CN111017262A - Inflatable reentry deceleration flexible unfolding structure folding and unfolding method - Google Patents
Inflatable reentry deceleration flexible unfolding structure folding and unfolding method Download PDFInfo
- Publication number
- CN111017262A CN111017262A CN201911195118.3A CN201911195118A CN111017262A CN 111017262 A CN111017262 A CN 111017262A CN 201911195118 A CN201911195118 A CN 201911195118A CN 111017262 A CN111017262 A CN 111017262A
- Authority
- CN
- China
- Prior art keywords
- heat
- rope
- wrapping
- inflatable
- proof
- 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 abstract description 32
- 238000004806 packaging method and process Methods 0.000 claims abstract description 38
- 239000004744 fabric Substances 0.000 claims description 41
- 229920000742 Cotton Polymers 0.000 claims description 14
- 238000009958 sewing Methods 0.000 claims description 14
- 230000000149 penetrating effect Effects 0.000 claims description 7
- 239000002775 capsule Substances 0.000 claims description 4
- 238000012856 packing Methods 0.000 claims description 4
- 238000000926 separation method Methods 0.000 claims description 4
- 238000003825 pressing Methods 0.000 claims description 3
- 238000005086 pumping Methods 0.000 claims description 3
- 239000004677 Nylon Substances 0.000 claims description 2
- 229920001778 nylon Polymers 0.000 claims description 2
- 230000006835 compression Effects 0.000 abstract description 3
- 238000007906 compression Methods 0.000 abstract description 3
- 230000007547 defect Effects 0.000 description 2
- 230000002457 bidirectional effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000012858 packaging process Methods 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
Images
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
- 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
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
- B64G1/2221—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state characterised by the manner of deployment
- B64G1/2227—Inflating
-
- 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
- B64G1/62—Systems for re-entry into the earth's atmosphere; Retarding or landing devices
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Air Bags (AREA)
- Packages (AREA)
Abstract
A folding and unfolding method for an inflatable reentry deceleration flexible unfolding structure belongs to the technical field of reentry, return and landing of spacecrafts. The invention relates to a high-efficiency reasonable folding and unfolding method for an inflatable reentry deceleration flexible unfolding structure. The flexible unfolding structure is folded in the carrier during launching and before reentering and decelerating mainly through compression and folding; the connection and fixation with the carrier are simple, and the package unlocking is reliable; when the speed is reduced, the flexible unfolding structure can be unfolded orderly, and the normal work of the flexible unfolding structure is ensured. By adopting the folding and packaging method, the volume of the inflatable reentry deceleration flexible unfolding structure in the spacecraft can be effectively reduced, the connection unlocking form is simplified, the orderly unfolding of the flexible unfolding structure is ensured, and the folding and packaging method has higher application value.
Description
Technical Field
The invention relates to a folding and unfolding method of an inflatable reentry deceleration flexible unfolding structure, and belongs to the technical field of reentry, return and landing of spacecrafts.
Background
The application field of human space activities is extended for improving the means and the capability of reentry and return of the spacecraft. Advanced space reentry deceleration structures must be developed to accommodate new potentials and new technical requirements. The inflatable reentry deceleration flexible unfolding structure is an important light space structure with application prospect.
The inflatable reentry deceleration flexible unfolding structure is wrapped at the periphery of a payload cabin by a foldable high-temperature-resistant flexible braided fabric, is folded and contracted into a small volume during launching, and is driven to expand and unfold by the internal gas pressure of the structure according to the functional requirement after launching and entering the orbit to form a structural form meeting the requirement. The requirements of reentry (or entry), landing and safe landing are effectively realized.
The flexible unfolding structure is characterized in that the folding package can be folded to reduce occupied space during launching, and according to the specific design of the structure, the adopted folding package method can not only consider the space to be fully utilized to ensure that the volume is as small as possible, but also pay attention to the unfolding working performance to ensure.
