CN114801215A - Flexible pressurization system for splicing and assembling of thermal protection of reusable aircraft - Google Patents
Flexible pressurization system for splicing and assembling of thermal protection of reusable aircraft Download PDFInfo
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- CN114801215A CN114801215A CN202210316234.1A CN202210316234A CN114801215A CN 114801215 A CN114801215 A CN 114801215A CN 202210316234 A CN202210316234 A CN 202210316234A CN 114801215 A CN114801215 A CN 114801215A
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- 230000004224 protection Effects 0.000 title claims abstract description 76
- 230000007246 mechanism Effects 0.000 claims abstract description 27
- 230000007704 transition Effects 0.000 claims abstract description 18
- 239000003292 glue Substances 0.000 claims abstract description 8
- 238000000034 method Methods 0.000 claims description 7
- 239000000463 material Substances 0.000 claims description 6
- 230000008859 change Effects 0.000 claims description 5
- 230000008569 process Effects 0.000 claims description 4
- 229920005830 Polyurethane Foam Polymers 0.000 claims description 3
- 229920001971 elastomer Polymers 0.000 claims description 3
- 238000009434 installation Methods 0.000 claims description 3
- 239000011496 polyurethane foam Substances 0.000 claims description 3
- 230000009467 reduction Effects 0.000 claims description 2
- 239000000853 adhesive Substances 0.000 abstract description 11
- 230000001070 adhesive effect Effects 0.000 abstract description 11
- 230000000007 visual effect Effects 0.000 abstract description 5
- 238000004026 adhesive bonding Methods 0.000 description 10
- 210000001503 joint Anatomy 0.000 description 3
- 238000003825 pressing Methods 0.000 description 3
- 238000002679 ablation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000011153 ceramic matrix composite Substances 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 238000011002 quantification Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
- B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
- B29C65/78—Means for handling the parts to be joined, e.g. for making containers or hollow articles, e.g. means for handling sheets, plates, web-like materials, tubular articles, hollow articles or elements to be joined therewith; Means for discharging the joined articles from the joining apparatus
-
- 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
- B64G1/58—Thermal protection, e.g. heat shields
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Health & Medical Sciences (AREA)
- Critical Care (AREA)
- Emergency Medicine (AREA)
- General Health & Medical Sciences (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Adhesives Or Adhesive Processes (AREA)
Abstract
The invention relates to a flexible pressurizing system for assembling a reusable aircraft thermal protection adhesive joint, belonging to the technical field of reusable spaceflight; the system comprises a six-degree-of-freedom robot, a cooperative control system, a motion platform, a flexible pressurization executing mechanism, a transition disc and an air compressor; the transition disc is fixedly arranged on the upper surface of the motion platform; the six-degree-of-freedom robot is fixedly arranged at the top end of the transition disc; the flexible pressurizing execution mechanism is arranged at the top extending end of the six-degree-of-freedom robot; the cooperative control system and the air compressor are fixedly arranged on one side of the upper surface of the motion platform, which is far away from the flexible pressurization executing mechanism; the six-degree-of-freedom robot and the flexible pressurization executing mechanism are subjected to linkage control through a cooperative control system; the invention solves the problems of poor stability, limited pressurizing direction and pressurizing part and the like of the traditional support pressurizing and pasting, can realize rapid and automatic glue joint assembly of thermal protection, improves the assembly stability, and can adapt to quantitative and visual control of the pressurizing of the thermal protection bonding with various curvatures.
Description
Technical Field
The invention belongs to the technical field of reusable spaceflight, and relates to a flexible pressurizing system for hot-protection adhesive assembly of a reusable aircraft.
