Investigation of Wire Diameter of Helical Compression Spring for Payload Separation

Shandi Prio Laksono


The payload is designed to be separated from rocket at an altitude over 100 km.  One of critical component in the payload separation system is the helical compression spring. The helical compression spring ensures safe release the payload. The spring must satisfy some parameters such as static failure and buckling, also spring has enough energy storing to release the payload during launch. The objective of this paper is to do investigation of wire diameter of helical compression spring which can be used in the payload separation system of sounding rocket based on several constraints. The results obtained show that with payload weight of 60 kg, minimum wire diameter should be 8 mm with mean coil diameter of 80 mm. The maximum separation velocity of 1.76 m/swas obtained by using wire diameter of 8 mm and mean coil diameter of 96 mm.

Full Text:



Li, J., Yan, S., & Tan, X. Dynamic-Envelope Analysis of Clamp-Band Joint Considering Pyroshock of Satellite Separation Journal of Spacecraft and Rocket Volume 51, No. 5. | DOI: 10.2514/1.A32382

Liu, Y., Li, Z., Sun, Q., Fan, X., & Wang, W. (2012). Separation dynamics of large-scale fairing section: A fluid–structure interaction study. Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering.

Samani, M., & Pourtakdoust, S.H. (2014). Analysis of Two - Stage Endo - Atmospheric Separation Using Statistical Methods. Journal of Theoretical and Applied Mechanics 52,4, pp.1115-1124.

Abe, T., Nakamura, M., Ishii, N., & Inatani, Y. (2009). Recent Activities and Future Direction of Japanese Sounding Rocket Experiments for Scientific Purpose. Proc. 19th ESA Symposium on European Rocket and Balloon Programmes and Related Research.

Inatani, Y., Ishii, N., Nonaka, S., & Abe, T. (2016). Recent Activities of Sounding Rocket and Ballooning in Japan. International Seminar on Aerospace Science and Technology IV.

Hu, X., Chen, X., Zhao, Y., & Yao, W. (2014). Optimization design of satellite separation systems based on Multi-Island Genetic Algorithm. Advances in Space Research 53 pp 870-876.

Hu, H., Wang, J., & Lu, W.J. (2008). Simulation and Analysis of Fairing Jettison from Sounding Rocket. Journal of Aeronautics, Astronautics and Aviation, Series A, Volume 40, No.4, pp.237 -244.

Kolawole, S.O., Adewale, H., & Christian, O. (2018). Optimal Helical Spring Design for a P-Pod Using Chaotic Backtrack Search Algorithm. International Journal of Scientific & Engineering Research Volume 9, Issue 8.

Tayefi, M., & Ebrahimi, M. (2009). Design and Analysis of Separation Systems Based on an Optimization Approach. 47th AIAA Aerospace Sciences Meeting Including The New Horizons Forum and Aerospace Exposition.

Sawanobori, T., Akiyama, Y., Tsukaharat, T., & Nakamura, M. (1985). Analysis of Static and Dynamic Stresses in Helical Spring. Bulletin of Japan Society of Mechanical Engineers, Volume 28, No. 238.

Hu, X., Chen, X., Tuo, Z., & Zhang, Q. (2012). Dynamics and transient perturbation analysis of satellite separation systems. In: Proc. ImechE Part G: J. Aerospace Eng. doi: 10.1177/0954410012466780.

Chary, C.K., & Reddy, S. (2016). Design and Analysis of Helical Compression Spring of IC Engine. International Advanced Research Journal in Science, Engineering and Technology (IARJSET). Volume 3, Issue 10.

Pattar, S., Sanjay, S.J., & Math.V.B. (2014). Static Analysis of Helical Compression Spring. International Journal of Research in Engineering and Technology (IJRET), pp. 835-838.

Budynas, R.G., Nisbett, J.K, & Shigley, J.E. (2008). Shigley’s Mechanical Engineering Design 8th Edition. McGraw-Hill.


  • There are currently no refbacks.