CN103696916A - Straight acting device for spacecraft based on SMA (Shape Memory Alloy) spring and use method thereof - Google Patents
Straight acting device for spacecraft based on SMA (Shape Memory Alloy) spring and use method thereof Download PDFInfo
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- CN103696916A CN103696916A CN201310658735.9A CN201310658735A CN103696916A CN 103696916 A CN103696916 A CN 103696916A CN 201310658735 A CN201310658735 A CN 201310658735A CN 103696916 A CN103696916 A CN 103696916A
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Abstract
The invention discloses a straight acting device for a spacecraft based on an SMA (Shape Memory Alloy) spring and a use method thereof. The straight acting device for the spacecraft based on the SMA spring comprises a piston jacking rod, an upper end cover, a limiting spring, a sleeve, the SMA spring, a heater resistance wire, an electric heater, a soft outgoing line and an electric connector, wherein the sleeve is a piston cavity; a piston acting rod, the limiting spring, the SMA spring, the electric heater and the soft outgoing line are arranged in the sleeve from top to bottom; when the straight acting device does not work, the piston jacking rod is restrained in an initial position by the limiting spring, and the limiting spring and the SMA spring are balanced; when the straight acting device acts in orbit, any one of two heating wires in the heater is electrified through instruction, the SMA spring is heated, after the temperature reaches a phase-transition temperature, memory alloy is subjected to phase-transition, and the heat expanding type SMA spring stretches out and drives the piston jacking rod. The straight acting device for the spacecraft based on the SMA spring utilizes the advantage of easiness in controlling the action of the SMA spring and ensures the high reliability of a spacecraft mechanism.
Description
Technical field
The present invention relates to a kind of straight line actuator and using method thereof, particularly relate to a kind of based on SMA(marmem) straight line actuator and using method thereof for the astrovehicle of spring.
Background technique
The actuation mechanism of using on astrovehicle at present, having applied more is the spring push-rod formula device that uses common Compress Spring start, the shortcoming of this device is that the initial compression force of spring is large, needs larger pretightening force to overcome the effect of spring, and is not easy to start control.And in the spring-actuated space flight mechanism design based on SMA, due to the limited space of pressurized strut, therefore, the heating of memory alloy spring has been proposed compared with high requirement: as low in energy consumption, efficiency is high, volume is little, easy to connect etc.
Summary of the invention
Technical problem to be solved by this invention is to provide straight line actuator and using method thereof for a kind of astrovehicle based on SMA spring, and it had both utilized the start of SMA spring to be easy to the advantage of controlling, and has guaranteed again the high reliability, low power consumption of space flight mechanism etc.
The present invention solves above-mentioned technical problem by following technical proposals: a kind of straight line actuator of the astrovehicle based on SMA spring, it is characterized in that, it comprises piston mandril, upper end cap, limit spring, sleeve, SMA spring, heater resistance wire, electric heater, soft lighting outlet, electric coupler, described sleeve is a piston cavity, is furnished with piston operating bar, limit spring, SMA spring, electric heater, soft lighting outlet in sleeve from top to bottom; When not needing start, limit spring constrains in initial position by piston mandril, and forms balance with SMA spring; While needing start in-orbit, by instruction, to arbitrary group of two heating wire in heater, switch on, SMA spring is heated up, when it reaches after phase transition temperature, memory alloy undergoes phase transition, and the rise SMA spring of formula of heat is stretched external start driven plunger push rod.
Preferably, the described astrovehicle based on SMA spring comprises position hold mode and actuator state with straight line actuator, when in position hold mode, described SMA spring is in martensite compressive state, described limit spring is in extended configuration, and the convex platform lower end surface of piston mandril flushes with sleeve upper-end surface; When in actuator state, described SMA spring is in austenite extended configuration, and described limit spring, in compressive state, promotes piston mandril and stretches out sleeve.
Preferably, described electric heater is two resistance wire Redundancy Design, and two resistance wires adopt the transition of bridge-type mode.