Background
In the technical field of reusable spaceflight, the heat-proof tile is used as a high-temperature-resistant composite material and is commonly used for the wide application of heat protection on the outer surface of an aircraft, and the gluing, assembling and pressurizing of a heat protection system are key factors influencing the gluing strength and the assembling quality, so that the reusability of the whole aircraft is influenced and determined. . Currently, the heat-proof tile pasting process is completed through pure manual operation of workers. During pasting, the surfaces of the aircraft and the heat-proof tile are glued manually, pasted on the outer surface of the aircraft, and are cured by vacuum negative pressure pressurization, and the assembling clearance, the step difference and the pneumatic appearance of the heat-proof part need to be controlled strictly. However, the reusable aircraft is often complex in shape and structure, a large number of gaps, holes, openings and other features exist between the outer surface skin and the structural member, the air leakage phenomenon exists, a large number of parts of the outer surface of the aircraft cannot be sealed through thermal protection, bonding and curing are achieved through a vacuumizing negative pressure pressurizing mode, and pressurization is achieved through a simple supporting mode by means of a tool. However, since the structural shape of each part of the thermal protection of the aircraft is irregular and unique, the mode cannot cover parts with different curvatures, and the pressurizing pressure cannot be quantitatively controlled.
Disclosure of Invention
The technical problem solved by the invention is as follows: overcome prior art's not enough, provide a used repeatedly aircraft thermal protection and splice assembly flexible pressurization system, solved traditional support pressurization and pasted poor stability, pressurization direction and pressurization position limitation scheduling problem, can realize that the thermal protection is quick, the automatic assembly that splices, improves assembly stability to can adapt to multiple camber thermal protection bonding pressurization ration, visual control.
The technical scheme of the invention is as follows:
a flexible pressurization system for assembling a reusable aircraft through thermal protection glue joint comprises a six-degree-of-freedom robot, a cooperative control system, a motion platform, a flexible pressurization executing mechanism, a transition disc and an air compressor; wherein, the motion platform is horizontally arranged; the transition disc is fixedly arranged on the upper surface of the motion platform; the six-degree-of-freedom robot is fixedly arranged at the top end of the transition disc; the flexible pressurizing execution mechanism is arranged at the top extending end of the six-degree-of-freedom robot; the cooperative control system and the air compressor are fixedly arranged on one side of the upper surface of the motion platform, which is far away from the flexible pressurization executing mechanism; the six-degree-of-freedom robot and the flexible pressurizing execution mechanism are subjected to linkage control through the cooperative control system, and the flexible pressurizing execution mechanism is adjusted to be in contact fit with the outer surface of a heat protection layer of an external aircraft shell in a space pose manner.
At foretell flexible pressurization system of the glueing assembly of reuse aircraft thermal protection, air compressor is the air feeder of flexible pressurization actuating mechanism, realizes according to pressure variation adjustment pressure intensity.
In the flexible pressurizing system for splicing and assembling the thermal protection of the reusable aircraft, the transition disc is of a connecting and counterweight structure, the six-degree-of-freedom robot and the multi-degree-of-freedom motion platform are connected, and meanwhile, the weight and the installation position of the transition disc are located at the mass center position of the system, and the six-degree-of-freedom robot is prevented from overturning through the counterweight.
In the flexible pressurization system assembled by the heat protection adhesive bonding of the reusable aircraft, the flexible pressurization executing mechanism comprises a switching disk, a pressurization air bag, a connecting plate, a rectangular block and a pressure sensor; the adapter plate is in butt joint with the extending end of the six-degree-of-freedom robot; the pressure sensor is arranged at the center of the outer side surface of the adapter plate; the pressure applying air bag is in butt joint with the pressure sensor; the connecting plate is butted with the pressure applying air bag; the rectangular block is arranged on the outer side wall of the connecting plate; the symbols are directed towards the exterior aircraft shell.
In the flexible pressurization system assembled by the heat protection adhesive bonding of the reusable aircraft, the adapter plate is a connection interface of the flexible pressurization actuating mechanism and the six-degree-of-freedom robot; the pressurizing air bag is inflated through the air compressor, so that the pressurizing air bag extrudes the connecting plate and the rectangular block, and the rectangular block pressurizes a thermal protection layer of the outer aircraft shell.