The inflatable unfolding structures of the traditional flexible parachute and the like mainly limit the folding volume through the parachute bag, carry out one-dimensional one-way folding on the parachute, then compress the folded parachute through a press machine, and finally carry out one-way packaging. When the parachute is unfolded, the parachute is reversely and sequentially pulled out from the parachute bag according to the folding sequence of the parachute, and finally the parachute is inflated and unfolded.
The defects of the traditional folding and unfolding method are as follows: the operation link is increased by separating from the final assembly link; the folding compression ratio is large, and disorder entanglement interference is easy to occur in the folding process; the pressure packing is carried out by using the aid of a press, so that the structure is easy to damage; the unfolding process can only be carried out in one direction; the inflation by ambient gas is not stable enough.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, and the inflatable reentry deceleration flexible unfolding structure is folded and unfolded through an efficient and reasonable folding and packaging method, so that the flexible unfolding structure can be folded and furled in the spacecraft when being launched and before reentry deceleration, the storage space and the launching cost are effectively reduced, and meanwhile, the flexible unfolding structure can be orderly unfolded when being reentered and decelerated, and the normal work of the flexible unfolding structure is ensured.
The technical solution of the invention is as follows: a folding method of an inflatable reentry deceleration flexible unfolding structure comprises the following steps:
connecting a rigid nose cone of the inverted cone-shaped flexible unfolding structure with the head of the spacecraft re-entry capsule, wrapping the heat-proof inflatable structure of the flexible unfolding structure on the leeward side of the rigid nose cone, and connecting and fixing the heat-proof inflatable structure with a pressing strip and a screw;
vacuumizing by a vacuum pump through an air inlet valve on the heat-proof air inflation structure; after the vacuum pumping is finished, closing the air inlet valve;
compressing the heat-proof inflatable structure along the axial direction, and flattening the heat-proof inflatable structure;
dividing the heat-proof inflatable structure into a plurality of blocks along the circumferential direction, and sequentially folding the outer side of each block to the inner side along the circumferential direction;
from one corner of the folded heat-proof inflatable structure, sequentially turning over the heat-proof inflatable structure again along the circumferential direction to enable each corner of the heat-proof inflatable structure to be nearest to the axis;
erecting the heat-proof inflatable structure which is turned over again along the axial direction, and rotationally attaching the heat-proof inflatable structure around the spacecraft reentry module;
wrapping the heat-proof inflatable structure with wrapping cloth on the outer side, and sequentially closing up two rows of buckle loops between the two wrapping cloths in a chain manner from the bottom to the top end of the wrapping cloth;
and packaging the heat-proof inflatable structure to finish the packaging of the folded part.
Further, the packaging comprises the following steps:
manually sewing 3 circles with silk thread, fixing the cutter on the top end of wrapping cloth, wrapping the cutter body with cotton cloth, and tying two plain knots at two ends with two strands of 0.18 × 10mm cotton tapes;
the two sides of the wrapping cloth are furled, 2 euphroes are respectively tied up and down on the outer side of the wrapping cloth for one time, and the euphroes are tightened;
arranging the inflatable rings of the heat-proof inflatable structure, so that the inflatable rings cannot exceed the maximum outer diameter range of the rigid nose cone, and meanwhile, the inflatable rings are uniformly distributed outside the central cylinder;
sequentially closing the buckles at the two sides of the wrapping cloth in a chain manner from the bottom to the top end of the wrapping cloth;
sequentially passing the packaging rope through 6 packaging buckle loops, 2 chain type closed-up top buckle loops and 2 cutter rope-passing holes, then tightening the rope end and tying two flat knots; closing the two ends, and sewing with silk thread;
a double strand of 0.18 multiplied by 10mm cotton tape passes through the stringing hole of the cutter, and the packing rope is tied on the side without a blade; making two flat knots with the head, keeping the length of 10mm, and cutting off the redundant part;
straightening the pull rope of the cutter, and fixing the pull rope by using a cotton belt of 0.51 multiplied by 12 mm;
and sequentially penetrating the packaging rope through the packaging buckle loop on the packaging cloth, the chain type closing-up top buckle loop and the rope penetrating hole of the cutter, finally tightening the packaging rope, tying two flat knots, and sewing a needle to fix the rope head.
