• Title/Summary/Keyword: Non-explosive Separation Device

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Non-explosive Separation Device Harnessing Spring Clamp and Shape Memory Alloy Wire (스프링 클램프와 형상기억합금 와이어를 이용한 비폭발식 분리장치)

  • Choi, Junwoo;Lee, Dongkyu;Hwang, Kukha;Lee, Minhyung;Kim, Byungkyu
    • Journal of Aerospace System Engineering
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    • v.9 no.2
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    • pp.7-12
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    • 2015
  • In this paper, we report a non-explosive separation device for a small satellite which utilize a shape memory alloy actuator and spring clamp. In order to increase the preload, the proposed device employs spring clamp that can generate high toque when the shape memory alloy actuator makes the cylinder key unlatch a holding ball effectively. Owing to simple design of separation device configuration, we could obtain good repeatability(up to 30 times activation). Conclusively, we could develop a non-explosive separation device which can reliably activate within 1.2 sec under high preload(up to 300kgf).

Performance evaluation on the separation device activated by shape memory alloy actuator (형상기억합금을 이용한 소형 위성용 분리장치의 성능평가)

  • Choi, Junwoo;Lee, Dongkyu;Hwang, Kukha;Lee, Minhyung;Kim, Byungkyu
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.43 no.7
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    • pp.635-640
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    • 2015
  • In this paper, we report a non-explosive separation device for a small satellite which utilize a shape memory alloy actuator. Based on previous research, we try to increase the reliability of the proposed device by changing some components. It enables the proposed device to activate under high preload. Also, we confirm it generates low shock which is main advantage of non-explosive separation device. Finally, vibration test which mimics launching environment and thermal vacuum test which mimics space environment are carried out respectively. After each environment test, we confirm the proposed device is successfully activated. Conclusively, we develop a non-explosive separation device which can activate with low shock under high preload after shock and environment tests(vibration and thermal vacuum tests).

Development of Non-Electric and Delay Explosive Bolt (비전기식 지연형 폭발볼트 개발)

  • Lee YeungJo;Kim DongJin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • v.y2005m4
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    • pp.92-95
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    • 2005
  • The present work has been developed the type of non-electric and delay explosive bolt which does not need power supply device and has the delay function in the operation of the explosive bolt. Separation device system could be minimized because of non-electric power supply system. In order to prove the mechanism of operation, the present work used to ignite the initiator the power of air resistance caused front aviation object. we can be founded from the present work that the changes in the operation load influence directly the ignition of the initiator. The design of non-electric and delay explosive bolt is the most suitable the separation system necessary to reduce the velocity of aviation object and safe landing of parachute system.

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Non-explosive separation device using screw jack mechanism (나사잭 메커니즘을 이용한 비폭발식 분리장치)

  • Park, Hyun-Jun;Lee, Min-Su;Jo, Jae-Wook;Kim, Byung-Kyu
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.38 no.4
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    • pp.321-326
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    • 2010
  • The non-explosive release device using jack mechanism is designed and fabricated for the small satellite. As a triggering actuator for the release device, a piezo rotory motor with torque of more than $1.7kgf{\cdot}cm$ is employed to guarantee stable activation. For performance tests of separation device, we conducted release time test, preload test and shock test. The device was operated within 1.172sec and activated stably under load of 45kgf. Maximum shock was measured as 18G that is much less than the pyro-separation device produces. We confirmed the possibility as a satellite separation device through above presented tests.

Development of Non-Electric and Delay-Type Explosive Bolt (비전기식 지연형 폭발볼트 개발)

  • Lee YeungJo;Kim DongJin
    • Journal of the Korean Society of Propulsion Engineers
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    • v.9 no.3
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    • pp.60-65
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    • 2005
  • The present work has developed non-electric and delay-type explosive bolt that does not need electric power supply device and has the delay function in the operation. Non-electric power supply system enables separation device system to be minimized. In order to prove the mechanism of the operation, the power of air resistance caused from aviation object used to ignite the initiator. we can be founded from the present work that the changes in the operation load influence directly the ignition of the initiator. The design of non-electric and delay type of explosive bolt is the most suitable for the separation system that is necessary to reduce the velocity of aviation object and safe landing of parachute system.

Non-Explosive Actuator Technology for Satellite Applications (인공위성용 비폭발식 분리장치 기술동향)

  • Lim, Jae-Hyuk;Kim, Kyung-Won;Kim, Sun-Won;Lee, Chang-Ho;Rhee, Ju-Hun;Hwang, Do-Soon
    • Current Industrial and Technological Trends in Aerospace
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    • v.7 no.1
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    • pp.97-104
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    • 2009
  • Successful separation of satellites from launch vehicles and release its appendages such as solar arrays and antennas are one of the most important tasks for mission accomplishment during in-orbit maneuver. Especially, specific release devices called NEA(Non-Explosive Actuator) have been widely adopted to perform safe separation and release due to its outstanding performance of low functional shock (below 500g), no contamination and easy handing as opposed to the pyroshock device. In the paper, various kinds of NEA and its history of development are reviewed along with a summary on the domestic research trend.

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Performance Verification of Separation Nut Type Non-explosive Separation Device for Cube Satellite Application (큐브위성 적용을 위한 분리너트형 비폭발식 구속분리장치 인증모델의 성능검증)

  • Oh, Hyun-Ung;Lee, Myeong-Jae
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.41 no.10
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    • pp.827-832
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    • 2013
  • Heating wire cutting type separation mechanism has been widely used for cube satellite applications due to its design constraints such as small size of $10cm{\times}10cm{\times}10cm$ and light weight of less than 1kg. In addition, usage of pyro technic device is not allowed for cube satellite application. The conventional methods have some disadvantages of relatively small mechanical constraint force and the system complexity for the multi-deployable systems. In this paper, a separation nut type non-explosive separation mechanism has been proposed and investigated. The effectiveness of the design has been verified through the qualification tests of the mechanism.

Non-explosive Low-shock Separation Device for small satellite (소형 위성용 비폭발식 저충격 분리장치)

  • Park, Hyun-Jun;Tak, Won-Jun;Han, Bum-Ku;Kwag, Dong-Gi;Hwang, Jai-Hyuk;Kim, Byung-Kyu
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.37 no.5
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    • pp.457-463
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    • 2009
  • This paper describes the development of non-explosive separation(NES) device which can be equipped on a small satellite. It comprises mechanism itself and spring-type shape memory alloy(SMA) actuator. In order to design SMA actuator properly, the necessary actuation force is measured. Based on that result, SMA actuator is designed and fabricated. Finally, SMA actuator and the proposed mechanism are integrated. In order to evaluate performance of the developed NES, we carried out a response time test, preload test and shock level test. In near future, we expect to replace the imported NES device with the developed device.

The compatible non-explosive separation device for various pre-loads using the Ni-Cr wire and Kevlar rope (다양한 사전하중에 적용할 수 있는 Ni-Cr wire와 Kevlar rope를 이용한 위성 분리장치)

  • Hwang, Hyun-Su;Kim, Byung-Kyu;Jang, Young-Keun
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.41 no.2
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    • pp.150-155
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    • 2013
  • We present a kevlar rope based Non-Explosive Actuator(NEA) device which has simple structure and is activated by burning Ni-Cr wire. Through performance test, we find it can be operated under various pre-load by simply changing turn number of Ni-Cr wire. It shows release time of 680ms and shock level of 110G under pre-load of 6.0kN. Launching environment and space environment tests are planned to verify performance of the NEA based on European Satellite Agency test manual. Conclusively, we expect the proposed NEA can be applicable to release solar panel and fairing separation.