In the flexible pressurization system for the glue joint assembly of the heat protection of the reusable aircraft, the pressure sensor monitors the actual applied pressure and feeds the actual applied pressure back to the cooperative control system, and the air pressure compensation or reduction of the air compressor is adjusted according to the pressure change.
In the above-mentioned flexible pressurization system of gluing assembly of heat protection of a kind of reuse aircraft, the course of operation of the said flexible pressurization system is:
after the shape block is adjusted to be attached to the outer surface of the thermal protection layer, the position and the posture of the six-degree-of-freedom robot are locked and kept still, the pressurizing air bag is inflated through the air compressor, and the pressurizing air bag expands to drive the shape block to apply pressure to the thermal protection layer, so that pressurization is completed.
In the above-mentioned flexible pressurization system of assembly of repeatedly using aircraft thermal protection cementing, the gasbag of exerting pressure is the airtight gasbag of elasticity rubber materials preparation, and the gasbag of exerting pressure possesses the flexibility, realizes adjusting along different directions to exert the same equipartition pneumatic pressure.
In the above-mentioned flexible pressurization system of assembly of repeatedly using aircraft thermal protection cementing, apply pressure gasbag bear not less than 0.10MPa pressure to supply air through the air compressor and keep pressure for no less than 10h duration.
In the flexible pressurization system assembled by the repeatedly-used aircraft thermal protection adhesive joint, the rectangular block is made of closed-cell polyurethane foam material and is attached to the thermal protection layer in shape; the rigidity and hardness of the rectangular block are lower than those of the thermal protection layer, so that the surface of the thermal protection layer is not damaged when pressure is applied; the normal direction of the hook block is consistent with the pressure direction of the pressure applying air bag.
Compared with the prior art, the invention has the beneficial effects that:
(1) the invention adopts a mode that the flexible pressurization actuating mechanism is matched with the air compressor for pressurization, thereby effectively solving the problem that the outer surface of the aircraft shell can not be pressurized in vacuum due to skin leakage;
(2) the invention controls the air input quantity of the air compressor by the cooperative control system, and solves the problems of poor bonding stability, difficult constant pressure maintenance and the like caused by the traditional supporting and pressurizing process;
(3) the flexible pressurization device is simple in structure, and is suitable for flexible pressurization of various curvature thermal protection bonding pressurization quantification and visual control.
Drawings
FIG. 1 is a schematic view of a heat protected adhesive assembled flexible compression system of the present invention;
FIG. 2 is a schematic view of a flexible pressurization actuator of the present invention;
fig. 3 is a schematic view of the assembly of the thermal protective adhesive of the present invention.
Detailed Description
The invention is further illustrated by the following examples.
The invention provides a flexible pressurizing system for repeatedly using thermal protection adhesive bonding assembly of an aircraft, solves the problems that the thermal protection of the outer surface of the aircraft cannot realize pressurizing, solves the problems of poor stability, limited pressurizing direction and pressurizing part and the like of the traditional supporting and pressurizing adhesive bonding, and provides a flexible pressurizing method which is suitable for quantitative and visual control of multi-curvature thermal protection adhesive bonding and can be suitable for quantitative and visual control of various curvature thermal protection adhesive bonding.
The flexible pressurizing system assembled by repeatedly using the aircraft thermal protection glue joint is shown in figure 1 and comprises a six-degree-of-freedom robot 1, a cooperative control system 2, a motion platform 3, a flexible pressurizing execution mechanism 4, a transition disc 21 and an air compressor 22; wherein the motion platform 3 is horizontally arranged; the transition disc 21 is fixedly arranged on the upper surface of the moving platform 3; the six-degree-of-freedom robot 1 is fixedly arranged at the top end of the transition disc 21; the flexible pressurizing execution mechanism 4 is arranged at the top extending end of the six-degree-of-freedom robot 1; the cooperative control system 2 and the air compressor 22 are fixedly arranged on one side of the upper surface of the moving platform 3, which is far away from the flexible pressurization executing mechanism 4; the six-degree-of-freedom robot 1 and the flexible pressurizing executing mechanism 4 are subjected to linkage control through the cooperative control system 2, and the flexible pressurizing executing mechanism 4 is adjusted to be in contact fit with the outer surface of a thermal protection layer 6 of an external aircraft shell 5 in a space pose manner.