Further, the cotton silk thread is a double-strand K9# nylon silk thread.
Further, the cutter is fixed at the top end of the wrapping cloth, specifically, the rope through hole of the cutter is flush with the wrapping buckle loop.
Further, the method for sewing with the silk thread comprises the following steps: 8 needles were sewn manually, the sewing length was 20mm, the end was left 10mm long and the thread ends were sintered.
An inflatable reentry deceleration flexible unfolding structure unfolding method comprises the following steps:
the spacecraft returning capsule provided with the flexible unfolding structure is ejected and separated at a preset height and then enters the atmosphere, and the cutter is started by means of ejection separation force;
the cutter operates to cut off the wrapping rope after delaying, so that the wrapping cloth is loosened from the tight state, the chain type closing-in among the wrapping cloth is sequentially untied, and the package of the folded part is released;
the flexible unfolding structure is inflated through the air inlet valve, the heat-proof inflatable structure is unfolded in sequence in the radial direction according to the reverse folding sequence, the inflatable rings are sequentially supported and formed from inside to outside, and the heat-proof skin is tightened under the action of the inflatable rings to form a conical resistance surface to finish unfolding.
Compared with the prior art, the invention has the advantages that:
1. the folding and unfolding method adopted by the invention can be used for the packaging folding and unfolding working process of the inflatable reentry deceleration flexible unfolding structure.
2. By adopting the folding and packaging method, the volume of the inflatable reentry deceleration flexible unfolding structure in the spacecraft can be effectively reduced, the orderly unfolding of the structure is ensured, and the folding and packaging method has high application value.
3. The folding package is carried out during final assembly, so that the operation links are reduced.
4. Through two-dimensional bidirectional folding, the packaging volume is further compressed, and precious carrying resources are saved;
5. through orderly folding, the damage of the inorganic fabric of the structure is reduced;
6. mechanical pressure is not required to be applied in the folding and packaging process, and parts are not damaged;
7. the operation can be carried out manually, so that the dependence on an umbrella packaging tool is reduced;
8. through the chain type package, the quick separation of the package binding device and the flexible inflatable structure is realized, so that the package binding device can be unfolded more quickly;
9. the inflation is carried out by the self-contained air source, so that the unfolding speed is higher, and the dead time is reduced;
10. the two-dimensional orderly unfolding is realized during unfolding, and entanglement interference can not occur.
Drawings
FIG. 1 is a schematic view of a thermal protective inflatable structure of the present invention;
FIG. 2 is a top view of the inflation ring of the present invention;
FIG. 3 is a schematic view of the axial fold of the present invention;
FIG. 4 is a schematic view of the radial fold of the present invention;
FIG. 5 is a schematic view of the radial refolding of the present invention;
FIG. 6 is a schematic diagram of a flexible deployment structure package according to the present invention.
Detailed Description
The invention is further explained and illustrated in the following figures and detailed description of the specification.
Referring to fig. 1 and 2, the inflatable reentry deceleration flexible unfolding structure comprises a nose cone, an air inlet valve, an inflation ring, a connecting belt, a heat-proof skin, wrapping cloth and a cutter.
In a folded state, the inner side of the inflating ring is connected with the head cone, the inflating ring, the connecting belt and the heat-proof skin are axially compressed, and all the inflating ring and the heat-proof skin are flattened; then, four corners are divided into four parts along the radial direction according to diagonal lines, the four corners are folded in half and folded to the inner side in sequence, and then the folded parts are rotationally attached around the central part of the head cone; and finally, packaging the folded flexible structure by wrapping cloth to maintain the compression state of the flexible structure.
In the unfolding state, the package is firstly removed through a cutter, then the inflation rings are inflated through controlling an air inlet valve, the inflation rings are sequentially supported and formed from small to large outside the nose cone, the relative positions of the inflation rings are fixed through a connecting belt, and the heat-proof skin is tightened under the action of each inflation ring, so that a conical resistance surface is enclosed.
