CN111301718A - Storage battery pack insulation installation and implementation method for spacecraft - Google Patents
Storage battery pack insulation installation and implementation method for spacecraft Download PDFInfo
- Publication number
- CN111301718A CN111301718A CN202010162891.6A CN202010162891A CN111301718A CN 111301718 A CN111301718 A CN 111301718A CN 202010162891 A CN202010162891 A CN 202010162891A CN 111301718 A CN111301718 A CN 111301718A
- Authority
- CN
- China
- Prior art keywords
- storage battery
- spacecraft
- battery pack
- mounting
- insulation
- 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.)
- Pending
Links
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
-
- 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
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/428—Power distribution and management
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M50/00—Constructional details or processes of manufacture of the non-active parts of electrochemical cells other than fuel cells, e.g. hybrid cells
- H01M50/20—Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/10—Energy storage using batteries
Abstract
The invention provides a storage battery pack insulation installation and implementation method for a spacecraft, which comprises the following steps: the device comprises a bolt, an elastic pad, a flat pad, an insulating sleeve, a storage battery mounting hole, a storage battery mounting pin, an insulating film and a spacecraft instrument board; the storage battery mounting screw penetrates through the storage battery waist-shaped mounting hole to fix the storage battery mounting foot on the spacecraft instrument board, an elastic pad and a flat pad are sequentially arranged between the storage battery mounting screw and the storage battery mounting foot, an insulating film is arranged between the storage battery mounting foot and the spacecraft instrument board, and the storage battery mounting hole is sleeved with an insulating sleeve. The invention has simple assembly and low cost: the whole set of insulation installation method only needs materials and equipment such as an insulation film, an insulation sleeve, a heat conduction material, metallographic abrasive paper, GD414(C) glue, an alcohol cotton ball, a universal meter for insulation test and the like.
Description
Technical Field
The invention relates to the technical field of aerospace systems, in particular to an insulation installation and implementation method of a storage battery pack for a spacecraft.
Background
Each spacecraft is provided with a storage battery pack, the storage battery pack is a 'fatal point' related to the success or failure of the spacecraft in the whole life cycle of ground test, spacecraft launching, on-orbit operation and the like, the storage battery pack has a unique function in the use of the spacecraft, so that the safety of the storage battery pack of the spacecraft is valued by all parties all the time, on the development history of the spacecraft, a plurality of faults of short circuit and failure of the storage battery pack caused by grounding installation occur, and for the ground test spacecraft, the failure of the storage battery pack can cause the scrapping of the storage battery pack or the failure of part of spacecraft equipment; for on-orbit spacecraft, the failure of the storage battery pack finally causes the spacecraft to lose partial functions, the application efficiency is reduced, and even the on-orbit spacecraft fails. On the basis of summarizing and analyzing the failure mode of the conventional spacecraft storage battery pack, in order to improve the safety of the storage battery pack, the storage battery pack is installed in an insulating mode and grounded in a high-resistance mode, so that the safety of the spacecraft storage battery pack is greatly improved by a simple method and low cost, and the possibility of short circuit failure of the storage battery pack to a spacecraft structure is reliably avoided.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide an insulation installation and implementation method of a storage battery pack for a spacecraft.
The invention provides an insulation installation and implementation method of a storage battery pack for a spacecraft, which comprises the following steps: the device comprises a bolt 1, an elastic pad 2, a flat pad 3, an insulating sleeve 4, a storage battery mounting hole 5, a storage battery mounting pin 6, an insulating film 7 and a spacecraft instrument board 8;
the bolt 1 penetrates through the storage battery mounting hole 5 to enable the storage battery mounting pin 6 to be fixed on the spacecraft instrument board 8, the elastic pad 2 and the flat pad 3 are sequentially arranged between the bolt 1 and the storage battery mounting pin 6 in a cushioning mode, the insulating film 7 is arranged between the storage battery mounting pin 6 and the spacecraft instrument board 8 in a cushioning mode, and the insulating sleeve 4 is sleeved on the storage battery mounting hole 5.
Preferably, the materials of the screw 1, the elastic pad 2 and the flat pad 3 are titanium alloy.