The air compressor 22 is an air supply device of the flexible pressurization executing mechanism 4, and adjusts the magnitude of the pressurization force according to the pressure change. The transition disc 21 is a connecting and counterweight structure, and when the six-degree-of-freedom robot 1 and the multi-degree-of-freedom motion platform 3 are connected, the weight and the installation position of the transition disc 21 are located at the mass center position of the system, and the six-degree-of-freedom robot 1 is prevented from overturning through counterweight.
As shown in fig. 2, the flexible pressurizing actuator 4 comprises an adapter plate 9, a pressurizing air bag 10, a connecting plate 11, a hook-shaped block 12 and a pressure sensor 13; wherein, the adapter plate 9 is butted with the extending end of the six-degree-of-freedom robot 1; the pressure sensor 13 is arranged at the center of the outer side surface of the adapter plate 9; the pressurizing air bag 10 is in butt joint with the pressure sensor 13; the connecting plate 11 is butted with the pressurizing air bag 10; the rectangular block 12 is installed at the outer side wall of the connection plate 11; the hook-shaped blocks 12 are directed towards the outer aircraft shell 5.
The adapter plate 9 is a connection interface of the flexible pressurizing actuator 4 and the six-degree-of-freedom robot 1; the pressurizing bladder 10 is inflated by the air compressor 22, so that the pressurizing bladder 10 compresses the connecting plate 11 and the shaped blocks 12, and the shaped blocks 12 pressurize the thermal protection layer 6 of the outer aircraft shell 5.
The pressure sensor 13 monitors the actual applied pressure and feeds the actual applied pressure back to the cooperative control system 2, and the air pressure of the air compressor 22 is adjusted to compensate or reduce according to the pressure change.
The working process of the flexible pressurization system is as follows:
after the shape block 12 is adjusted to be attached to the outer surface of the thermal protection layer 6, the six-degree-of-freedom robot 1 is locked and kept still in position and posture, the pressurizing air bag 10 is inflated through the air compressor 22, the pressurizing air bag 10 expands to drive the shape block 12 to apply pressure to the thermal protection layer 6, and pressurization is completed.
The pressing air bag 10 is a closed air bag made of elastic rubber materials, and the pressing air bag 10 has flexibility, realizes adjustment along different directions, and applies the same uniformly distributed pneumatic pressure. The pressurizing air bag 10 bears a pressure of not less than 0.10MPa, and air is supplied by the air compressor 22 to maintain the pressure for not less than 10 hours.
The rectangular block 12 is a closed-cell polyurethane foam material, and is attached to the thermal protection layer 6 in shape; the rigidity and hardness of the rectangular block 12 are lower than those of the thermal protection layer 6, so that the surface of the thermal protection layer 6 is not damaged by applying pressure; the normal direction of the hook block 12 coincides with the pressure direction of the pressurizing bladder 10.
As shown in fig. 3, the thermal protection layer 6 is bonded to the flexible layer 7 by a high temperature adhesive 8, and then bonded to the aircraft shell 5 by the high temperature adhesive 8, and the curing and bonding of the high temperature adhesive 8 are realized by maintaining a certain range of pressure for a certain time.
The thermal protection layer 6 is a high-temperature resistant heat-proof part on the outer surface of the aircraft shell 5, a thermal protection component is formed after one side surface of the flexible layer 7 is bonded through a high-temperature adhesive, and the other side of the flexible layer is coated with the high-temperature adhesive and then is bonded to the outer surface of the aircraft shell to play the roles of heat prevention, ablation and heat insulation, and is usually a ceramic matrix composite. The thermal protection is distributed on the outer surface of the shell in an array manner, each thermal protection is a complex curved surface with different shapes, and a 1mm gap exists between every two adjacent thermal protections.
