Passive Thermal Management of Launch Vehicle Systems using Phase Changing Materials

  • Vijay Kumar Sen Vikram Sarabhai Space Centre (VSSC), Indian Space Research Organization (ISRO)
  • Janmejay Jaiswal Vikram Sarabhai Space Centre (VSSC), Indian Space Research Organization (ISRO)
  • Amarnath Nandi Vikram Sarabhai Space Centre (VSSC), Indian Space Research Organization (ISRO)
  • Aliyas Areeckal Varkey Vikram Sarabhai Space Centre (VSSC), Indian Space Research Organization (ISRO)
  • Aravindakshan Pillai Vikram Sarabhai Space Centre (VSSC), Indian Space Research Organization (ISRO)
Keywords: Hybrid heat sink, Thermal inertia, Phase changing materials, Fins, Transient thermal response

Abstract

Electronic systems in expendable launch vehicles and missiles rely on their own thermal inertia to operate for the stipulated time, without overheating, owing to absence of active cooling systems and natural convection at elevated altitude. Traditionally, this inertia is built-into the electronics by increasing its chassis (support structure) mass, proportional to the associated thermal load. For power intensive systems, especially in vehicle upper stages where mass is at premium, this approach results in reduction in payload capability. In the proposed paper, a Heat Sink based on Neopentyl Glycol (NPG) with solid-to-solid phase change (crystalline transformation) is explored as a mass effective alternative due to the material’s capability to absorb a significant amount of energy during phase change. However, due to its lower thermal conductivity, a Thermal Conductivity Enhancer (TCE) to maximize heat transfer had to be employed. The resulting heat sink, utilizing TCE for heat transfer capability and NPG for heat storage capability is called as Hybrid Heat Sink. A heat sink with plate type fins as TCE is realized and a mass reduction factor of 1.4 is achieved against traditional approach. This is followed by a heat sink with pin type fins as TCE where mass reduction factor is increased to 2.6. Effect of thermal cycling and vibration on its performance is also studied.

Author Biographies

Vijay Kumar Sen, Vikram Sarabhai Space Centre (VSSC), Indian Space Research Organization (ISRO)
Mr V.K. Sen received his BTech (Mechanical Engineering) from Himachal Pradesh University, Shimla. Presently involved in structural and thermal design in Avionics Mechanical Fabrication Facility, Vikram Sarabhai Space Centre, Trivandrum.
Janmejay Jaiswal, Vikram Sarabhai Space Centre (VSSC), Indian Space Research Organization (ISRO)
Mr J. Jaiswal received his BTech (Aerospace Engineering) from Indian Institute of Space Science and Technology, Trivandrum. Presently involved in structural and thermal design in Avionics Mechanical Fabrication Facility, Vikram Sarabhai Space Centre, Trivandrum.
Amarnath Nandi, Vikram Sarabhai Space Centre (VSSC), Indian Space Research Organization (ISRO)
Mr A. Nandi received his BE (Mechanical Engineering) from North Bengal University, West Bengal. Presently heads the structural and thermal design section in Avionics Mechanical Fabrication Facility, Vikram Sarabhai Space Centre, Trivandrum.
Aliyas Areeckal Varkey, Vikram Sarabhai Space Centre (VSSC), Indian Space Research Organization (ISRO)
Mr A.V. Aliyas received his BTech in Mechanical Engineering from N.S.S. College of Engineering, Calicut University. Presently heads Avionics Mechanical Fabrication Facility, Vikram Sarabhai Space Centre, Trivandrum.
Aravindakshan Pillai, Vikram Sarabhai Space Centre (VSSC), Indian Space Research Organization (ISRO)
Mr A. Pillai received his BTech (Mechanical Engineering) from N.S.S. College of Engineering, Calicut University and ME (Mechanical Engineering) from Indian Institute of Science, Bangalore. Presently the Group Head of Propulsion and Plasma Research Group, Vikram Sarabhai Space Centre, Trivandrum.
Published
2018-06-26
How to Cite
SenV., JaiswalJ., NandiA., VarkeyA., & PillaiA. (2018). Passive Thermal Management of Launch Vehicle Systems using Phase Changing Materials. Defence Science Journal, 68(4), 337-342. https://doi.org/10.14429/dsj.68.10433
Section
Aeronautical Systems