Preferably, the insulating sleeve 4 material is a polyimide rod.
Preferably, the material of the insulating film 7 is implemented according to the requirement of a thermal control system, and the material of the insulating film 7 comprises polyimide insulating pressure sensitive adhesive tape or glass fiber reinforced plastic.
Preferably, the insulation resistance between the metal surface of the storage battery mounting pin 6 and the spacecraft instrument panel 8 should not be less than 10M omega.
Preferably, the insulating film 7 is coated with a heat conducting material comprising heat conducting silicone grease or indium foil according to the thermal control system requirements, but must not affect the insulation resistance between the metal surface of the battery mounting feet 6 and the spacecraft instrument panel 8.
A storage battery mounting surface treatment step: checking whether the mounting surface of the storage battery has obvious convex scratches or not, and when the storage battery has the obvious convex scratches, removing the convex scratches by using sand and wiping the surface clean; when no obvious convex scratch exists, the installation surface of the storage battery does not need to be treated;
an insulating film pasting step: adhering the insulating film 7 to the surface of the spacecraft instrument panel 8;
installing an insulating sleeve: cleaning the prepared insulating sleeve 4, coating adhesive, placing the insulating sleeve 4 into the storage battery pack mounting hole 5, and wiping off the redundant adhesive with gauze;
mounting screws: the elastic pad 2 and the flat pad 3 are sleeved on the screw 1 in sequence;
and (3) an insulation performance inspection step: after the storage battery pack is mounted on a spacecraft instrument board 8, the insulation resistance between a storage battery metal structure and the spacecraft instrument board 8 is checked by using a universal meter, wherein the insulation resistance is not less than 10M omega;
the battery mounting surface is a surface to be bonded to an instrument panel.
Preferably, the step of attaching an insulating film includes: and heat conduction materials are uniformly coated on two surfaces of the insulating film 7, and impurities cannot be contained in the heat conduction materials so as to avoid damaging the insulating film and influencing the insulating property.
Compared with the prior art, the invention has the following beneficial effects:
1. the assembly is simple and easy, and is with low costs: the whole set of insulation mounting method only needs materials and equipment such as an insulation film, an insulation sleeve, a heat conduction material, metallographic abrasive paper, GD414 glue, an alcohol cotton ball, a universal meter for insulation test and the like;
2. the reliability is high: the raw materials used for the whole set of insulation installation are common mature products for spaceflight, the used inspection method is a conventional method for spacecrafts, and the problems of insulation performance reduction or invalid test data and the like do not exist;
3. the insulating effect is good, can used repeatedly many times: the insulation mounting method is repeatedly used during the whole spacecraft ground test, and the storage battery pack does not move after being mounted in place during the spacecraft rail running, so that the problems of local insulation performance reduction and the like can be avoided, and the high-standard insulation requirement of the spacecraft can be met.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
fig. 1 is a schematic structural diagram of a method for insulating and mounting a storage battery pack for a spacecraft according to the present invention;
in fig. 1: the device comprises a mounting screw 1, an elastic pad 2, a flat pad 3, an insulating sleeve 4, a storage battery mounting hole 5, a storage battery mounting pin 6, an insulating film 7 and a spacecraft instrument board 8.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
In order to solve the problems of insufficient safety and high danger coefficient of the existing spacecraft storage battery pack, the invention aims to provide an insulated mounting and implementing method of the storage battery pack for the spacecraft.
The invention provides an insulation installation and implementation method of a storage battery pack for a spacecraft, which comprises the following steps: the device comprises a bolt 1, an elastic pad 2, a flat pad 3, an insulating sleeve 4, a storage battery mounting hole 5, a storage battery mounting pin 6, an insulating film 7 and a spacecraft instrument board 8;
the bolt 1 penetrates through the storage battery mounting hole 5 to enable the storage battery mounting pin 6 to be fixed on the spacecraft instrument board 8, the elastic pad 2 and the flat pad 3 are sequentially arranged between the bolt 1 and the storage battery mounting pin 6 in a cushioning mode, the insulating film 7 is arranged between the storage battery mounting pin 6 and the spacecraft instrument board 8 in a cushioning mode, and the insulating sleeve 4 is sleeved on the storage battery mounting hole 5.