When the thermal protection layer 6 is bonded, 0.05 MPa-0.10 MPa of pressure needs to be applied to the outer surface of the part, the pressure needs to be maintained for no less than 6 hours, an air layer between the flexible layer 7 and the outer surface of the aircraft shell 5 is eliminated, the complete curing of the high-temperature adhesive is ensured, and the bonding strength and the bonding quality are controlled.
A method of pressurizing an assembly of a flexible pressurization system, comprising the steps of:
(1) calibrating the assembly position of the thermal protection part according to the thermal protection position to be assembled, and installing the same-shaped rectangular blocks;
(2) calculating the pressurizing pressure according to the size of the curved surface of the pressurizing heat protection part, and determining the pressurizing direction according to the normal direction of the curved surface;
(3) controlling the moving multi-degree-of-freedom motion platform to move to a position of a thermal protection target to be assembled;
(4) the heat shield assembly is glued to the mounting location,
(5) the pose of the six-degree-of-freedom robot is adjusted, and the molded surface of the conformal block can be attached to the thermal protection shape;
(6) controlling an air compressor to supply air, inflating a pressurizing air bag to apply mechanical pressure, and eliminating air on the outer surface of the thermal protection and aircraft shell;
(7) controlling the air compressor to adjust air supply and compensation according to the pressure and maintaining the pressure;
(8) thermal protection bonding and curing;
(9) and (5) repeating the steps (1) to (8) to finish a thermal protection assembly.
The invention marks the assembling position of a heat protection part according to the heat protection position to be assembled, installs a shaped block with the same shape → calculates the pressurizing pressure according to the size of the curved surface of the pressurizing heat protection part, determines the pressurizing direction according to the normal direction of the curved surface → controls the moving multi-freedom-degree motion platform to move to the target position of the heat protection to be assembled → the heat protection component is glued and connected to the assembling position → adjusts the pose of the six-freedom-degree robot, ensures that the molded surface of the shaped block can be jointed with the heat protection appearance → controls the air supply of an air compressor, inflates a pressurizing air bag to apply mechanical pressure, eliminates the air on the outer surface of the heat protection and an aircraft shell → controls the air compressor to adjust the air supply and the compensation according to the pressure, maintains the pressure → the heat protection glue is cured.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (10)
1. A flexible pressurization system of glued assembly of hot protection of used repeatedly aircraft which characterized in that: the system comprises a six-degree-of-freedom robot (1), a cooperative control system (2), a motion platform (3), a flexible pressurization executing mechanism (4), a transition disc (21) and an air compressor (22); wherein the motion platform (3) is horizontally arranged; the transition disc (21) is fixedly arranged on the upper surface of the moving platform (3); the six-degree-of-freedom robot (1) is fixedly arranged at the top end of the transition disc (21); the flexible pressurizing execution mechanism (4) is arranged at the top extending end of the six-degree-of-freedom robot (1); the cooperative control system (2) and the air compressor (22) are fixedly arranged on one side of the upper surface of the moving platform (3) far away from the flexible pressurization executing mechanism (4); the six-degree-of-freedom robot (1) and the flexible pressurizing execution mechanism (4) are subjected to linkage control through the cooperative control system (2), and the flexible pressurizing execution mechanism (4) is adjusted to be in contact fit with the outer surface of a heat protection layer (6) of an external aircraft shell (5) in a space pose manner.
2. The system of claim 1, wherein the flexible press system comprises: the air compressor (22) is an air supply device of the flexible pressurization executing mechanism (4), and the size of the pressurization force can be adjusted according to the pressure change.
3. The system of claim 1, wherein the flexible press system comprises: the transition disc (21) is of a connecting and counterweight structure, the six-degree-of-freedom robot (1) and the multi-degree-of-freedom motion platform (3) are connected, meanwhile, the weight and the installation position of the transition disc (21) are located at the mass center position of the system, and the six-degree-of-freedom robot (1) is prevented from overturning through counterweight.
