SHOCK REDUCING TAPE SPRING HINGE

• US 20180142729A1
• Filed: 03/03/2017
• Published: 05/24/2018
• Est. Priority Date: 11/21/2016
• Status: Active Grant

• Current Assignee: Korea Aerospace Research Institute
• Original Assignee: Korea Aerospace Research Institute
• Inventors: LEE, Chang Ho, KIM, Kyung Won, JEONG, Ju Won, KIM, Young Jin, LEE, Jung Ju
• Granted Patent: US 10,641,320 B2
• Time in Patent Office: Days
• CPC Class Codes: B64G 1/222 for deploying structures between a stowed and deployed state
• CPC Class Codes: B64G 1/443 Photovoltaic cell arrays
• CPC Class Codes: F16C 11/12 incorporating flexible connections, e.g. leaf springs
• CPC Class Codes: F16F 1/027 Planar, e.g. in sheet form; leaf springs
• CPC Class Codes: F16F 13/00 Units comprising springs of the non-fluid type as well as vibration-dampers, shock-absorbers, or fluid springs F16F5/00, F16F6/00, F16F9/003 take precedence
• CPC Class Codes: F16F 2224/0258 Shape-memory metals, e.g. Ni-Ti alloys
• CPC Class Codes: F16F 3/02 with springs made of steel or of other material having low internal friction

Abstract

Provided is a shock reducing tape spring hinge including fixing members fixed to at least two objects, respectively, a thin shell type tape spring having both end portions that are fastened to the fixing members, respectively, and a shell-shaped damping plate aligned with the tape spring, the damping plate having both end portions that are fastened to the fixing members, respectively. The damping plate and the tape spring may be configured to connect the at least two objects being spaced through the fixing members, and the damping plate may be configured to reduce a deployment shock occurring when the tape spring is deployed.

Claims

1. A shock reducing tape spring hinge, comprising:

fixing members fixed to at least two objects, respectively;

a thin shell type tape spring having both end portions that are fastened to the fixing members, respectively; and

a shell-shaped damping plate aligned with the tape spring, the damping plate having both end portions that are fastened to the fixing members, respectively,

wherein the damping plate and the tape spring are configured to connect the at least two objects being spaced through the fixing members, and the damping plate is configured to reduce a deployment shock occurring when the tape spring is deployed.

2. The shock reducing tape spring hinge of claim 1, wherein two tape springs are disposed parallel to each other, and

the damping plate is disposed between the two tape springs.

3. The shock reducing tape spring hinge of claim 1, wherein the damping plate has a crystal structure and a mechanical characteristic that change based on a temperature.

4. The shock reducing tape spring hinge of claim 3, wherein the damping plate comprises a shape memory alloy, and

the martensite-phase damping plate is deployed in a state of being bent along with the tape spring, and simultaneously the damping plate is configured to reduce a deployment speed of the tape spring by generating a reducing moment corresponding to a deployment moment of the tape spring.

5. The shock reducing tape spring hinge of claim 1, wherein an opening is formed at a center of the damping plate to determine a reducing moment of the damping plate corresponding to a deployment moment caused by the tape spring.

6. The shock reducing tape spring hinge of claim 1, wherein the tape spring and the damping plate each have a curved cross section.

7. A solar array wing for a satellite comprising a shock reducing hinge, the solar array wing comprising:

several solar panels; and

a shock reducing hinge being bent, the shock reducing hinge configured to connect the several solar panels,

wherein the shock reducing hinge comprises;

a shell-shaped damping plate; and

fixing members fastened to both end portions of the damping plate,

wherein the fixing members are connected to the several solar panels, and the damping plate is disposed between the solar panels to reduce deployment shocks of the solar array wing.

8. The solar array wing of claim 7, wherein the damping plate is configured to perform a martensite detwinning transformation or an austenite phase transformation by a change in temperature and a deformation force.

9. The solar array wing of claim 8, wherein the damping plate is deformed by a martensitic detwinning transformation occurring during a deployment process, and reduces a deployment shock of the shock reducing hinge by causing a residual moment that resists a deployment moment.

10. The solar array wing of claim 8, wherein a stiffness of the damping plate increases as the austenite phase transformation occurs due to an increase in temperature of the solar panels after the damping plate is deployed.

11. The solar array wing of claim 8, wherein a phase transformation start temperature of the damping plate is determined based on constituents thereof, and the damping plate is replaceable with a damping plate comprising different constituents.

12. The solar array wing of claim 7, wherein the shock reducing hinge further comprises a tape spring having a curved cross section, and

the tape spring is aligned with the damping plate and fastened to the fixing members.

13. The solar array wing of claim 7, wherein the shock reducing hinge further comprises a heater configured to supply heat to the shock reducing hinge.