Specifically, the screw 1, the elastic pad 2 and the flat pad 3 are made of titanium alloy.
Specifically, the insulating sleeve 4 is made of a polyimide rod and has a thickness of 1mm-2 mm.
Specifically, the insulating film 7 material is implemented according to the requirement of a thermal control system, and the insulating film 7 material comprises polyimide insulating pressure sensitive adhesive tape or glass fiber reinforced plastic. The thickness of the polyimide insulation pressure sensitive adhesive tape is generally 0.05mm-0.1mm, and the thickness of the glass fiber reinforced plastic is generally 0.5mm-2 mm. The surface of the insulating film is coated with heat conducting materials, and the heat conducting materials comprise heat conducting silicone grease, indium foil and the like.
Specifically, the insulation resistance between the metal surface of the storage battery mounting pin 6 and the spacecraft instrument panel 8 should be not less than 10M Ω.
Specifically, the insulating film 7 is coated with heat conducting materials such as heat conducting silicone grease and indium foil according to the requirement of a thermal control system, but the insulating resistance between the metal surface of the storage battery mounting pin 6 and the spacecraft instrument panel 8 is not affected. Impurities cannot be contained in the heat conduction material so as to prevent the insulation film from being damaged and the insulation performance from being influenced.
A storage battery mounting surface treatment step: whether obvious convex scratches exist on the installation surface of the storage battery is checked, when the obvious convex scratches exist, the convex scratches are removed in time by using metallographic abrasive paper, and the surface of the storage battery is wiped clean by using an alcohol cotton ball, so that the convex scratches are prevented from penetrating through the insulating film 7 to influence the insulating effect; when no obvious convex scratch exists, the installation surface of the storage battery does not need to be treated;
an insulating film pasting step: the insulating film 7 is pasted on the surface of the spacecraft instrument board 8 according to the size of the storage battery pack; if the insulating film needs to be spliced, gaps cannot be left at seams and the insulating film cannot be lapped, after splicing, the film is complete and is not damaged, no air bubbles and no impurities exist between the insulating film and a bottom plate, the length and the width of the insulating film 7 are cut to be slightly larger than the size of the installation surface of the storage battery, the size of the general film is cut by 3-5 mm according to the appearance of the installation surface of the storage battery, heat conducting materials are required to be uniformly coated on two surfaces of the insulating film 7 according to the requirements of a thermal control system, and the fact that impurities cannot exist in the heat conducting materials so as to avoid damaging;
installing an insulating sleeve: cleaning the prepared insulating sleeve 4, coating GD414(C) glue, putting the insulating sleeve 4 into the storage battery mounting hole 5, and wiping off the excess GD414(C) glue with gauze;
mounting screws: the elastic pad 2 and the flat pad 3 are sleeved on the screw 1 in sequence; installing the screw 1 by using a torque wrench;
and (3) an insulation performance inspection step: after the storage battery pack is mounted on a spacecraft instrument board 8, the insulation resistance between a storage battery metal structure and the spacecraft instrument board 8 is checked by using a universal meter, wherein the insulation resistance is not less than 10M omega;
the battery mounting surface is a surface to be bonded to an instrument panel.
An insulating film is pasted between the storage battery pack mounting surface and a spacecraft instrument board, the surface of the insulating film is coated with a heat conducting material, the storage battery pack mounting feet are connected with the spacecraft instrument board by using titanium alloy mounting screws, elastic pads, flat pads and insulating sleeves are sequentially arranged between the mounting screws and the storage battery pack mounting feet, and the storage battery pack mounting surface treatment, the insulating film pasting, the insulating sleeve mounting, the screw mounting and the insulating property inspection are implemented according to the implementation method.