4. The system of claim 2, wherein the flexible press system comprises: the flexible pressurizing executing mechanism (4) comprises an adapter plate (9), a pressurizing air bag (10), a connecting plate (11), a hook-shaped block (12) and a pressure sensor (13); wherein, the adapter plate (9) is butted with the extending end of the six-freedom-degree robot (1); the pressure sensor (13) is arranged at the center of the outer side surface of the adapter plate (9); the pressurizing air bag (10) is butted with the pressure sensor (13); the connecting plate (11) is butted with the pressurizing air bag (10); the rectangular block (12) is arranged on the outer side wall of the connecting plate (11); the rectangular block (12) is directed towards the outer aircraft shell (5).
5. The glue assembly flexible pressurization system for the hot protection of reusable aircraft according to claim 4, characterized in that: the adapter plate (9) is a connection interface of the flexible pressurization executing mechanism (4) and the six-degree-of-freedom robot (1); the air compressor (22) is used for inflating the pressure applying air bag (10), so that the pressure applying air bag (10) extrudes the connecting plate (11) and the rectangular blocks (12), and the rectangular blocks (12) are pressurized to the thermal protection layer (6) of the outer aircraft shell (5).
6. The glue assembly flexible pressurization system for the hot protection of reusable aircraft according to claim 5, characterized in that: the pressure sensor (13) monitors the actual applied pressure, feeds the actual applied pressure back to the cooperative control system (2), and adjusts the air pressure compensation or reduction of the air compressor (22) according to the pressure change.
7. The glue assembly flexible pressurization system for the hot protection of reusable aircraft according to claim 6, characterized in that: the working process of the flexible pressurization system is as follows:
after the hook block (12) is adjusted to be attached to the outer surface of the thermal protection layer (6), the six-degree-of-freedom robot (1) is locked and kept still in position and posture, the pressurizing air bag (10) is inflated through the air compressor (22), and the pressurizing air bag (10) expands to drive the hook block (12) to apply pressure to the thermal protection layer (6), so that pressurization is completed.
8. The system of claim 7, wherein the flexible press fit assembly comprises: the pressure applying air bag (10) is a closed air bag made of elastic rubber materials, the pressure applying air bag (10) is flexible, adjustment in different directions is achieved, and the same uniformly distributed pneumatic pressure is applied.
9. The system of claim 8, wherein the flexible press fit assembly comprises: the pressure applying air bag (10) bears pressure not lower than 0.10MPa, and air is supplied by the air compressor (22) to maintain the pressure for not less than 10 h.
10. The system of claim 7, wherein the flexible press fit assembly comprises: the rectangular block (12) is a closed-cell polyurethane foam material, and is attached to the thermal protection layer (6) in shape; the rigidity and hardness of the rectangular block (12) are lower than those of the thermal protection layer (6), so that the surface of the thermal protection layer (6) is not damaged when pressure is applied; the normal direction of the hook block (12) is in accordance with the pressure direction of the pressurizing air bag (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210316234.1A CN114801215A (en) | 2022-03-28 | 2022-03-28 | Flexible pressurization system for splicing and assembling of thermal protection of reusable aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210316234.1A CN114801215A (en) | 2022-03-28 | 2022-03-28 | Flexible pressurization system for splicing and assembling of thermal protection of reusable aircraft |
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| CN202210316234.1A Pending CN114801215A (en) | 2022-03-28 | 2022-03-28 | Flexible pressurization system for splicing and assembling of thermal protection of reusable aircraft |
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2022
- 2022-03-28 CN CN202210316234.1A patent/CN114801215A/en active Pending
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102431185A (en) * | 2011-09-20 | 2012-05-02 | 南京航空航天大学 | Curved surface self-adaptive pressure shoe and controlling method thereof |
| CN103878666A (en) * | 2014-03-28 | 2014-06-25 | 中国科学院自动化研究所 | Free-form surface robot polishing system |
| US20190039334A1 (en) * | 2017-08-02 | 2019-02-07 | The Boeing Company | Controlling application of forces to different portions of object surface using flexible wall |
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