KR101230493B1 - Hinge for deployment solar panels and the method using the same - Google Patents

Hinge for deployment solar panels and the method using the same Download PDF

Info

Publication number
KR101230493B1
KR101230493B1 KR1020100124126A KR20100124126A KR101230493B1 KR 101230493 B1 KR101230493 B1 KR 101230493B1 KR 1020100124126 A KR1020100124126 A KR 1020100124126A KR 20100124126 A KR20100124126 A KR 20100124126A KR 101230493 B1 KR101230493 B1 KR 101230493B1
Authority
KR
South Korea
Prior art keywords
hinge
solar panel
hinge fitting
spring
deployment
Prior art date
Application number
KR1020100124126A
Other languages
Korean (ko)
Other versions
KR20120063091A (en
Inventor
박종석
Original Assignee
한국항공우주연구원
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by 한국항공우주연구원 filed Critical 한국항공우주연구원
Priority to KR1020100124126A priority Critical patent/KR101230493B1/en
Publication of KR20120063091A publication Critical patent/KR20120063091A/en
Application granted granted Critical
Publication of KR101230493B1 publication Critical patent/KR101230493B1/en

Links

Images

Classifications

    • 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
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/50—Photovoltaic [PV] energy

Landscapes

  • Engineering & Computer Science (AREA)
  • Photovoltaic Devices (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)

Abstract

The present invention relates to a solar panel deployment hinge and a method for deploying a solar panel using the hinge, and more particularly, the reliability of the satellite body by preventing the impact load during deployment of the solar panel using a spring of the shape memory alloy material And it relates to a solar panel deployment hinge that can increase the stability and a method for developing a solar panel using the hinge.
To this end, the solar panel deployment hinge according to the present invention is coupled to the first hinge fitting coupled to the first hinge fitting and the second solar panel coupled to the first solar panel and the first hinge fitting at one end, and the other end. And a steel tape coupled to the second hinge fitting and a spring varying between the first hinge fitting and the second hinge fitting.
As a result, the development speed of the solar panel can be maintained constant, thereby protecting the solar panel from impact.

Description

Hinge for deployment solar panels and the method using the same}

The present invention relates to a solar panel deployment hinge and a method for deploying a solar panel using the hinge, and more particularly, the reliability of the satellite body by preventing the impact load during deployment of the solar panel using a spring of the shape memory alloy material And it relates to a solar panel deployment hinge that can increase the stability and a method for developing a solar panel using the hinge.

Spacecraft satellites are equipped with solar panels to provide the power needed by each subsystem. Accordingly, after the satellite is loaded onto the projectile, the solar panel for generating the power source is separated from the lock of the satellite body and deployed. At this time, the impact load should not be applied during the process of detaching the solar panel from the lock and unfolding. In addition, the space should be designed to operate stably in any situation because the temperature difference is a series of extreme conditions.

Conventional solar panel deployment device uses a cylinder containing a viscous fluid and a coil and a leaf spring to generate torque, the coil generates a rotational torque of the solar panel, the viscous fluid to reduce the rotation deployment speed and impact at the last step It is in charge of letting. However, such a deployment device is difficult to match the deployment speed of the solar panel by the cylinder, and because these devices are composed of mechanical devices, there is a problem that does not provide enough stability and reliability in space.

In addition, the hinge for deploying a solar tape type solar panel using existing strain energy is not easy to control the deployment speed. In this case, the shock due to excessive development speed may cause structural stability of the solar cell attached to the solar panel or sudden increase in moment load in the solar panel and the satellite body. Therefore, there is a need for a hinge that can control such excessive deployment speed.

The present invention was created in order to solve the above-described problems, and to develop a solar panel using a hinge for developing a solar panel and a hinge for improving the reliability and stability of the satellite by preventing the impact load during the deployment of the solar panel. The purpose is to provide a method.

Solar panel deployment hinge according to the present invention for achieving the above object, the first hinge fitting coupled to the first solar panel and the second hinge fitting coupled to the second solar panel and the first hinge fitting at one end and And a steel tape coupled to the other end and coupled to the second hinge fitting and a spring varying between the first hinge fitting and the second hinge fitting.