The present invention also provides the using method of a kind of astrovehicle based on SMA spring with straight line actuator, it is characterized in that, it comprises the following steps: utilize electric heater to heat SMA spring, thereby undergo phase transition after SMA spring is heated, recover the axial motion of deformation driving operating bar, realize external start, limit spring is spacing to the axial motion generation of operating bar simultaneously, and the motion of operating bar is produced to buffer function.
Positive progressive effect of the present invention is: first, the space actuation mechanism that is applied to small volume of the present invention, by design, make actuator there is the functional characteristics such as start process is easy to control, the load of position hold mode is little, reusable, make this invention meet space flight usage requirement.Secondly, the actuator that is applied to space of the present invention has taken into full account the factors such as processing technology, interface installation in design process, make whole device there is interface simple, quality is light, self-resetting, the features such as extensibility is strong, only need modify to associated components, just can meet the requirement of installing and using of different astrovehicles.Moreover, during designing, the actuator that is applied to space of the present invention considered the redundancy requirement of space flight mechanism, be designed with two electric resistance silks, guaranteed high reliability request in-orbit.Prove by analysis, of the present inventionly be applied to that astrovehicle mechanism straight line actuator principle is correct in-orbit, there is the functions such as connection interface is simple, start process is easy to control, reusable, whole device quality is light, the features such as the little extensibility of volume is strong, can meet the requirement of installing and using of different astrovehicles, there is higher versatility.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of straight line actuator for the astrovehicle based on SMA spring provided by the invention;
Fig. 2 is the schematic diagram of straight line actuator for the astrovehicle based on SMA spring provided by the invention.
In figure:
1 is piston mandril;
2 upper end caps;
3 is limit spring;
4 is sleeve;
5 is SMA spring;
6 is heater resistance wire;
7 is electric heater;
8 is soft lighting outlet;
9 is electric coupler.
Embodiment
Below in conjunction with accompanying drawing, provide preferred embodiment of the present invention, to describe technological scheme of the present invention in detail.
Below in conjunction with specific embodiment, the present invention is described in detail.Following examples will contribute to those skilled in the art further to understand the present invention, but not limit in any form the present invention.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, can also make some distortion and improvement.These all belong to protection scope of the present invention.
As depicted in figs. 1 and 2, a kind of astrovehicle based on SMA spring comprises piston mandril 1, upper end cap 2, limit spring 3, sleeve 4, SMA spring 5, heater resistance wire 6, electric heater 7, soft lighting outlet 8, electric coupler 9 with straight line actuator, described sleeve 4 is a piston cavity, is furnished with piston operating bar 1, limit spring 3, SMA spring 5, electric heater 7, soft lighting outlet 8 in sleeve 4 from top to bottom; When not needing start, limit spring 3 constrains in initial position by piston mandril 1, and forms balance with SMA spring 5; While needing start in-orbit, by instruction, to arbitrary group of two heating wire in heater, switch on, SMA spring 5 is heated up, when it reaches after phase transition temperature, memory alloy undergoes phase transition, and the rise SMA spring 5 of formula of heat is stretched external start driven plunger push rod 1.
The upper end perforate of described sleeve, lower end is furnished with screw thread; Described limit spring one end is spacing by described sleeve upper end, and the other end contacts with piston mandril; One end of described SMA spring contacts with piston mandril, and the other end contacts with described sleeve lower end surface; Between described SMA spring and limit spring, coordinate to realize the position of described piston mandril is kept.
Astrovehicle based on SMA spring comprises position hold mode and actuator state with straight line actuator, when in position hold mode, described SMA spring is in martensite compressive state, and described limit spring is in extended configuration, and the convex platform lower end surface of piston mandril 1 flushes with sleeve 4 upper-end surfaces; When in actuator state, described SMA spring is in austenite extended configuration, and described limit spring, in compressive state, promotes piston mandril 1 and stretches out sleeve 4.