The flexible structure is composed of a plurality of groups of inflation rings, and the inflation rings are communicated with each other to ensure the penetration of gas during inflation. The air charging ring is connected with an external air source through an air inlet valve. The plurality of wrapping cloths are connected and fixed through chains. The whole package of the flexible structure is realized by sequentially penetrating the wrapping ropes through the buckle loops on the wrapping cloth and finally bundling and tightening. The cutter is fixed on the package rope, and when the cutter is unfolded, the cutter cuts off the package rope to realize the removal of the package.
Referring to fig. 3 to 6, a method for folding an inflatable reentry deceleration flexible unfolding structure comprises the following steps:
a. the flexible unfolding structure is placed on the rigid nose cone and is connected and fixed by a pressing strip and a screw.
b. Vacuumizing by using a vacuum pump through an air inlet valve on the flexible unfolding structure; and after the vacuum pumping is finished, closing the air inlet valve.
c. And compressing the flexible unfolding structure along the axial direction, and flattening the inflatable ring and the heat-proof skin.
d. Then, four divisions are carried out along the radial direction according to the diagonal line, and from one point, four corners are folded up and down and folded to the inner side clockwise along the circumferential direction in turn, and the square shape is formed.
e. And turning over the inflating ring and the heat-proof skin again clockwise from the protruding parts of the four corners of the square shape.
f. Finally, the folding part is erected along the axial direction and is rotationally attached around the central part of the nose cone;
g. and tightly wrapping the folded part with wrapping cloth at the outer side, and sequentially closing up the two rows of buckle loops between the two wrapping cloths in a chain manner from the bottom to the top end of the wrapping cloth.
h. And sequentially penetrating the packaging rope through the packaging buckle loop on the packaging cloth, the chain type closing-up top buckle loop and the rope penetrating hole of the cutter, finally tightening the packaging rope, tying two flat knots, and sewing a needle to fix the rope end to finish the packaging of the folded part.
The packaging method comprises the following steps:
manually sewing 3 circles with silk thread, fixing the cutter on the top end of wrapping cloth, wrapping the cutter body with cotton cloth, and tying two plain knots at two ends with two strands of 0.18 × 10mm cotton tapes;
the two sides of the wrapping cloth are furled, 2 euphroes are respectively tied up and down on the outer side of the wrapping cloth for one time, and the euphroes are tightened;
arranging the inflatable rings of the heat-proof inflatable structure, so that the inflatable rings cannot exceed the maximum outer diameter range of the rigid nose cone, and meanwhile, the inflatable rings are uniformly distributed outside the central cylinder;
sequentially closing the buckles at the two sides of the wrapping cloth in a chain manner from the bottom to the top end of the wrapping cloth;
sequentially passing the packaging rope through 6 packaging buckle loops, 2 chain type closed-up top buckle loops and 2 cutter rope-passing holes, then tightening the rope end and tying two flat knots; closing the two ends, and sewing with silk thread;
a double strand of 0.18 multiplied by 10mm cotton tape passes through the groove of the cutting knife and the rope threading hole, and the package rope is tied on the side without the cutting edge; making two flat knots with the head, keeping the length of 10mm, and cutting off the redundant part;
straightening the pull rope of the cutter, and fixing the pull rope by using a 0.51 multiplied by 12 cotton tape;
the packaging rope sequentially passes through the packaging buckle loop, the chain type closed-up top buckle loop and the rope through hole of the cutter on the packaging cloth,
and finally, the packing rope is tightly pulled out, two flat knots are tied tightly, and the rope end is fixed by sewing needles.