In addition, the spring may be mounted between the first hinge fitting and the second hinge fitting, the spring may comprise a shape memory alloy.

The solar panel deployment hinge may further include a power supply unit supplying power to the shape memory alloy, wherein the power supply unit supplies power at a predetermined initial time when the solar panel is deployed, The power supply can be cut off in time.

In addition, the steel tape may be equipped with a strain gauge, the power supplied from the power supply may vary according to the strain of the strain gauge.

On the other hand, the method for deploying a solar panel using a hinge according to the present invention for achieving the above object is the step of supplying power to the spring mounted between the first hinge fitting and the second hinge fitting and at the first end Comparing the strain of the steel tape coupled to the hinge fitting and the second hinge fitting at the other end with a predetermined value, and adjusting the power supply amount according to the comparison result and the spring power according to the adjusted power supply amount. And changing the stiffness and adjusting the unfolding speed of the steel tape according to the stiffness change of the spring.

In addition, the spring may include a shape memory alloy material.

According to the solar panel deployment hinge according to the invention and a method for developing a solar panel using the hinge,

First, it is possible to maintain a constant development rate of the solar panel can protect the solar panel from impact.

Second, the development speed of the solar panel can be kept constant, which increases the stability and reliability.

1 is a view showing a folded shape of the hinge according to the present invention.
2 is a view showing the stiffness change of the spring of the shape memory alloy.
3 is a view showing a shape in which the hinge according to the present invention is deployed.
4 shows an embodiment of a hinge according to the invention.
5 is a flowchart of a method for deploying a solar panel using a hinge according to the present invention.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. Prior to this, terms and words used in the present specification and claims should not be construed as limited to ordinary or dictionary terms, and the inventor should appropriately interpret the concepts of the terms appropriately The present invention should be construed in accordance with the meaning and concept consistent with the technical idea of the present invention.

Therefore, the embodiments described in this specification and the configurations shown in the drawings are merely the most preferred embodiments of the present invention and do not represent all the technical ideas of the present invention. Therefore, It is to be understood that equivalents and modifications are possible.

The present invention relates to a solar panel deployment hinge that can increase the reliability and stability of the satellite body by preventing impact loads when the solar panel is deployed using a spring of a shape memory alloy material, and a method of deploying the solar panel using the hinge. will be.

1 is a view showing a folded shape of the hinge according to the present invention, with reference to FIG. 1 will be described for the solar panel deployment hinge according to the present invention.

First, the solar panel deployment hinge 100 includes a first hinge fitting 110 coupled to a first solar panel, a second hinge fitting 120 coupled to a second solar panel, and one end of the first hinge fitting 110. And a spring 140 that is coupled to the other end of the steel tape 130 and the first hinge fitting 110 and the second hinge fitting 120 that are coupled to the second hinge fitting 120. Include.

The spring 140 is mounted between the first hinge fitting 110 and the second hinge fitting 120 and may be formed of a shape memory alloy. The shape memory alloy is formed by forming a material of a certain shape at a higher temperature than the critical temperature (shaping treatment temperature), and then quenching it to remember the shape. It is a material that returns to the original shape that was remembered because the deformation is lost. In other words, titanium-nickel alloys are typical alloys that have a property of returning to a shape before deformation even if they are transformed into other shapes.

2 is a view showing the stiffness change of the spring made of the shape memory alloy, when the shape memory alloy is produced in the spring type as the present invention can induce a stiffness change. This will be described again below.

Meanwhile, the solar panel deployment hinge 100 according to the present invention may further include a power supply unit 150 for supplying power to the shape memory alloy. When the solar panel 200 is deployed, the power supply unit 150 supplies power at a predetermined early time, and stops supplying power at a preset second time.

For example, the steel tape 130 may be equipped with a strain gauge, the rigidity of the spring 140 of the hinge by varying the power supplied from the power supply unit 150 according to the strain of the strain gauge Induces a change to control the speed at which the solar panel 200 is deployed.

That is, if the strain of the strain gauge of the steel tape 130 is more than the predetermined level corresponds to the initial stage of the development of the solar panel 200, the strain value decreases as the development proceeds, by which the solar panel 200 is deployed When power is supplied through the power supply unit 150 at the start of the shape memory alloy spring 140, the rigidity is large enough to control the deployment speed of the hinge 100.

