CN109515761A - A kind of space flight microminiature fuse cutter - Google Patents
A kind of space flight microminiature fuse cutter Download PDFInfo
- Publication number
- CN109515761A CN109515761A CN201811654244.6A CN201811654244A CN109515761A CN 109515761 A CN109515761 A CN 109515761A CN 201811654244 A CN201811654244 A CN 201811654244A CN 109515761 A CN109515761 A CN 109515761A
- Authority
- CN
- China
- Prior art keywords
- hot
- tool apron
- resistance wire
- fuse
- cutter according
- 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
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims abstract description 19
- 238000005192 partition Methods 0.000 claims abstract description 11
- 238000003801 milling Methods 0.000 claims abstract description 4
- 239000000835 fiber Substances 0.000 claims description 11
- 239000004698 Polyethylene Substances 0.000 claims description 6
- -1 polyethylene Polymers 0.000 claims description 6
- 229920000573 polyethylene Polymers 0.000 claims description 6
- 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 2
- 125000000391 vinyl group Chemical group [H]C([*])=C([H])[H] 0.000 claims 1
- 229920002554 vinyl polymer Polymers 0.000 claims 1
- 230000007246 mechanism Effects 0.000 abstract description 6
- 230000006835 compression Effects 0.000 abstract description 5
- 238000007906 compression Methods 0.000 abstract description 5
- 108091092878 Microsatellite Proteins 0.000 abstract description 4
- 230000002452 interceptive effect Effects 0.000 abstract description 3
- 239000010410 layer Substances 0.000 description 11
- 210000004209 hair Anatomy 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 3
- 229910045601 alloy Inorganic materials 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- 230000008602 contraction Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000037452 priming Effects 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 239000004699 Ultra-high molecular weight polyethylene Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000002355 dual-layer Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
- 239000000696 magnetic material Substances 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 238000004321 preservation Methods 0.000 description 1
- 239000010959 steel Substances 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 present invention provides a kind of space flight microminiature fuse cutters, including pedestal, upper cover plate, the first hot tool apron, the second hot tool apron, resistance wire, partition, elastic element and pressure line terminal；Resistance wire is mounted on as hot knife and is wound on around hot tool apron, and only head slot milling, rest part are processed into groove to hot tool apron, and resistance wire is inserted in groove；Resistance wire is connect by pressure line terminal with external circuit；Every hot knife is powered using different circuits, is mutually backups；To avoid interfering with each other between hot knife, increase by one layer of partition between hot knife；To drive hot tool apron, between pedestal and hot tool apron elastic elements fuse cutter of the invention it is small in size, it is light-weight can, it is high by property, without impact, it can be used for the compression and release of the solar battery array of microsatellite or skin Nano satellite, it can also be used to the compression and release of the mechanisms such as microsatellite antenna.
Description
Technical field
The present invention relates to spacecraft controlled detachment engineering device technique fields more particularly to a kind of space flight microminiature fuse to cut
Device.
Background technique
The cutter used on spacecraft is a kind of action element for compressing release device, is commonly used in solar wing, antenna
It compresses in release device.The function of cutter is turned off screw rod, rope, rope etc. for locking these mechanisms, is released with reaching one
The purpose put.Whether the reliability of cutter is directly related to solar wing or antenna and acts, so influence entire spacecraft at
It loses, is generally decided to be the key component of whole star, there is very important effect in spacecraft.According to cutter action principle not
Together, common cutter has firer's cutter, memorial alloy cutter and non-firer's cutter etc..
The shortcomings that firer separates mainly has: (1) weight is big, and common firer's cutter is greater than 120g；(2) taking care of and use needs
Priming system administrative provisions are abided by, with needing special messenger's special show preservation and management；(3) volume is big；(4) separation impact is very big, generally
Greater than 2000g.Since the above problem exists, this firer's cutter is mainly used for the big quality structure connection solution of big spacecraft
Lock is not suitable for small mechanism and uses.
The major defect of memorial alloy cutter is: (1) weight is big, and common firer's cutter is greater than 100g；(2) volume is slightly
Greatly；(3) separation impact is big, generally higher than 1000g.Due to the above problem, this priming system can be widely used for medium space mechanism
Link unlock.
Summary of the invention
In order to solve the problems in the prior art, the present invention provides a kind of space flight microminiature fuse cutter, this hairs
Bright cutter structure is simple, small in size, and weight is small (20g), high reliablity, no impact, and no circuit can directly 3V power supply.This hair
It is bright to be realized especially by following technical solution:
A kind of space flight microminiature fuse cutter, the cutter include pedestal, upper cover plate, the first hot tool apron, second
Hot tool apron, resistance wire, partition, elastic element and pressure line terminal；Resistance wire is mounted on as hot knife and is wound on around hot tool apron, hot knife
Only head slot milling, rest part are processed into groove to seat, and resistance wire is inserted in groove；Resistance wire by pressure line terminal with
External circuit connection；Every hot knife is powered using different circuits, is mutually backups；To avoid interfering with each other between hot knife, in heat
Increase by one layer of partition between knife；To drive hot tool apron, the elastic elements between pedestal and hot tool apron.