An inflatable reentry deceleration flexible unfolding structure unfolding method comprises the following steps:
a. the inflatable reentry deceleration flexible unfolding structure is ejected, separated and reentered at a preset height, and the cutter is started by depending on the ejection separation force.
b. The cutter operates to cut off the wrapping rope after time delay, the wrapping cloth is loosened from the tight state, the chain type closing-up between the wrapping cloth is sequentially untied, and the package of the folding part is released.
c. The flexible unfolding structure is inflated through an air inlet valve, and the folding parts are sequentially unfolded in the radial direction according to the folding sequence.
d. The inflation ring is sequentially supported and formed from inside to outside, and the connecting band fixes the relative position of the inflation ring and the head cone.
e. The heat-proof skin is tightened under the action of each inflation ring to form a conical resistance surface, and the safe deceleration landing working condition is achieved.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (6)
1. A folding method of an inflatable reentry deceleration flexible unfolding structure is characterized by comprising the following steps:
connecting a rigid nose cone of the inverted cone-shaped flexible unfolding structure with the head of the spacecraft re-entry capsule, wrapping the heat-proof inflatable structure of the flexible unfolding structure on the leeward side of the rigid nose cone, and connecting and fixing the heat-proof inflatable structure with a pressing strip and a screw;
vacuumizing by a vacuum pump through an air inlet valve on the heat-proof air inflation structure; after the vacuum pumping is finished, closing the air inlet valve;
compressing the heat-proof inflatable structure along the axial direction, and flattening the heat-proof inflatable structure;
dividing the heat-proof inflatable structure into a plurality of blocks along the circumferential direction, and sequentially folding the outer side of each block to the inner side along the circumferential direction;
from one corner of the folded heat-proof inflatable structure, sequentially turning over the heat-proof inflatable structure again along the circumferential direction to enable each corner of the heat-proof inflatable structure to be nearest to the axis;
erecting the heat-proof inflatable structure which is turned over again along the axial direction, and rotationally attaching the heat-proof inflatable structure around the spacecraft reentry module;
wrapping the heat-proof inflatable structure with wrapping cloth on the outer side, and sequentially closing up two rows of buckle loops between the two wrapping cloths in a chain manner from the bottom to the top end of the wrapping cloth;
and packaging the heat-proof inflatable structure to finish the packaging of the folded part.
2. The method of claim 1, wherein said wrapping comprises the steps of:
manually sewing 3 circles with silk thread, fixing the cutter on the top end of wrapping cloth, wrapping the cutter body with cotton cloth, and tying two plain knots at two ends with two strands of 0.18 × 10mm cotton tapes;
the two sides of the wrapping cloth are furled, 2 euphroes are respectively tied up and down on the outer side of the wrapping cloth for one time, and the euphroes are tightened;
arranging the inflatable rings of the heat-proof inflatable structure, so that the inflatable rings cannot exceed the maximum outer diameter range of the rigid nose cone, and meanwhile, the inflatable rings are uniformly distributed outside the central cylinder;
sequentially closing the buckles at the two sides of the wrapping cloth in a chain manner from the bottom to the top end of the wrapping cloth;
sequentially passing the packaging rope through 6 packaging buckle loops, 2 chain type closed-up top buckle loops and 2 cutter rope-passing holes, then tightening the rope end and tying two flat knots; closing the two ends, and sewing with silk thread;
a double strand of 0.18 multiplied by 10mm cotton tape passes through the stringing hole of the cutter, and the packing rope is tied on the side without a blade; making two flat knots with the head, keeping the length of 10mm, and cutting off the redundant part;
straightening the pull rope of the cutter, and fixing the pull rope by using a cotton belt of 0.51 multiplied by 12 mm;
and sequentially penetrating the packaging rope through the packaging buckle loop on the packaging cloth, the chain type closing-up top buckle loop and the rope penetrating hole of the cutter, finally tightening the packaging rope, tying two flat knots, and sewing a needle to fix the rope head.
3. The method of claim 2, wherein the method further comprises: the cotton silk thread is a double-strand K9# brocade silk thread.
4. The method of claim 2, wherein the method further comprises: the cutter is fixed at the top end of the wrapping cloth, and specifically, the rope through hole of the cutter is flush with the wrapping buckle loop.