In the same principle, when the second half of the deployment of the predetermined solar panel 200 through the strain of the strain gauge of the steel tape 130, the power supply unit 150 stops supplying power to the shape memory alloy spring 140 Relative rigidity of the () so that the deployment rigidity of the hinge 100 can act on the full deployment of the solar panel. 3 is a view showing a shape in which the hinge according to the present invention is deployed.

4 illustrates an embodiment of a hinge according to the present invention, and shows a shape in which the solar panel 200 is fully developed by the solar panel deployment hinge according to the present invention. As such, by controlling the speed at which the solar panel is deployed using the shape memory alloy material, the structural stability of the solar cell attached to the solar panel can be guaranteed, and a sudden moment load is increased in the portion mounted on the solar panel and the satellite body. Can be prevented.

On the other hand, Figure 5 is a flow chart of a method for developing a solar panel using a hinge according to the present invention, with reference to Figure 5 describes a method for developing a solar panel using a hinge according to the present invention.

First, when power is supplied to a spring mounted between the first hinge fitting and the second hinge fitting (S10), the spring returns to the shape memorized by the temperature change when the spring is made of the shape memory alloy material. Using this restoring force to return to the memorized shape, the stiffness change of the spring is induced.

Next, the strain of the steel tape coupled to the first hinge fitting at one end and the second hinge fitting at the other end is compared with a predetermined value (S20) to adjust the amount of power supply according to the comparison result (S30). . The adjustment method is as described above in the solar panel deployment hinge. As the power supply amount is adjusted as described above, the stiffness of the spring is changed (S40), and the development speed of the steel tape is adjusted according to the stiffness of the spring (S50).

As described above, although the present invention has been described by way of limited embodiments and drawings, the present invention is not limited thereto and is intended by those skilled in the art to which the present invention pertains. Of course, various modifications and variations are possible within the scope of equivalents of the claims to be described.

100 hinge
110 first hinge fitting 120 second hinge fitting
130 Steel Tape 140 Spring
150 Power Supply
200 solar panels

Claims (8)

delete delete A first hinge fitting coupled to the first solar panel;
A second hinge fitting coupled to the second solar panel;
A steel tape coupled to the first hinge fitting at one end and coupled to the second hinge fitting at the other end; And
And a spring that varies between the first hinge fitting and the second hinge fitting.
The spring is,
Mounted between the first hinge fitting and the second hinge fitting,
A solar panel deployment hinge comprising a shape memory alloy. The method of claim 3, wherein
A solar panel deployment hinge further comprising; a power supply unit for supplying power to the shape memory alloy. The method of claim 4, wherein
The power supply unit,
A solar panel deployment hinge, characterized in that when the solar panel is deployed, the power is supplied at a predetermined early time, and the power supply is stopped at a predetermined second time. The method of claim 4, wherein
The steel tape,
Characterized in that the strain gauge is mounted,
The solar panel deployment hinge, characterized in that the power supplied from the power supply is changed according to the strain of the strain gauge. delete Supplying power to a spring mounted between the first hinge fitting and the second hinge fitting;
Comparing the strain of the steel tape coupled to the first hinge fitting at one end and coupled to the second hinge fitting at the other end with a predetermined value;
Adjusting a power supply amount according to the comparison result;
Changing the rigidity of the spring according to the adjusted power supply amount; And
Including the step of adjusting the deployment speed of the steel tape in accordance with the change in the rigidity of the spring;
The spring is a method of deploying a solar panel using a hinge, characterized in that it comprises a shape memory alloy material.
KR1020100124126A 2010-12-07 2010-12-07 Hinge for deployment solar panels and the method using the same KR101230493B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
KR1020100124126A KR101230493B1 (en) 2010-12-07 2010-12-07 Hinge for deployment solar panels and the method using the same

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
KR1020100124126A KR101230493B1 (en) 2010-12-07 2010-12-07 Hinge for deployment solar panels and the method using the same

Publications (2)

Publication Number Publication Date
KR20120063091A KR20120063091A (en) 2012-06-15
KR101230493B1 true KR101230493B1 (en) 2013-02-06

