Functional Verification of Nylon Wire Cutting-Type Holding & Release Mechanism for 6U CubeSat"s Solar Panel

2018 ◽  
Vol 46 (10) ◽  
pp. 867-875
Author(s):  
Yeon-Hyeok Park ◽  
Ji-Seong Go ◽  
Bong-Geon Chae ◽  
Seong-Ho Lee ◽  
Hyun-Ung Oh
Keyword(s):  
Solar Panel ◽  
Functional Verification ◽  
Release Mechanism ◽  
Wire Cutting

scholarly journals Development of 6 U CubeSat’s Deployable Solar Panel with Burn Wire Triggering Holding and Release Mechanism

2019 ◽  
Vol 2019 ◽  
pp. 1-13
Author(s):  
Tae-Yong Park ◽  
Bong-Geon Chae ◽  
Hyun-Ung Oh
Keyword(s):  
Random Vibration ◽  
Printed Circuit Board ◽  
Solar Panel ◽  
Circuit Board ◽  
Structural Safety ◽  
Release Mechanism ◽  
Printed Circuit ◽  
Test Conditions ◽  
Wire Cutting ◽  
Vibration Tests

In the present work, a deployable solar panel based on a burn wire triggering holding and release mechanism was developed for use of 6 U CubeSat. The holding and release mechanism was designed based on a nichrome burn wire cutting method widely used for CubeSat applications. However, it provides a high loading capability, reliable wire cutting, multiplane constraints, and handling simplicity during the tightening process of wire. A demonstration model of a printed circuit board-based solar panel stiffened by a high-pressure fiberglass-laminated G10 material was fabricated and tested to validate the effectiveness of the design and functionality of the mechanism under various test conditions. The structural safety of the solar panel combined with the mechanism in a launch vibration environment was verified through sine and random vibration tests at qualification level.

scholarly journals Experimental CanSat Platform for Functional Verification of Burn Wire Triggering-Based Holding and Release Mechanisms

Aerospace ◽  
2021 ◽  
Vol 8 (7) ◽  
pp. 192
Author(s):  
Shankar Bhattarai ◽  
Ji-Seong Go ◽  
Hyun-Ung Oh
Keyword(s):  
Functional Performance ◽  
Flight Test ◽  
Easy Access ◽  
Functional Verification ◽  
Release Mechanism ◽  
Space Technology ◽  
Solar Panels ◽  
Distinctive Features ◽  
Release Mechanisms ◽  
Design Effectiveness

In this study, we present the Diverse Holding and Release Mechanism Can Satellite (DHRM CanSat) platform developed by the Space Technology Synthesis Laboratory (STSL) at Chosun University, South Korea. This platform focuses on several types of holding and release mechanisms (HRMs) for application in deployable appendages of nanosatellites. The objectives of the DHRM CanSat mission are to demonstrate the design effectiveness and functionality of the three newly proposed HRMs based on the burn wire triggering method, i.e., the pogo pin-type HRM, separation nut-type HRM, and Velcro tape-type HRM, which were implemented on deployable dummy solar panels of the CanSat. The proposed mechanisms have many advantages, including a high holding capability, simultaneous constraints in multi-plane directions, and simplicity of handling. Additionally, each mechanism has distinctive features, such as spring-loaded pins to initiate deployment, a plate with a thread as a nut for a high holding capability, and a hook and loop fastener for easy access to subsystems of the satellite without releasing the holding constraint. The design effectiveness and functional performance of the proposed mechanisms were demonstrated through an actual flight test of the DHRM CanSat launched by a model rocket.

scholarly journals Experimental Validation of a Highly Damped Deployable Solar Panel Module with a Pogo Pin-Based Burn Wire Triggering Release Mechanism

2020 ◽  
Vol 2020 ◽  
pp. 1-14 ◽  
Author(s):  
Shankar Bhattarai ◽  
Ji-Seong Go ◽  
Hongrae Kim ◽  
Hyun-Ung Oh
Keyword(s):  
Room Temperature ◽  
Experimental Validation ◽  
Solar Panel ◽  
Structural Safety ◽  
Release Mechanism ◽  
Thermal Vacuum ◽  
Triggering Mechanism ◽  
Damping Characteristics ◽  
Ambient Room Temperature ◽  
Design Effectiveness

In this present work, a highly damped deployable solar panel module was developed for application in the 3 U CubeSat. The solar panel proposed herein is effective in guaranteeing the structural safety of solar cells under a launch environment owing to the superior damping characteristics achieved using multilayered stiffeners with viscoelastic acrylic tapes. A holding and release action of the solar panel was achieved by a new version of spring-loaded pogo pin-based burn wire triggering mechanism. A demonstration model of high-damping solar panel assembly was fabricated and tested to validate the effectiveness of the design. The holding and release mechanism achieved using a pogo pin was functionally tested through solar panel deployment tests under ambient room temperature and a thermal vacuum environment. The design effectiveness and structural safety of the solar panel module were validated through qualification-level launch and in-orbit environment tests.

scholarly journals Development of a Novel Deployable Solar Panel and Mechanism for 6U CubeSat of STEP Cube Lab-II