5. The method of claim 2, wherein the method further comprises: the method for sewing by the nylon yarn comprises the following steps: 8 needles were sewn manually, the sewing length was 20mm, the end was left 10mm long and the thread ends were sintered.
6. An inflatable reentry deceleration flexible unfolding structure unfolding method is characterized by comprising the following steps:
the spacecraft returning capsule provided with the flexible unfolding structure is ejected and separated at a preset height and then enters the atmosphere, and the cutter is started by means of ejection separation force;
the cutter operates to cut off the wrapping rope after delaying, so that the wrapping cloth is loosened from the tight state, the chain type closing-in among the wrapping cloth is sequentially untied, and the package of the folded part is released;
the flexible unfolding structure is inflated through the air inlet valve, the heat-proof inflatable structure is unfolded in sequence in the radial direction according to the reverse folding sequence, the inflatable rings are sequentially supported and formed from inside to outside, and the heat-proof skin is tightened under the action of the inflatable rings to form a conical resistance surface to finish unfolding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911195118.3A CN111017262B (en) | 2019-11-28 | 2019-11-28 | Inflatable reentry deceleration flexible unfolding structure folding and unfolding method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911195118.3A CN111017262B (en) | 2019-11-28 | 2019-11-28 | Inflatable reentry deceleration flexible unfolding structure folding and unfolding method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111017262A true CN111017262A (en) | 2020-04-17 |
| CN111017262B CN111017262B (en) | 2021-07-13 |
Family
ID=70207041
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911195118.3A Active CN111017262B (en) | 2019-11-28 | 2019-11-28 | Inflatable reentry deceleration flexible unfolding structure folding and unfolding method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111017262B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112591145A (en) * | 2021-01-14 | 2021-04-02 | 哈尔滨工业大学 | Flexible film inflatable cylinder with reinforcing sheath and rectangular parallelepiped containing and folding method thereof |
| CN113280694A (en) * | 2021-04-06 | 2021-08-20 | 北京空天技术研究所 | Integrated air bag speed reduction device for interstage separation of aircraft and design method |
| CN114030649A (en) * | 2021-11-26 | 2022-02-11 | 哈尔滨工业大学 | Inflatable unfolding semi-rigid sealed cabin adopting compressible multilayer sandwich protective layer |
| CN114132480A (en) * | 2021-12-03 | 2022-03-04 | 中国特种飞行器研究所 | Foldable flexible device for three-dimensional nose cone comparison and using method and preparation method thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2001022530A1 (en) * | 1999-09-21 | 2001-03-29 | The Johns Hokpins University | Hybrid inflatable antenna |
| US6264144B1 (en) * | 1999-08-03 | 2001-07-24 | Lockheed Martin Corporation | Material assembly for an inflatable aerodynamic braking device for spacecraft deceleration and the like |
| CN105173121A (en) * | 2015-09-22 | 2015-12-23 | 哈尔滨工业大学 | Double-helix inflatable deployment type spinning-stability reduction aircraft |
| CN106516168A (en) * | 2016-09-23 | 2017-03-22 | 北京空间技术研制试验中心 | Fully-protected flexible unfolding re-entry aeroshell |
| CN109455318A (en) * | 2018-10-11 | 2019-03-12 | 北京空间机电研究所 | A kind of gas-filled unfolded re-entry deceleration system |
| CN110065652A (en) * | 2019-03-29 | 2019-07-30 | 上海卫星工程研究所 | Spacecraft stores the method for folding than folding and inflatable deployment structure with plane |
-
2019
- 2019-11-28 CN CN201911195118.3A patent/CN111017262B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6264144B1 (en) * | 1999-08-03 | 2001-07-24 | Lockheed Martin Corporation | Material assembly for an inflatable aerodynamic braking device for spacecraft deceleration and the like |