As shown in fig. 1, the insulating film 7 effectively isolates the mechanical contact between the storage battery and the spacecraft instrument panel 8, the insulating sleeve 4 effectively isolates the mechanical contact between the storage battery mounting screw 1 and the storage battery mounting pin 6, the storage battery mounting surface processing method, the insulating film 7 attaching method, the insulating sleeve 4 mounting method and the screw 1 mounting method effectively guarantee the insulating property between the storage battery and the spacecraft instrument panel 8, and the insulating property checking method effectively verifies the insulating property between the storage battery and the spacecraft instrument panel 8.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (9)
1. A method for insulating and installing and implementing a storage battery pack for a spacecraft is characterized by comprising the following steps: the device comprises a bolt (1), an elastic pad (2), a flat pad (3), an insulating sleeve (4), a storage battery mounting hole (5), a storage battery mounting pin (6), an insulating film (7) and a spacecraft instrument board (8);
the screw (1) penetrates through the storage battery mounting hole (5) to enable the storage battery mounting foot (6) to be fixed on the spacecraft instrument board (8), the elastic pad (2) and the flat pad (3) are sequentially filled between the screw (1) and the storage battery mounting foot (6), the insulating film (7) is filled between the storage battery mounting foot (6) and the spacecraft instrument board (8), and the insulating sleeve (4) is sleeved on the storage battery mounting hole (5).
2. Method for battery pack insulation mounting and implementation for spacecraft according to claim 1, characterized in that the screw (1), the spring washer (2) and the flat washer (3) are made of titanium alloy.
3. Method for the insulating mounting and implementation of a battery pack for spacecraft according to claim 1, characterized in that the insulating sleeve (4) material is a polyimide rod.
4. The method for mounting and implementing battery pack insulation for spacecraft according to claim 1, wherein the material of the insulating film (7) is implemented according to thermal control system requirements, and the material of the insulating film (7) comprises polyimide insulating pressure sensitive tape or glass fiber reinforced plastic.
5. The method for mounting and implementing battery pack insulation for spacecraft of claim 1, wherein the insulation resistance between the metal surface of the battery pack mounting foot (6) and the spacecraft instrument panel (8) is not less than 10M Ω.
6. The spacecraft battery pack insulation mounting and implementation method according to claim 1, characterized in that the insulation film (7) is coated with a heat conducting material comprising heat conducting silicone grease or indium foil according to thermal control system requirements, but without affecting the insulation resistance between the metal face of the battery pack mounting feet (6) and the spacecraft instrument panel (8);
impurities cannot be contained in the heat conduction material so as to prevent the insulation film from being damaged and the insulation performance from being influenced.
7. The battery pack insulation mounting and implementation method for spacecraft of claim 1, characterized in that the insulation film (7) is pasted on the surface of the spacecraft instrument panel (8).
8. Method for the insulating mounting and implementation of a battery pack for spacecraft according to claim 1, characterized in that the insulating sleeve (4) is first cleaned, the insulating sleeve (4) is cleaned ready, glue is applied, the glue-applied insulating sleeve (4) is inserted into the battery pack mounting hole (5), and excess glue is wiped off.