Between described electric heater and sleeve, be provided with connecting thread.
Described electric heater 7 is two resistance wire Redundancy Design, and two resistance wires adopt the transition of bridge-type mode.
Astrovehicle based on SMA spring comprises the following steps by the using method of straight line actuator: utilize electric heater to heat SMA spring, thereby undergo phase transition after SMA spring is heated, recover the axial motion of deformation driving operating bar, realize external start, limit spring is spacing to the axial motion generation of operating bar simultaneously, and the motion of operating bar is produced to buffer function.
The present invention is achieved through the following technical solutions, and a kind of astrovehicle based on SMA spring of the present invention comprises the parts such as piston mandril, upper end cap, limit spring, sleeve, SMA spring, heater resistance wire, electric heater, soft lighting outlet, electric coupler with straight line actuator.By the heat effect of heater, under the effect of SMA spring that recovers deformation, promote piston mandril axial motion, realize external start.And limit spring plays that the initial position of push rod keeps and axial motion spacing, heater is furnished with screw thread, realizes fixing and being connected of heating element and agent structure sleeve.
Selected actuation element is SMA spring, by adding thermal deformation, recover and start, and SMA is used external existing a lot of cases, external application in recent years progressively to increase on astrovehicle, by the heating of memory alloy being realized to two states, i.e. position hold mode and actuator state.
Use common Compress Spring to keep and axial motion limit element as the initial position of piston mandril, the power of the initial position maintenance of piston mandril is provided on the one hand, provide on the other hand ejector rob axis to sports limiting and damping force.
The heater of selecting is as the heating function of memory alloy, and in heater, provides the redundancy backup ability of heating, the heater of integrated design to provide heating element to be connected with main structure and the facility of dismounting.
The present invention, after its main structure sleeve is fixed, heats to realize the start to piston rod member to SMA spring with two redundant electric heaters of sleeve integrated design by one, thereby externally drives.When driving, can pass through different instruction, control respectively to one group of independent heating wire and power up or two groups of heating wires power up and power-off simultaneously, realize the Redundancy Design of heating process, to reach the high reliability of actuation mechanism.The dexterous layout that the invention solves in less space operating bar, heater, shape memory alloy spring and main structure part be connected, when guaranteeing effectively reliable start, reduced to greatest extent the enveloping space of whole mechanism.
Above specific embodiments of the invention are described.It will be appreciated that, the present invention is not limited to above-mentioned specific implementations, and those skilled in the art can make various distortion or modification within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (4)
1. the straight line actuator of the astrovehicle based on SMA spring, it is characterized in that, it comprises piston mandril, upper end cap, limit spring, sleeve, SMA spring, heater resistance wire, electric heater, soft lighting outlet, electric coupler, described sleeve is a piston cavity, is furnished with piston operating bar, limit spring, SMA spring, electric heater, soft lighting outlet in sleeve from top to bottom; When not needing start, limit spring constrains in initial position by piston mandril, and forms balance with SMA spring; While needing start in-orbit, by instruction, to arbitrary group of two heating wire in heater, switch on, SMA spring is heated up, when it reaches after phase transition temperature, memory alloy undergoes phase transition, and the rise SMA spring of formula of heat is stretched external start driven plunger push rod.
2. the straight line actuator of the astrovehicle based on SMA spring as claimed in claim 1, it is characterized in that, the described astrovehicle based on SMA spring comprises position hold mode and actuator state with straight line actuator, when in position hold mode, described SMA spring is in martensite compressive state, described limit spring is in extended configuration, and the convex platform lower end surface of piston mandril flushes with sleeve upper-end surface; When in actuator state, described SMA spring is in austenite extended configuration, and described limit spring, in compressive state, promotes piston mandril and stretches out sleeve.
3. the straight line actuator of the astrovehicle based on SMA spring as claimed in claim 1, is characterized in that, described electric heater is two resistance wire Redundancy Design, and two resistance wires adopt the transition of bridge-type mode.