Aerospace ◽  
2021 ◽  
Vol 8 (3) ◽  
pp. 64
Author(s):  
Shankar Bhattarai ◽  
Ji-Seong Go ◽  
Hongrae Kim ◽  
Hyun-Ung Oh
Keyword(s):  
Solar Cells ◽  
Printed Circuit Board ◽  
Solar Panel ◽  
Circuit Board ◽  
Structural Safety ◽  
Release Mechanism ◽  
Constrained Layer Damping ◽  
Solar Panels ◽  
Printed Circuit ◽  
Design Effectiveness

The structural safety of solar cells mounted on deployable solar panels in the launch vibration environment is a significant aspect of a successful CubeSat mission. This paper presents a novel highly damped deployable solar panel module that is effective in ensuring structural protection of solar cells under the launch environment by rapidly suppressing the vibrations transmitting through the solar panel by constrained layer damping achieved using printed circuit board (PCB)-based multilayered thin stiffeners with double-sided viscoelastic tapes. A high-damping solar panel demonstration model with a three-pogo pin-based burn wire release mechanism was fabricated and tested for application in the 6U CubeSat “STEP Cube Lab-II” developed by Chosun University, South Korea. The reliable release function and radiation hardness assurance of the mechanism in an in-orbit environment were confirmed by performing solar panel deployment tests and radiation tests, respectively. The design effectiveness and structural safety of the proposed solar panel module were validated by launch vibration and in-orbit environment tests at the qualification level.

Design of hold-down and release mechanism for solar panel of micro-satellite

2017 ◽  
Vol 25 (4) ◽  
pp. 979-986
Author(s):  
宣明 XUAN Ming ◽  
张道威 ZHANG Dao-wei ◽  
谷松 GU Song ◽  
杨林 YANG Lin ◽  
程龙 CHENG Long
Keyword(s):  
Solar Panel ◽  
Release Mechanism

Effects of release modifier on Carvedilol release from Kollidon SR based matrix

2012 ◽  
Vol 1 (8) ◽  
pp. 186 ◽  
Author(s):  
Urmi Das ◽  
Mohammad Salim Hossain
Keyword(s):  
Drug Release ◽  
Sustained Release ◽  
Microcrystalline Cellulose ◽  
Matrix Tablets ◽  
Dissolution Time ◽  
Release Mechanism ◽  
Matrix Tablet ◽  
Weight Variation ◽  
The Matrix ◽  
Tablet Formulations

<p>Sustained release Carvedilol matrix tablets constituting Kollidon SR were developed in this study in an attempt to investigate the effect of release modifiers on the release profile of Carvedilol from matrix. Three matrix tablet formulations were prepared by direct compression of Kollidon SR in combination with release modifier (HPMC and Microcrystalline Cellulose) and magnesium stearate. Tablets containing only Kollidon SR with the active ingredient demonstrated a rapid rate of drug release. Incorporation of HPMC in the matrix tablet prolonged the release of drug but incorporation of Microcrystalline Cellulose showed superimposable release pattern with an initial burst effect as confirmed by mean dissolution time and Higuchi release rate data. After 7 hours of dissolution, Carvedilol release from the matrix systems were 91.42%, 83.41%, from formulation F1 and F2 respectively. Formulation F3 exhibited 100 % release at 4 hours. All the tablet formulations showed acceptable pharmaco-technical properties and complied with the in-house specifications for tablet weight variation, friability, hardness, thickness, and diameter. Prepared tablets also showed sustained release property for carvedilol. The drug release mechanism from the matrix tablets of F1 and F2 was found to be followed by Fickian and F3 by Non-Fickian mechanism.</p><p>DOI: <a href="http://dx.doi.org/10.3329/icpj.v1i8.11095">http://dx.doi.org/10.3329/icpj.v1i8.11095</a></p> <p>International Current Pharmaceutical Journal 2012, 1(8): 186-192</p>

THE EFFECT OF FASTING AND SELECTIVE RE-FEEDING ON INSULIN RELEASE IN THE RAT

1973 ◽  
Vol 72 (1) ◽  
pp. 46-53 ◽  
Author(s):  
D. S. Turner ◽  
D. A. B. Young
Keyword(s):  
Insulin Release ◽  
Acute Effect ◽  
Secretory Response ◽  
Release Mechanism ◽  
Β Cell ◽  
Intestinal Hormones ◽  
Intravenous Glucose ◽  
Glucose Ingestion ◽  
Glucose Test ◽  
Insulin Secretory Response

ABSTRACT The insulin secretory response in the rat to intravenous glucose was found to be greatly impaired by fasting for three days, whereas that to orally administered glucose was not significantly affected. Rats fasted for two days were given either protein or starch pellets for six hours, and then fasted for a further eighteen hours before the intravenous glucose test. The protein pre-feeding failed to affect significantly the subsequent insulin secretory response to intravenous glucose, whereas starch prefeeding greatly enhanced it. It is suggested that intestinal hormones released by glucose ingestion may exert not only an acute effect on insulin release, but also a 'priming' effect on the insulin release mechanism of the β cell, which enables it to respond to the subsequent stimulus of glucose alone.

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