9. The method for mounting and implementing the insulation of the storage battery pack for the spacecraft as claimed in claim 1, wherein, if the mounting surface of the storage battery pack has obvious convex scratches, the convex scratches are sanded off, and the surface is wiped clean; when there is no significant convex scratch, the battery mounting surface does not need to be treated.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010162891.6A CN111301718A (en) | 2020-03-10 | 2020-03-10 | Storage battery pack insulation installation and implementation method for spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010162891.6A CN111301718A (en) | 2020-03-10 | 2020-03-10 | Storage battery pack insulation installation and implementation method for spacecraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111301718A true CN111301718A (en) | 2020-06-19 |
Family
ID=71155478
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010162891.6A Pending CN111301718A (en) | 2020-03-10 | 2020-03-10 | Storage battery pack insulation installation and implementation method for spacecraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111301718A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111867324A (en) * | 2020-06-30 | 2020-10-30 | 北京卫星制造厂有限公司 | Heat radiation structure suitable for spacecraft high-power device |
| CN113060303A (en) * | 2021-03-18 | 2021-07-02 | 中国人民解放军国防科技大学 | Integrated spacecraft cabin plate containing structural lithium battery |
Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10106519A (en) * | 1996-09-27 | 1998-04-24 | Tec Corp | Battery mounting device |
| JPH10196881A (en) * | 1997-01-16 | 1998-07-31 | Nec Eng Ltd | Heat insulating member |
| JPH11293780A (en) * | 1998-04-13 | 1999-10-26 | Mitsubishi Electric Corp | Joint device for articulated assembly |
| CN201933974U (en) * | 2010-12-14 | 2011-08-17 | 上海嘉成轨道交通安全保障系统有限公司 | Safety door insulation mounting mechanism of rail transit platform |
| CN202333022U (en) * | 2011-11-02 | 2012-07-11 | 浙江天能电池(江苏)有限公司 | Storage battery with internal lead |
| CN103662088A (en) * | 2013-11-26 | 2014-03-26 | 中国空间技术研究院 | Thermal control distribution method for star sensors of GEO (geostationary earth orbit) satellite |
| CN105810867A (en) * | 2016-05-10 | 2016-07-27 | 国防科学技术大学 | Solid-state polymer lithium battery pack and preparation method thereof |
| CN107346877A (en) * | 2016-05-04 | 2017-11-14 | 沈阳铝镁设计研究院有限公司 | A kind of insulation installation structure of potroom cable testing bridge |
| CN206742356U (en) * | 2017-04-21 | 2017-12-12 | 安徽欧鹏巴赫新能源科技有限公司 | A kind of soft copper drains line bracket |
| CN206947430U (en) * | 2017-07-17 | 2018-01-30 | 中盈志合科技有限公司 | A kind of tool structure of metal-back capacitor batteries pole and cover plate |
| CN207298867U (en) * | 2017-08-17 | 2018-05-01 | 西安立明电子科技有限责任公司 | The insulating sleeve and felt pad of a kind of superinsulation |
| CN108054315A (en) * | 2017-12-07 | 2018-05-18 | 上海空间电源研究所 | Space rectangular lithium ion accumulator group |
| CN109398759A (en) * | 2018-09-17 | 2019-03-01 | 上海航天设备制造总厂有限公司 | A kind of driving mechanism is insulated precision control device and its installation method |
| CN110120479A (en) * | 2019-04-17 | 2019-08-13 | 上海空间电源研究所 | A kind of high-pressure sealed insulation lithium-ions battery group structure of aerospace |
| CN209312844U (en) * | 2018-12-27 | 2019-08-27 | 中国电子科技集团公司第十八研究所 | Felt pad is used in the energy storage battery group installation of spacecraft |
-
2020
- 2020-03-10 CN CN202010162891.6A patent/CN111301718A/en active Pending
Patent Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10106519A (en) * | 1996-09-27 | 1998-04-24 | Tec Corp | Battery mounting device |
| JPH10196881A (en) * | 1997-01-16 | 1998-07-31 | Nec Eng Ltd | Heat insulating member |
| JPH11293780A (en) * | 1998-04-13 | 1999-10-26 | Mitsubishi Electric Corp | Joint device for articulated assembly |
| CN201933974U (en) * | 2010-12-14 | 2011-08-17 | 上海嘉成轨道交通安全保障系统有限公司 | Safety door insulation mounting mechanism of rail transit platform |
| CN202333022U (en) * | 2011-11-02 | 2012-07-11 | 浙江天能电池(江苏)有限公司 | Storage battery with internal lead |
| CN103662088A (en) * | 2013-11-26 | 2014-03-26 | 中国空间技术研究院 | Thermal control distribution method for star sensors of GEO (geostationary earth orbit) satellite |
