Hostname: page-component-745bb68f8f-grxwn Total loading time: 0 Render date: 2025-02-11T15:33:25.808Z Has data issue: false hasContentIssue false
  • English
  • Français

Study on shock reduction during pyro-actuated separation mechanism by use of shock absorbers and dampers

Published online by Cambridge University Press:  06 February 2025

A. Chakraborty Open the ORCID record for A. Chakraborty [Opens in a new window] ,
D. Laxman ,
R. Srinivasan ,
S.A. Khalane ,
P.A. Ramakrishna  and
H. Murthy
A. Chakraborty*
Affiliation:
Advanced Systems Laboratory, Defence Research and Development Organisation, Kanchanbagh, Hyderabad, India
D. Laxman
Affiliation:
Advanced Systems Laboratory, Defence Research and Development Organisation, Kanchanbagh, Hyderabad, India
R. Srinivasan
Affiliation:
Advanced Systems Laboratory, Defence Research and Development Organisation, Kanchanbagh, Hyderabad, India
S.A. Khalane
Affiliation:
Advanced Systems Laboratory, Defence Research and Development Organisation, Kanchanbagh, Hyderabad, India
P.A. Ramakrishna
Affiliation:
Department of Aerospace Engineering, Indian Institute of Technology Chennai, Chennai, India
H. Murthy
Affiliation:
Department of Aerospace Engineering, Indian Institute of Technology Chennai, Chennai, India
*
Corresponding author: A. Chakraborty; Email: [email protected]
Get access Rights & Permissions [Opens in a new window]

Abstract

The current emphasis in aerospace component development is on creating safe, reliable and cost-effective technologies. However, the intricate design of stage separation systems renders component reliability a critical factor in determining mission success or failure. One of the technical challenges involves the development of various aerospace mechanisms, such as payload separation, heavy propulsion system separation, ejection of auxiliary components and detachment of rigid components. These stage separation mechanisms commonly employ pyrotechnic devices, which, by their operational nature, impart shock to the spacecraft, potentially causing damage or adverse effects on flight instruments. Therefore, it is imperative to explore multiple viable concepts aimed at reducing shock and experimentally ascertain the impact of shock using diverse shock attenuation techniques. While existing literature primarily addresses shock attenuation with distance from the shock source, limited attention has been given to diminishing shock at the location of the shock-generating element. This study employed various shock-attenuating devices, including dampers, metallic foam structures, viscous materials and dampeners, to assess the effectiveness of shock reduction. Furthermore, the study investigated shock reduction resulting from the elimination of rigid connections, such as bolted joints, from pyro-actuated mechanisms. Through a series of experiments, a conclusive analysis was conducted to determine the approach for achieving a substantial reduction in pyro shock.

Keywords

pyro shockseparation mechanismshock absorberspyro device
Type
Research Article
Information
The Aeronautical Journal , First View , pp. 1 - 21
Check for updates
Copyright
© The Author(s), 2025. Published by Cambridge University Press on behalf of Royal Aeronautical Society

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

C J. Pyrotechnic Shock Failures, IES Pyrotechnic Shock Tutorial Program, 31st ATM, Institute of Environmental Science, 1985.Google Scholar
Moening, C.J. Views of the world of pyrotechnic shock, Shock Vibr. Bull., 1986, 56, (3), pp 3–28.Google Scholar
Isakowitz, S., Hopkins, J. Jr. and Hopkins, J. International Reference Guide to Space Launch Systems, 4th ed, American Institute of Aeronautics and Astronautics, Inc, 2004.Google Scholar
Pyro Shock Test Criteria. NASA Technical Standard, NASA-STD-7003, USA, 2011.Google Scholar
Babuska, V., Gomez, S., Smith, S. and Hammetter, C. Spacecraft pyro shock attenuation in three parts, J. Am. Inst. Aeronaut. Astronaut. (p. 0633) 2016. https://doi.org/10.2514/6.2017-0633 Google Scholar
Lee, D.-O., Han, J.-H., Jang, H.-W., Woo, S.-H. and Kim, K.-W. Shock response prediction of a low altitude earth observation satellite during launch vehicle separation, Int’l J. Aeronaut. Space Sci., 2010.CrossRefGoogle Scholar
Graham, J.A. Separation system with shock attenuation. Patent No. US 8,727,654 B2, 2014.Google Scholar
Suresh, B.N. and Sivan, K. Stage auxiliary systems, in Integrated Design for Space Transportation System, 2015, pp 539–580, Chapter 12.CrossRefGoogle Scholar
Naga Sreenivasa Rao, Y., Prakash, P., Subramanian, U.A., Purushothaman, P., Premdas, M., Abraham, B., Kishorenath, V. and Jayachandran, T. Development of RLV-TD stage separation system, J. Inst. Eng. (India): Ser. C, 2017, 98, pp 669–678.Google Scholar
Youn, S.-H. Development of a three-axis hybrid mesh isolator using the pseudoelasticity of a shape memory alloy, Smart Mater. Struct., 2011, 20, pp 1-–12.CrossRefGoogle Scholar
Ming, J., Qianguang, X., Liqiang, T. and Xinbo, S. Experimental study on vibration and shock characteristics of Metal rubber damper, Reliab. Environ. Exp. Electron. Devices, 2012, 30, (2), pp 49–57.Google Scholar
Winfree, N.A. and Hyunchul Kang, J. Mechanical filter for sensors. Patent No. US7706213 B2, 2010-04-27, 2010.Google Scholar
Huan, Z., Tianxiong, L., Shuhong, X., Changjiang, L. and Qingming, Z. Spacecraft pyro shock protecting techniques, Spacecraft Environ. Eng., 2014, 2.Google Scholar
Park, H.-S., Hwang, D.-H., Han, J.-H. and Yang, J. Development of shock absorbing insert for honeycomb sandwich panel, J. Aerospace Sci. Technol., 2020.CrossRefGoogle Scholar
Lee, J., Hwang, D.-H. and Han, J.-H. Study of pyro shock propagation through plates with joints and washers, J. Aerospace Sci. Technol., 2018.CrossRefGoogle Scholar
Gao, W., Qin, Z. and Chu, F. Theoretical and experimental studies on pyroshock attenuation via periodic rods, J. Am. Inst. Aeronaut. Astronaut., 2021.Google Scholar
Laughlin, P.J. Non-explosive tension release actuator. European Patent Application EP 2 848 538 A1, 18.03.2015, 2015.Google Scholar
Floyd, B. and Owens, J. Gas Strut Separation Alternative for Ares I. Proceedings of the 39th Aerospace Mechanisms Symposium, NASA Marshall Space Flight Center, 2008.Google Scholar
Floyd, B.A. Gas Strut Separation for Staged Rocket. Patent No. US 8,783,026 B2, 22, 2014.Google Scholar
Chakraborty, A., Rathi, N., Srinivasan, R., Khalane, S.A., Ramakrishna, P.A. and Murthy, H.S.N. Reduction of pyro shock in stage separation mechanism by use of gas generator systems, Int. J. Energetic Mater. Chem. Propul., 2022, 21, (4), pp 1–15.CrossRefGoogle Scholar
Seeholzer, T.L., Smith, F.Z., Eastwood, C.W., Steffes, P.R. Application Catalog of Pyrotechnically Actuated Devices/Systems, NASA Technical Memorandum 106810, 1995.Google Scholar
Chang, K.Y. Pyrotechnic devices, shock levels and their applications, Presented at Pyroshock Seminar, ICSV9, 2002.Google Scholar
Bateman, V.I., Himelblau, H. and Merritt, R. Validation of pyroshock data. Sound and vibration, J. IEST, 2012, 55, pp 40–56.CrossRefGoogle Scholar
Cebrian, A.S., Halter, B.-U. and Gerngross, T. RUAG’s approach to develop a modular low shock separation and jettison system, 8th European Conference for Aeronautics and Space Sciences (EUCASS), 2019.Google Scholar
Space Vector, Separation system brochure. https://spacevector.com/downloads/brochures/Sep_Systems_Brochure.pdf Google Scholar