As a further improvement of the present invention, the resistance wire is controlled by external circuit, or increase in cutter
Add control circuit.
As a further improvement of the present invention, the quantity of the hot knife is two layers or two layers or more.
As a further improvement of the present invention, the material of the partition uses Teflon.
As a further improvement of the present invention, the elastic element is compressed spring.
As a further improvement of the present invention, there is mounting post on the pedestal, there is mounting hole in corresponding position on upper cover plate,
Mounting post cooperation on pedestal, is attached using 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 present invention, the diameter value of the high-strength polyethylene fiber is 1mm, the pulling force on rope
For 200N.
As a further improvement of the present invention, the resistance wire is about 49mm, and resistance value is about 0.8Q.
As a further improvement of the present invention, the pedestal uses aluminium alloy 2A12, and hot tool apron and upper cover plate use glass
Steel, the model OD.LZ1-6 of pressure line terminal
The beneficial effects of the present invention are: fuse cutter of the invention it is small in size, it is light-weight can, it is high by property, without impact, can
Compression and release for microsatellite or the solar battery array of skin Nano satellite, it can also be used to the pressure of the mechanisms such as microsatellite antenna
Tight and release.
Detailed description of the invention
Fig. 1 is the tomograph of fuse cutter of the invention；
Fig. 2 is the explosive view of fuse cutter of the invention；
Fig. 3 is fuse cutter elongation state schematic diagram of the invention；
Fig. 4 is fuse cutter contraction state schematic diagram of the invention.
Specific embodiment
The present invention is further described for explanation and specific embodiment with reference to the accompanying drawing.
The principle of fuse cutter is all to be heated to certain temperature using heating device (also known as hot knife), and then fuse rope
Or other fibers.Present invention is mainly used for the unlocks of the mechanism of aerospace, and cutting object is high-strength polyethylene fiber.
As shown in Figs. 1-2, space flight microminiature fuse cutter of the invention includes pedestal (1), upper cover plate (2), upper layer
Hot tool apron (3), the hot tool apron of lower layer (4), resistance wire (5), partition (6), elastic element (7), pressure line terminal (8).
Resistance wire (5) is mounted on as hot knife and is wound on around hot tool apron, and only head slot milling, rest part add hot tool apron
Work becomes groove, resistance wire is inserted in groove, in such heating process except a head part, the heat of remaining resistance wire is by hot tool apron
It guides, avoids the too long problem for causing wire temperature excessively high of resistance wire.Resistance wire (5) passes through pressure line terminal (8) and external
Circuit connection is controlled by external circuit.Or increase control circuit in cutter.
Cutter includes two hot knives, and two hot knives are powered using different circuits, are mutually backups.Certainly, the quantity of hot knife
Two are not limited to, can be one layer, three layers or three layers or more.
In structure, the hot knife of upper layer and lower layer is mutually indepedent, to avoid interfering with each other between the hot knife of upper and lower level, increases one layer
Partition (6), material use Teflon.
To drive hot tool apron, elastic element (7) can be increased between the pedestal (1) of cutter and hot tool apron (such as compression bullet
Spring), the power of elastic element (7) is on certain influence is cut with, and after tested, compressed spring selects under maximum compression stroke, and thrust is about
For 150N, it can reliably ensure hot knife movement.
Pedestal has mounting post on (1), is used for fixed cover plate (2).There is mounting hole in corresponding position on upper cover plate (2), and
Mounting post cooperation on pedestal (1), is attached using screw (9,10).
The object of this hair invention cutting is high-strength polyethylene fiber (or being ultra high molecular weight polyethylene fiber), this
Rope has intensity high, and low-melting characteristic is suitable as being cut rope, and the diameter recommendation of high-strength polyethylene fiber is
1mm, the pulling force recommendation on rope are 200N.This kind of fiber has very high intensity and relatively small elongation and compacted
Become, it is preferably by cutting fibre that relative to the common Kev drawstring of space flight, the cutting temperature of the rope is lower.Fuse cutting
Device is pasted on the outside of the structure of spacecraft when working.
The main body of each cutter is Dual-layer resistance wire (hot knife) and its matched hot tool apron, is padded between two hot knives
There is special teflon partition for relative motion to be isolated and provides certain lubrication, the resistance wire of each hot knife is about 49mm, and (resistance value is about
For 0.8 Ω).Resistance wire length can be reduced or increased according to the difference of cutting object or modify the diameter of resistance wire.
The selection of material of the present invention is also critically important, and wherein pedestal (1) uses aluminium alloy 2A12, hot tool apron and upper cover plate (2)
Use glass reinforced plastic, the model OD.LZ1-6 of pressure line terminal (8).