| CN107346877A (en) * | 2016-05-04 | 2017-11-14 | 沈阳铝镁设计研究院有限公司 | A kind of insulation installation structure of potroom cable testing bridge |
| CN105810867A (en) * | 2016-05-10 | 2016-07-27 | 国防科学技术大学 | Solid-state polymer lithium battery pack and preparation method thereof |
| CN206742356U (en) * | 2017-04-21 | 2017-12-12 | 安徽欧鹏巴赫新能源科技有限公司 | A kind of soft copper drains line bracket |
| CN206947430U (en) * | 2017-07-17 | 2018-01-30 | 中盈志合科技有限公司 | A kind of tool structure of metal-back capacitor batteries pole and cover plate |
| CN207298867U (en) * | 2017-08-17 | 2018-05-01 | 西安立明电子科技有限责任公司 | The insulating sleeve and felt pad of a kind of superinsulation |
| CN108054315A (en) * | 2017-12-07 | 2018-05-18 | 上海空间电源研究所 | Space rectangular lithium ion accumulator group |
| CN109398759A (en) * | 2018-09-17 | 2019-03-01 | 上海航天设备制造总厂有限公司 | A kind of driving mechanism is insulated precision control device and its installation method |
| CN209312844U (en) * | 2018-12-27 | 2019-08-27 | 中国电子科技集团公司第十八研究所 | Felt pad is used in the energy storage battery group installation of spacecraft |
| CN110120479A (en) * | 2019-04-17 | 2019-08-13 | 上海空间电源研究所 | A kind of high-pressure sealed insulation lithium-ions battery group structure of aerospace |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111867324A (en) * | 2020-06-30 | 2020-10-30 | 北京卫星制造厂有限公司 | Heat radiation structure suitable for spacecraft high-power device |
| CN111867324B (en) * | 2020-06-30 | 2023-04-14 | 北京卫星制造厂有限公司 | Heat radiation structure suitable for spacecraft high-power device |
| CN113060303A (en) * | 2021-03-18 | 2021-07-02 | 中国人民解放军国防科技大学 | Integrated spacecraft cabin plate containing structural lithium battery |
| CN113060303B (en) * | 2021-03-18 | 2022-07-29 | 中国人民解放军国防科技大学 | Integrated spacecraft cabin plate containing structural lithium battery |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111301718A (en) | Storage battery pack insulation installation and implementation method for spacecraft | |
| US8199506B2 (en) | Solid state data storage assembly | |
| CN110175396B (en) | Bonding structure fracture failure analysis method based on unified stress criterion | |
| CN101263444A (en) | Method and article for mounting a touch screen | |
| JP2008083308A (en) | Liquid crystal display device and manufacturing method thereof | |
| CN103331985A (en) | Electronic device and buffering foam module thereof | |
| CN109669253A (en) | Large caliber reflecting mirror vibration damping flexible support structure and mirror assembly | |
| JP2012141846A (en) | Touch panel | |
| EP0980827A1 (en) | Pressure sensitive adhesive for mounting a deicer and method for mounting thereof | |
| JP2020082735A (en) | Passive anti-icing and/or deicing devices, aircraft anti-icing and/or deicing systems, and methods therefor | |
| JP4031625B2 (en) | Electronic component mounting apparatus and electronic component mounting method | |
| CN108216694A (en) | A kind of more equipment thermal vacuum test facilities | |
| JPH11317173A (en) | Removal method and removal device for anisotropic conductive film | |
| CN112937925A (en) | Thermal control method for aerospace equipment | |
| CN107992226B (en) | ON-CELL product and binding region sealing method thereof | |
| KR960016166B1 (en) | Modulus of elasticity tester apparatus particularly adapted for testing compliant materials | |
| CN109870837B (en) | Display assembly, display, terminal and display disassembling method | |
| JP2006198572A (en) | Removal process of anisotropic electric conductive adhesive | |
| CA1323707C (en) | Ink-on-glass digitizer tablet and method of construction | |
| CN110299898A (en) | A kind of Band-reject crystal filter coil reinforcement means and device | |
| Hart-Smith | An engineer asks: is it really more important that paint stays stuck on the outside of an aircraft than that glue stays stuck on the inside? | |
| JP3115116B2 (en) | Liquid crystal display manufacturing method | |
| CN103729150A (en) | Method for processing Write Hole in memory array | |
| CN219302812U (en) | LCD laminating platform with antistatic property | |
| CN109703043A (en) | Spacecraft Kapton type heating sheet resistance to deformation silicone rubber pad method of attaching |
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 | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200619 |