Family

ID=46683678

Family Applications (1)

Application Number Title Priority Date Filing Date
KR1020100124126A KR101230493B1 (en) 2010-12-07 2010-12-07 Hinge for deployment solar panels and the method using the same

Country Status (1)

Country Link
KR (1) KR101230493B1 (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101468997B1 (en) * 2013-08-27 2014-12-04 한국항공우주연구원 Satellite for deployment apparatus using tape spring hinge and coil spring hinge
KR101495246B1 (en) * 2014-03-20 2015-02-25 한국과학기술원 Structure Deploying Apparatus and Satellite Equipping it
KR102540371B1 (en) * 2020-06-25 2023-06-05 주식회사 케이티앤지 Aerosol generating device
WO2022139339A1 (en) * 2020-12-22 2022-06-30 엘아이지넥스원 주식회사 Yokes with viscoelastic characteristics and deployable solar palels using same
CN113957962A (en) * 2021-09-26 2022-01-21 广东广深环保科技股份有限公司 Movable intelligent solar environment-friendly toilet

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR19980053892U (en) * 1996-12-31 1998-10-07 추호석 Locking and deploying device of solar panel of satellite
KR20090081139A (en) * 2008-01-23 2009-07-28 한국기계연구원 Artificial Satellite of Hinge-equipment

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR19980053892U (en) * 1996-12-31 1998-10-07 추호석 Locking and deploying device of solar panel of satellite
KR20090081139A (en) * 2008-01-23 2009-07-28 한국기계연구원 Artificial Satellite of Hinge-equipment

Also Published As

Publication number Publication date
KR20120063091A (en) 2012-06-15

Similar Documents

Publication Publication Date Title
KR101230493B1 (en) Hinge for deployment solar panels and the method using the same
US9663252B1 (en) Method for attitude controlling based on finite time friction estimation for flexible spacecraft
Yeh et al. Nonlinear tracking control for satellite formations
JP7253061B2 (en) Launch vehicle and multi-stage pneumatic support cylinders for retrieving the launch vehicle
US9045241B2 (en) Method for reducing the angular momentum and controlling the attitude of a spacecraft
JP4061652B2 (en) Attitude control method for satellites in elliptical orbit using solar radiation energy
Zhou et al. Magnetic attitude control for Earth-pointing satellites in the presence of gravity gradient
JP6433607B2 (en) Method and device for controlling the attitude of a spacecraft
US10641320B2 (en) Shock reducing tape spring hinge
CA2728393C (en) Method and device for optimization of the mass of a satellite
US20170174366A1 (en) Device for retaining and releasing appendages
CN107323690B (en) Satellite large-angle momentum compensation synchronism design method
Zhu et al. Effect of drive mechanisms on dynamic characteristics of spacecraft tracking-drive flexible systems
US20210171179A1 (en) Strategy for safeguarding an airship in the event of heating of its solar generator
JP6793724B2 (en) Deployment of solar arrays
US8401717B2 (en) Actuator control reducing the level of vibration of an associated flexible structure
Yang et al. Fault tolerant pi control design for satellite attitude systems with actuator fault
Höhn Design, construction and validation of an articulated solar panel for CubeSats
KR101009418B1 (en) Asymmetry satellite apparatus, momentum dumping method and rotation angle setting method for asymmetry satellite
KR19980053892U (en) Locking and deploying device of solar panel of satellite
Chen et al. Modelica-based modeling and simulation of satellite On-orbit deployment and attitude control
US7712706B2 (en) Space tethers for limiting the dynamic response of structures
Flanigan et al. MESSENGER’s Maneuvers to Reduce Orbital Period During the Extended Mission: Ensuring Maximum Use of the Bi-Propellant Propulsion System
Bedrossian et al. ISS contingency attitude control recovery method for loss of automatic thruster control
Oguri et al. Design Criteria of Reflectivity Control System Under Uncertainty in Sail Property for Maneuverability Requirement of Spinning Solar Sail

Legal Events

Date Code Title Description
A201 Request for examination
E902 Notification of reason for refusal
E701 Decision to grant or registration of patent right
GRNT Written decision to grant
LAPS Lapse due to unpaid annual fee