Fuse cutter parameter of the invention are as follows:
A) normal-temperature vacuum clipping time :≤20s
B) cutting current: 2.0~2.2A
C) overall weight :≤50g
D) repeatable cutting times: > 20 times
E) Dan Xiesuo reliability: > 0.9996
F) operating temperature: -50 DEG C~80 DEG C
G) ground storage life >=2 year
H) it uses non-magnetic material and meets space environment requirement.
One load of rope passes through resistance wire, and resistance wire is ined succession hot tool apron pull-out into elongate shown in Fig. 3
State, spring-compressed state, wire temperature raising after heating, fusing rope are released by the object of rope, are pressed at this time
Tight load is released, while hot tool apron and resistance wire return to contraction state as shown in Figure 4 under the drive of compressed spring.
The above description is only a preferred embodiment of the present invention, is not intended to limit the scope of the invention, all utilizations
Equivalent structure or equivalent flow shift made by description of the invention and accompanying drawing content is applied directly or indirectly in other correlations
Technical field, be included within the scope of the present invention.
For those of ordinary skill in the art, without departing from the inventive concept of the premise, if can also make
Simple deduction or replace are done, all shall be regarded as belonging to protection scope of the present invention.
Claims (10)
1. a kind of space flight microminiature fuse cutter, it is characterised in that: the cutter includes pedestal, upper cover plate, the first heat
Tool apron, the second hot tool apron, resistance wire, partition, elastic element and pressure line terminal；Resistance wire is mounted on as hot knife and is wound on hot tool apron
Around, only head slot milling, rest part are processed into groove to hot tool apron, and resistance wire is inserted in groove；Resistance wire passes through
Pressure line terminal is connect with external circuit；Every hot knife is powered using different circuits, is mutually backups；It is mutual between hot knife to avoid
Interference increases by one layer of partition between hot knife；To drive hot tool apron, the elastic elements between pedestal and hot tool apron.
2. fuse cutter according to claim 1, it is characterised in that: the resistance wire is controlled by external circuit,
Or increase control circuit in cutter.
3. fuse cutter according to claim 1, it is characterised in that: the quantity of the hot knife be two layers or two layers with
On.
4. fuse cutter according to claim 1, it is characterised in that: the material of the partition uses Teflon.
5. fuse cutter according to claim 1, it is characterised in that: the elastic element is compressed spring.
6. fuse cutter according to claim 1, it is characterised in that: there is mounting post on the pedestal, it is right on upper cover plate
There is the cooperation of the mounting post on mounting hole and pedestal in the position answered, is attached using screw.
7. fuse cutter according to claim 1, it is characterised in that: the cutting object of the cutter is high-intensitive poly-
Vinyl fiber.
8. fuse cutter according to claim 8, it is characterised in that: the diameter value of the high-strength polyethylene fiber is
1mm, the pulling force on rope are 200N.
9. fuse cutter according to claim 9, it is characterised in that: the resistance wire is about 49mm, and resistance value is about
0.8Ω。
10. making fuse cutter according to claim 1, it is characterised in that: the pedestal uses aluminium alloy 2A12, hot knife
Seat and upper cover plate use glass reinforced plastic, the model OD.LZ1-6 of pressure line terminal.
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 true CN109515761A (en) | 2019-03-26 |
| CN109515761B 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) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111969291A (en) * | 2020-08-18 | 2020-11-20 | 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 |
| CN117759679A (en) * | 2023-12-28 | 2024-03-26 | 东莞理工学院 | A vibration isolation and noise reduction system for manned spacecraft control moment gyro |
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|---|---|---|---|---|
| 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 |
| US20150115106A1 (en) * | 2011-09-29 | 2015-04-30 | The Government Of The Us, As Represented By The Secretary Of The Navy | Separation system and burn wire release mechanism for tethered spacecraft |
| US20150372374A1 (en) * | 2014-06-24 | 2015-12-24 | Los Alamos National Security, Llc | Space vehicle electromechanical system and helical antenna winding fixture |
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-
2018
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| US6439122B1 (en) * | 2000-01-28 | 2002-08-27 | Lockhead Martin Corporation | Separation system for missile payload fairings |
| US20150115106A1 (en) * | 2011-09-29 | 2015-04-30 | The Government Of The Us, As Represented By The Secretary Of The Navy | Separation system and burn wire release mechanism for tethered spacecraft |
| US20150372374A1 (en) * | 2014-06-24 | 2015-12-24 | Los Alamos National Security, Llc | Space vehicle electromechanical system and helical antenna winding fixture |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111969291A (en) * | 2020-08-18 | 2020-11-20 | 天津航天机电设备研究所 | Satellite antenna pressing and unlocking device and using method |
| 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 |
| CN117759679A (en) * | 2023-12-28 | 2024-03-26 | 东莞理工学院 | A vibration isolation and noise reduction system for manned spacecraft control moment gyro |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109515761B (en) | 2024-04-02 |
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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 |