4. the using method of straight line actuator for an astrovehicle based on SMA spring, it is characterized in that, it comprises the following steps: utilize electric heater to heat SMA spring, thereby undergo phase transition after SMA spring is heated, recover the axial motion of deformation driving operating bar, realize external start, limit spring is spacing to the axial motion generation of operating bar simultaneously, and the motion of operating bar is produced to buffer function.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310658735.9A CN103696916A (en) | 2013-12-06 | 2013-12-06 | Straight acting device for spacecraft based on SMA (Shape Memory Alloy) spring and use method thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310658735.9A CN103696916A (en) | 2013-12-06 | 2013-12-06 | Straight acting device for spacecraft based on SMA (Shape Memory Alloy) spring and use method thereof |
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| CN103696916A true CN103696916A (en) | 2014-04-02 |
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|---|---|---|---|
| CN201310658735.9A Pending CN103696916A (en) | 2013-12-06 | 2013-12-06 | Straight acting device for spacecraft based on SMA (Shape Memory Alloy) spring and use method thereof |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104833271A (en) * | 2015-05-22 | 2015-08-12 | 北京航空航天大学 | Shape memory alloy driver |
| CN107352049A (en) * | 2017-06-06 | 2017-11-17 | 上海卫星工程研究所 | Spacecraft memorial alloy driving rope holds repeatable tripper tightly |
| KR101805589B1 (en) * | 2016-07-01 | 2017-12-07 | 한국항공대학교산학협력단 | Active vortex generator using sma linear actuator |
| CN108869216A (en) * | 2018-06-19 | 2018-11-23 | 北京航空航天大学 | A kind of non-firer's paraffin driver of Rapid reset using SMA spring |
| CN112096583A (en) * | 2020-09-16 | 2020-12-18 | 电子科技大学 | SMA electric excitation type two-way rotary actuator |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4984542A (en) * | 1989-08-24 | 1991-01-15 | Mcguane Industries | Thermal throttle actuator |
| JPH07167037A (en) * | 1993-12-16 | 1995-07-04 | Sanki Eng Co Ltd | Shape memory alloy actuator |
| US6124662A (en) * | 1999-03-22 | 2000-09-26 | Maness; Richard | Actuator using electrical contacts pressed in abutment |
| CN102003363A (en) * | 2010-11-19 | 2011-04-06 | 哈尔滨工业大学 | Square telescopic shape memory alloy actuator for adding activation force |
-
2013
- 2013-12-06 CN CN201310658735.9A patent/CN103696916A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4984542A (en) * | 1989-08-24 | 1991-01-15 | Mcguane Industries | Thermal throttle actuator |
| JPH07167037A (en) * | 1993-12-16 | 1995-07-04 | Sanki Eng Co Ltd | Shape memory alloy actuator |
| US6124662A (en) * | 1999-03-22 | 2000-09-26 | Maness; Richard | Actuator using electrical contacts pressed in abutment |
| CN102003363A (en) * | 2010-11-19 | 2011-04-06 | 哈尔滨工业大学 | Square telescopic shape memory alloy actuator for adding activation force |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104833271A (en) * | 2015-05-22 | 2015-08-12 | 北京航空航天大学 | Shape memory alloy driver |
| KR101805589B1 (en) * | 2016-07-01 | 2017-12-07 | 한국항공대학교산학협력단 | Active vortex generator using sma linear actuator |
| CN107352049A (en) * | 2017-06-06 | 2017-11-17 | 上海卫星工程研究所 | Spacecraft memorial alloy driving rope holds repeatable tripper tightly |
| CN108869216A (en) * | 2018-06-19 | 2018-11-23 | 北京航空航天大学 | A kind of non-firer's paraffin driver of Rapid reset using SMA spring |
| CN112096583A (en) * | 2020-09-16 | 2020-12-18 | 电子科技大学 | SMA electric excitation type two-way rotary actuator |
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Application publication date: 20140402 |