internal pressure data of the flexible ball spacecraft.
Wherein the test equipment is a vacuum tank.
Advantageous effects
The invention provides an evaluation method for an inflatable unfolding structure of a flexible ball spacecraft, which relates to the test conditions and the mounting and bearing mode of the flexible ball spacecraft and the monitoring of the inflatable unfolding process of the flexible ball, and can verify the inflatable unfolding function of the flexible ball spacecraft so as to evaluate the rationality and the reliability of the inflatable unfolding structure of the flexible ball spacecraft.
Drawings
FIG. 1 is a schematic view of the process of the present invention.
Wherein, 1-test equipment; 2-flexible ball spacecraft; 3-a barometric sensor; 4-Kevlar or nylon rope; 5-a camera; 6-unfolding the flexible ball before unfolding; 7-unfolding the flexible ball to be unfolded.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The invention provides an evaluation method for an inflatable unfolding structure of a flexible ball spacecraft, which can verify the inflatable unfolding function of the flexible ball spacecraft so as to evaluate the reasonability and reliability of the inflatable unfolding structure of the flexible ball spacecraft.
The method for evaluating the inflatable unfolding structure of the flexible ball spacecraft, disclosed by the invention, comprises the following steps of:
step 1, selecting test equipment 1 with the internal space size and the vacuum degree meeting the requirements of a vacuum environment, and carrying out an inflation and expansion test of the flexible ball spacecraft. The size of the inner space of the test equipment 1 is required to accommodate the inflated and unfolded flexible ball spacecraft; the vacuum degree of the test equipment is less than or equal to 6.65 multiplied by 10-3Pa (vacuum environment requirement). A vacuum tank may be used as the test device.
The specific suspension mode is four-point suspension, namely 4 fixed points on the outer side of a cuboid of the flexible ball spacecraft are selected, the fixed points are dragged and suspended in the test equipment through a Kevlar rope, and the other end of the rope is fixed at the corresponding position of the test equipment.
And 3, carrying out an inflation unfolding test, monitoring the inflation unfolding process through video monitoring and air pressure monitoring, and evaluating the inflation unfolding structure of the flexible ball spacecraft according to the monitoring result.
The video monitoring method comprises the following specific steps: arranging a camera 5 around the flexible ball unfolding structure, and directly observing the unfolding process of the flexible ball spacecraft by a video means.
The specific air pressure monitoring mode is as follows: an air pressure sensor 3 is arranged in the flexible ball unfolding structure, the internal pressure change of the sailball in the inflation unfolding process is monitored, and whether the flexible ball unfolding structure works normally or not is judged according to the internal pressure data of the flexible ball spacecraft.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. A flexible ball spacecraft inflation unfolding structure evaluation method is characterized by comprising the following steps:
step 1, selecting test equipment with the internal space size and the vacuum degree meeting the requirements of a vacuum environment, and carrying out an inflation unfolding test of the flexible ball spacecraft; the inner space of the test equipment is of a size capable of accommodating the inflatable and unfolded flexible ball spacecraft; the vacuum degree of the test equipment is less than or equal to 6.65 multiplied by 10-3Pa；
Step 2, fixing the flexible ball spacecraft in test equipment;
and 3, carrying out an inflation unfolding test, monitoring the inflation unfolding process through video monitoring and air pressure monitoring, and evaluating the inflation unfolding structure of the flexible ball spacecraft according to the monitoring result.
2. The method for evaluating the inflatable deployment structure of the flexible ball spacecraft as claimed in claim 1, wherein the flexible ball spacecraft is fixed in the test equipment in a suspension manner, and the fixing material is Kevlar or nylon ropes.
3. The method for evaluating the inflatable deployment structure of a flexball spacecraft of claim 2, wherein the suspension is specifically a four-point suspension.
4. The evaluation method for the inflatable unfolding structure of the flexible ball spacecraft as claimed in claim 1, wherein the flexible ball spacecraft comprises a flexible ball unfolding structure and a spacecraft, wherein the flexible ball unfolding structure before unfolding is a cuboid structure and is in a folded and stored state, and after inflation and unfolding, the unfolded flexible ball unfolding structure is positioned on one side of the flexible ball unfolding structure before unfolding.
5. The assessment method for the inflatable deployment structure of the flexible ball spacecraft as claimed in claim 4, wherein the video monitoring is carried out in a specific manner as follows: arranging cameras around the flexible ball unfolding structure, and directly observing the unfolding process of the flexible ball spacecraft by a video means.
6. The evaluation method for the inflatable deployment structure of the flexible ball spacecraft as claimed in claim 4, wherein the specific manner of air pressure monitoring is as follows: and an air pressure sensor is arranged in the flexible ball unfolding structure, the internal pressure change of the sailball in the inflation unfolding process is monitored, and whether the flexible ball unfolding structure works normally or not is judged according to the internal pressure data of the flexible ball spacecraft.
7. The method for evaluating the inflated deployed structure of a flexible ball spacecraft of claim 1, wherein the test equipment is a vacuum tank.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011475547.9A CN112591155A (en) | 2020-12-15 | 2020-12-15 | Evaluation method for inflatable unfolding structure of flexible ball spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011475547.9A CN112591155A (en) | 2020-12-15 | 2020-12-15 | Evaluation method for inflatable unfolding structure of flexible ball spacecraft |
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| Publication Number | Publication Date |
|---|---|
| CN112591155A true CN112591155A (en) | 2021-04-02 |
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|---|---|---|---|
| CN202011475547.9A Pending CN112591155A (en) | 2020-12-15 | 2020-12-15 | Evaluation method for inflatable unfolding structure of flexible ball spacecraft |
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Application publication date: 20210402 |