| WO2001022530A1 (en) * | 1999-09-21 | 2001-03-29 | The Johns Hokpins University | Hybrid inflatable antenna |
| CN105173121A (en) * | 2015-09-22 | 2015-12-23 | 哈尔滨工业大学 | Double-helix inflatable deployment type spinning-stability reduction aircraft |
| CN106516168A (en) * | 2016-09-23 | 2017-03-22 | 北京空间技术研制试验中心 | Fully-protected flexible unfolding re-entry aeroshell |
| CN109455318A (en) * | 2018-10-11 | 2019-03-12 | 北京空间机电研究所 | A kind of gas-filled unfolded re-entry deceleration system |
| CN110065652A (en) * | 2019-03-29 | 2019-07-30 | 上海卫星工程研究所 | Spacecraft stores the method for folding than folding and inflatable deployment structure with plane |
Non-Patent Citations (1)
| Title |
|---|
| 曹旭等: "充气式减速技术试验器的设计和飞行试验", 《载人航天》 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112591145A (en) * | 2021-01-14 | 2021-04-02 | 哈尔滨工业大学 | Flexible film inflatable cylinder with reinforcing sheath and rectangular parallelepiped containing and folding method thereof |
| CN112591145B (en) * | 2021-01-14 | 2022-06-17 | 哈尔滨工业大学 | Flexible film inflatable cylinder with reinforcing sheath and rectangular parallelepiped containing and folding method thereof |
| CN113280694A (en) * | 2021-04-06 | 2021-08-20 | 北京空天技术研究所 | Integrated air bag speed reduction device for interstage separation of aircraft and design method |
| CN113280694B (en) * | 2021-04-06 | 2022-11-11 | 北京空天技术研究所 | Integrated air bag speed reduction device for interstage separation of aircraft and design method |
| CN114030649A (en) * | 2021-11-26 | 2022-02-11 | 哈尔滨工业大学 | Inflatable unfolding semi-rigid sealed cabin adopting compressible multilayer sandwich protective layer |
| CN114132480A (en) * | 2021-12-03 | 2022-03-04 | 中国特种飞行器研究所 | Foldable flexible device for three-dimensional nose cone comparison and using method and preparation method thereof |
| CN114132480B (en) * | 2021-12-03 | 2023-08-04 | 中国特种飞行器研究所 | Three-dimensional nose cone comparison foldable flexible device, and use method and preparation method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111017262B (en) | 2021-07-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111017262B (en) | Inflatable reentry deceleration flexible unfolding structure folding and unfolding method | |
| US3141640A (en) | Method of deploying flexible wing glider | |
| US10703495B2 (en) | Secondary release arrangement for evacuation slide systems | |
| US8096509B2 (en) | Parachute inlet control system and method | |
| US20200148371A1 (en) | Asymmetric yoke | |
| CN109250123B (en) | Slit type inflatable ram parafoil | |
| US10053221B2 (en) | Multi-staged suspension line length parachutes | |
| CN109250122B (en) | Inflatable ram parafoil for pulling parachute opening | |
| CN107826256B (en) | Method for reducing parachute opening impact of ram parafoil | |
| US3940095A (en) | Parachute assembly | |
| CN213008770U (en) | Air blowing pocket type secondary unfolding parachute | |
| CN110723296A (en) | Method for improving parachute opening reliability of large-scale stamping parafoil | |
| US3450377A (en) | Parachutes | |
| EP3348485B1 (en) | Continuously restrained evacuation system | |
| US2762589A (en) | Parachute pack | |
| US10689123B2 (en) | Parachute inlet control system and method | |
| CN109466776B (en) | Control large tracts of land crowd umbrella structure of opening | |
| CN110723299A (en) | Method for improving parachute opening synchronism of multi-parachute system | |
| CA2422945A1 (en) | Flexible linkage system for environmentally sealed parachutes and other safety devices | |
| US3837604A (en) | Means for controlling the deployment and the development of a parachute canopy | |
| US3386687A (en) | Method of deploying a flexible wing vehicle | |
| CN106628438B (en) | A kind of high density packaging parachute pack and package method | |
| CN112644715B (en) | Open parachute packaging container | |
| CN114194419B (en) | Parachute system suitable for recovering fairing of carrier rocket | |
| CN115716535A (en) | Parachute opening control system |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |