CN109515761B - Microminiature fuse cutter for spaceflight - Google Patents
Microminiature fuse cutter for spaceflight Download PDFInfo
- Publication number
- CN109515761B CN109515761B CN201811654244.6A CN201811654244A CN109515761B CN 109515761 B CN109515761 B CN 109515761B CN 201811654244 A CN201811654244 A CN 201811654244A CN 109515761 B CN109515761 B CN 109515761B
- Authority
- CN
- China
- Prior art keywords
- hot knife
- hot
- cutter
- wire
- knife holder
- 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.)
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Links
- 238000003825 pressing Methods 0.000 claims abstract description 11
- 238000005192 partition Methods 0.000 claims abstract description 8
- 239000000835 fiber Substances 0.000 claims description 12
- 230000006835 compression Effects 0.000 claims description 9
- 238000007906 compression Methods 0.000 claims description 9
- 239000004698 Polyethylene Substances 0.000 claims description 8
- 238000005520 cutting process Methods 0.000 claims description 8
- -1 polyethylene Polymers 0.000 claims description 8
- 229920000573 polyethylene Polymers 0.000 claims description 8
- 239000004809 Teflon Substances 0.000 claims description 4
- 229920006362 Teflon® Polymers 0.000 claims description 4
- 239000000463 material Substances 0.000 claims description 4
- 229910000838 Al alloy Inorganic materials 0.000 claims description 3
- 239000011152 fibreglass Substances 0.000 claims description 3
- 238000005461 lubrication Methods 0.000 claims description 2
- 230000007246 mechanism Effects 0.000 abstract description 6
- 108091092878 Microsatellite Proteins 0.000 abstract description 4
- 230000006872 improvement Effects 0.000 description 7
- 238000000926 separation method Methods 0.000 description 4
- 239000002360 explosive Substances 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 3
- 230000000977 initiatory effect Effects 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 229910001285 shape-memory alloy Inorganic materials 0.000 description 2
- 229920000271 Kevlar® Polymers 0.000 description 1
- 239000004699 Ultra-high molecular weight polyethylene Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 239000004761 kevlar Substances 0.000 description 1
- 239000000696 magnetic material Substances 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 229920000785 ultra high molecular weight polyethylene Polymers 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
- B64G1/443—Photovoltaic cell arrays
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
- H01Q1/288—Satellite antennas
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Details Of Cutting Devices (AREA)
- Perforating, Stamping-Out Or Severing By Means Other Than Cutting (AREA)
Abstract
The invention provides a microminiature fuse cutter for spaceflight, which comprises a base, an upper cover plate, a first hot knife holder, a second hot knife holder, a resistance wire, a partition plate, an elastic element and a wire pressing terminal, wherein the upper cover plate is arranged on the base; the resistor wire is used as a hot knife and is arranged around the hot knife holder, only the head part of the hot knife holder leaves a space, the rest part of the hot knife holder is processed into a groove, and the resistor wire is filled in the groove; the resistance wire is connected with an external circuit through a wire pressing terminal; each hot knife is powered by different circuits and is mutually backed up; in order to avoid mutual interference between the hot knives, a layer of partition plate is added between the hot knives; in order to drive the hot knife holder, the elastic element is arranged between the base and the hot knife holder, and the fuse cutter has the advantages of small volume, light weight, high reliability and no impact, and can be used for compressing and releasing a solar cell array of a microsatellite or a pico-satellite and also can be used for compressing and releasing mechanisms such as a microsatellite antenna and the like.
Description
Technical Field
The invention relates to the technical field of spacecraft controlled separation devices, in particular to a microminiature fuse cutter for spaceflight.
Background
The cutter used on the spacecraft is an action element of a compression release device and is commonly used in solar wings and antenna compression release devices. The function of the cutter is to sever the screws, ropes, cords, etc. used to lock the mechanisms for a release purpose. The reliability of the cutter directly relates to whether a solar wing or an antenna acts or not, so that the success or failure of the whole spacecraft is affected, and the cutter is generally determined as a key piece of the whole spacecraft, and plays a very important role in the spacecraft. Common cutters are fireers, memory alloy cutters, non-fireers, etc., according to the principle of operation of the cutter.
The defects of the initiating explosive device separation are as follows: (1) heavy weight, common firearms cutter greater than 120g; (2) Keeping and using are required to be in compliance with the initiating explosive device management regulations, and special places are required to be kept and managed; (3) bulky; (4) the separation impact is very large, typically greater than 2000g. Because of the problems, the fire cutter is mainly used for connecting and unlocking large-mass structures of large spacecrafts and is not suitable for small mechanisms.
The main disadvantages of the memory alloy cutter are: (1) heavy weight, common firearms cutter greater than 100g; (2) slightly larger; (3) the separation impact is large, typically greater than 1000g. Due to the problems, the initiating explosive device can be widely used for linking and unlocking of medium-sized space mechanisms.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides a miniature fuse wire cutter for spaceflight, which has the advantages of simple structure, small volume, small weight (20 g), high reliability, no impact and no circuit, and can directly supply power at 3V. The invention is realized by the following technical scheme:
a microminiature fuse cutter for spaceflight comprises a base, an upper cover plate, a first hot knife holder, a second hot knife holder, a resistance wire, a partition plate, an elastic element and a wire pressing terminal; the resistor wire is used as a hot knife and is arranged around the hot knife holder, only the head part of the hot knife holder leaves a space, the rest part of the hot knife holder is processed into a groove, and the resistor wire is filled in the groove; the resistance wire is connected with an external circuit through a wire pressing terminal; each hot knife is powered by different circuits and is mutually backed up; in order to avoid mutual interference between the hot knives, a layer of partition plate is added between the hot knives; to drive the hot knife holder, an elastic element is mounted between the base and the hot knife holder.
As a further development of the invention, the resistance wire is controlled by an external circuit or a control circuit is added to the cutter.
As a further improvement of the present invention, the number of the hot knives is two or more.
As a further improvement of the invention, teflon is used as the material of the separator.
As a further development of the invention, the elastic element is a compression spring.
As a further improvement of the invention, the base is provided with the mounting column, the corresponding position on the upper cover plate is provided with the mounting hole, and the mounting hole is matched with the mounting column on the base and is connected by adopting a screw.
As a further improvement of the present invention, the cutting object of the cutter is high-strength polyethylene fiber.
As a further improvement of the invention, the diameter value of the high-strength polyethylene fiber is 1mm, and the pulling force on the rope is 200N.
As a further improvement of the invention, the length of the resistance wire is about 49mm, and the resistance value is about 0.8Q.
As a further improvement of the invention, the base is made of aluminum alloy 2A12, the hot knife holder and the upper cover plate are made of glass fiber reinforced plastic, and the model number of the wire pressing terminal is OD.LZ1-6
The beneficial effects of the invention are as follows: the fuse cutter has small volume, light weight, high reliability and no impact, and can be used for compressing and releasing a solar cell array of a microsatellite or a pico-satellite and also can be used for compressing and releasing mechanisms such as a microsatellite antenna and the like.
Drawings
FIG. 1 is a three-dimensional block diagram of a fuse cutter of the present invention;
FIG. 2 is an exploded view of the fuse cutter of the present invention;
FIG. 3 is a schematic view of the fuse cutter of the present invention in an extended state;
fig. 4 is a schematic view of the fuse cutter of the present invention in a contracted state.
Detailed Description
The invention is further described with reference to the following description of the drawings and detailed description.
The principle of fuse cutters is to heat a heating device (also called a hot knife) to a certain temperature and then fuse a rope or other fibers. The invention is mainly used for unlocking the mechanism of aerospace, and the cutting object is high-strength polyethylene fiber.
As shown in fig. 1-2, the miniature fuse cutter for spaceflight provided by the invention comprises a base (1), an upper cover plate (2), an upper hot blade holder (3), a lower hot blade holder (4), a resistance wire (5), a partition plate (6), an elastic element (7) and a wire pressing terminal (8).
The resistance wire (5) is arranged around the hot knife seat as the hot knife, the head of the hot knife seat is provided with a space, the rest part of the hot knife seat is processed into a groove, and the resistance wire is filled into the groove, so that the heat of the rest resistance wires except the head in the heating process is conducted away by the hot knife seat, and the problem that the temperature of the resistance wire is too high due to overlong resistance wire is avoided. The resistance wire (5) is connected with an external circuit through a wire pressing terminal (8) and is controlled by the external circuit. Or a control circuit is added to the cutter.
The cutter comprises two hot knives which are powered by different circuits and are mutually backed up. Of course, the number of the hot knives is not limited to two, and may be one layer, three layers, or more than three layers.
Structurally, the upper layer of hot knife and the lower layer of hot knife are mutually independent, a layer of partition plate (6) is added for avoiding mutual interference between the upper layer of hot knife and the lower layer of hot knife, and Teflon is adopted as a material.
In order to drive the hot knife holder, an elastic element (7) (such as a compression spring) can be added between the base (1) of the cutter and the hot knife holder, the force of the elastic element (7) has a certain influence on cutting, and the compression spring selects the maximum compression stroke to push force to about 150N through testing, so that the hot knife action can be reliably ensured.
The base (1) is provided with a mounting column for fixing the upper cover plate (2). The corresponding positions of the upper cover plate (2) are provided with mounting holes which are matched with mounting columns on the base (1), and the upper cover plate is connected by bolts (9, 10).
The invention cuts the object of high-strength polyethylene fiber (or ultra-high molecular weight polyethylene fiber), the rope has the characteristics of high strength and low melting point, the rope is suitable for being used as a cut rope, the diameter recommended value of the high-strength polyethylene fiber is 1mm, and the recommended value of the pulling force on the rope is 200N. The fiber has very high strength, relatively small elongation and creep deformation, and compared with a common Kevlar rope for aerospace, the rope has low cutting temperature and is an ideal cut fiber. The fuse cutter is stuck on the outer side of the structure of the spacecraft during working.
The main body of each cutter is an upper and a lower double-layer resistance wires (hot knives) and a hot knife seat matched with the upper and the lower double-layer resistance wires, a Teflon Long Geban is arranged between the two hot knives for isolating relative movement and providing certain lubrication, and the length of the resistance wires of each hot knife is about 49mm (the resistance value is about 0.8Ω). The length of the resistance wire may be reduced or increased or the diameter of the resistance wire may be modified according to the cutting object.
The selection of the material is also important, wherein the base (1) is made of aluminum alloy 2A12, the hot knife rest and the upper cover plate (2) are made of glass fiber reinforced plastic, and the model OD.LZ1-6 of the wire pressing terminal (8) is formed.
The parameters of the fuse cutter of the invention are as follows:
a) Normal temperature vacuum cutting time: less than or equal to 20s
b) Cutting current: 2.0 to 2.2A
c) The whole weight is as follows: less than or equal to 50g
d) The number of cuts can be repeated: > 20 times
e) Single unlock reliability: > 0.9996
f) Operating temperature: -50-80 DEG C
g) The ground storage life is more than or equal to 2 years
h) And a non-magnetic material is adopted and meets the space environment requirement.
The rope tightens a load, passes through the resistance wire, pulls the resistance wire out of the hot knife holder and the resistance wire into an extension state shown in fig. 3, at the moment, the spring is in a compression state, the temperature of the resistance wire rises after heating, the rope is fused, an object tightened by the rope is loosened, the compressed load is released, and simultaneously the hot knife holder and the resistance wire return to a contraction state shown in fig. 4 under the drive of the compression spring.
The foregoing description is only of the preferred embodiments of the present invention and is not intended to limit the scope of the invention, and all equivalent structures or equivalent processes using the descriptions and drawings of the present invention or directly or indirectly applied to other related technical fields are included in the scope of the invention.
It will be apparent to those skilled in the art that several simple deductions or substitutions may be made without departing from the spirit of the invention, and are to be considered as falling within the scope of the invention.
Claims (6)
1. A microminiature fuse cutter for spaceflight is characterized in that: the cutter comprises a base, an upper cover plate, an upper hot knife holder, a lower hot knife holder, a resistance wire, a partition plate, an elastic element and a wire pressing terminal; the resistor wire is wound around the upper hot knife seat and the lower hot knife seat as hot knives, only the heads of the upper hot knife seat and the lower hot knife seat leave a space, the rest parts are processed into grooves, and the resistor wire is filled into the grooves; the resistance wire is connected with an external circuit through a wire pressing terminal; each hot knife is powered by different circuits and is mutually backed up; in order to avoid mutual interference between the hot knives, a layer of partition plate is added between the upper layer hot knife rest and the lower layer hot knife rest; for the drive upper strata hot blade holder with lower floor's hot blade holder upper cover plate with upper strata hot blade holder and the base with install elastic element between the lower floor's hot blade holder, the resistance wire is controlled by external circuit, perhaps increases control circuit in the cutterbar, the quantity of hot blade is two-layer, the material of baffle adopts the teflon, through the baffle keeps apart relative motion and provides lubrication, elastic element is compression spring.
2. The fuse cutter of claim 1, wherein: the base is provided with a mounting column, a mounting hole is formed in a corresponding position on the upper cover plate and matched with the mounting column on the base, and the mounting column is connected by adopting a screw.
3. The fuse cutter of claim 1, wherein: the cutting object of the cutter is high-strength polyethylene fiber.
4. A fuse cutter as claimed in claim 3, wherein: the diameter value of the high-strength polyethylene fiber is 1mm, and the tensile force on the high-strength polyethylene fiber is 200N.
5. The fuse cutter of claim 1, wherein: the resistance wire is about 49mm long and has a resistance value of about 0.8Ω.
6. The fuse cutter of claim 1, wherein: the base uses aluminum alloy 2A12, the upper layer hot knife holder, the lower layer hot knife holder and the upper cover plate use glass fiber reinforced plastic, and the model OD.LZ1-6 of the line pressing terminal is used.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811654244.6A CN109515761B (en) | 2018-12-29 | 2018-12-29 | Microminiature fuse cutter for spaceflight |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811654244.6A CN109515761B (en) | 2018-12-29 | 2018-12-29 | Microminiature fuse cutter for spaceflight |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109515761A CN109515761A (en) | 2019-03-26 |
| CN109515761B true CN109515761B (en) | 2024-04-02 |
Family
ID=65797494
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811654244.6A Active CN109515761B (en) | 2018-12-29 | 2018-12-29 | Microminiature fuse cutter for spaceflight |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109515761B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111969291B (en) * | 2020-08-18 | 2022-11-22 | 天津航天机电设备研究所 | Satellite antenna pressing and unlocking device and using method |
| CN113401436A (en) * | 2021-07-05 | 2021-09-17 | 邯郸宏大化纤机械有限公司 | Cutting-off control device for full-automatic packaging machine surrounding membrane |
| CN117759679B (en) * | 2023-12-28 | 2024-07-05 | 东莞理工学院 | Vibration isolation and noise reduction system for manned spacecraft control moment gyro |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4540873A (en) * | 1983-03-03 | 1985-09-10 | Fokker B.V. | System for breaking a tensioned connecting element |
| US6133818A (en) * | 1999-08-11 | 2000-10-17 | Space Systems/Loral, Inc. | Redundant fuse wire release device |
| US6439122B1 (en) * | 2000-01-28 | 2002-08-27 | Lockhead Martin Corporation | Separation system for missile payload fairings |
| CN205396581U (en) * | 2016-03-11 | 2016-07-27 | 北京空间飞行器总体设计部 | Microminiature fuse ware |
| CN106005489A (en) * | 2016-06-21 | 2016-10-12 | 上海航天测控通信研究所 | Ultra-light pressing and releasing device |
| CN108357699A (en) * | 2018-02-23 | 2018-08-03 | 哈尔滨工业大学 | A kind of spatial flexible arm end-of-arm tooling box compresses and antiradiation protection mechanism |
| CN209757571U (en) * | 2018-12-29 | 2019-12-10 | 深圳航天东方红海特卫星有限公司 | Microminiature fuse cutter for spaceflight |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2013049588A1 (en) * | 2011-09-29 | 2013-04-04 | The Government Of The United States Of America, As Represented By The Secretary Of The Navy | Tethered spacecraft and separation system for tethered spacecraft |
| US9853353B2 (en) * | 2014-06-24 | 2017-12-26 | Los Alamos National Security, Llc | Space vehicle electromechanical system and helical antenna winding fixture |
-
2018
- 2018-12-29 CN CN201811654244.6A patent/CN109515761B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4540873A (en) * | 1983-03-03 | 1985-09-10 | Fokker B.V. | System for breaking a tensioned connecting element |
| US6133818A (en) * | 1999-08-11 | 2000-10-17 | Space Systems/Loral, Inc. | Redundant fuse wire release device |
| US6439122B1 (en) * | 2000-01-28 | 2002-08-27 | Lockhead Martin Corporation | Separation system for missile payload fairings |
| CN205396581U (en) * | 2016-03-11 | 2016-07-27 | 北京空间飞行器总体设计部 | Microminiature fuse ware |
| CN106005489A (en) * | 2016-06-21 | 2016-10-12 | 上海航天测控通信研究所 | Ultra-light pressing and releasing device |
| CN108357699A (en) * | 2018-02-23 | 2018-08-03 | 哈尔滨工业大学 | A kind of spatial flexible arm end-of-arm tooling box compresses and antiradiation protection mechanism |
| CN209757571U (en) * | 2018-12-29 | 2019-12-10 | 深圳航天东方红海特卫星有限公司 | Microminiature fuse cutter for spaceflight |
Non-Patent Citations (1)
| Title |
|---|
| 微小卫星太阳帆板压紧释放机构的设计;宣明;张道威;谷松;杨林;程龙;;光学精密工程(第04期);447-454 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109515761A (en) | 2019-03-26 |
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Address after: 518000 whole building of satellite building, 61 Gaoxin South Jiudao, Yuehai street, Nanshan District, Shenzhen City, Guangdong Province Patentee after: Shenzhen Aerospace Dongfanghong Satellite Co.,Ltd. Country or region after: China Address before: 518000 whole building of satellite building, 61 Gaoxin South Jiudao, Yuehai street, Nanshan District, Shenzhen City, Guangdong Province Patentee before: AEROSPACE DONGFANGHONG DEVELOPMENT Ltd. Country or region before: China |