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An End-To-End Airframe Structural System Design


Affiliations
1 Vikram Sarabhai Space Centre/Indian Space Research Organization, Thiruvananthapuram 695 022, India
 

Design of aerospace reusable launch vehicle (RLV) structures offers diverse challenges due to stringent specifications in geometry, structural mass, integrity for thermal protection system and interfaces with propulsion, avionics and power systems. Airframe structures for RLVs should cater to the specified strength, stiffness and stability, and meet the functional and integration requirements of aerospace vehicles. To address these challenges, an integrated design cycle comprising load estimation, layout design, torsion box analysis and sizing of structural components is devised and presented. Verification of structural design is done by structural and thermo-structural analyses of the integrated airframe. Qualification of the airframe by integrated airframe test, thermo-structural test and acoustic test is also discussed.

Keywords

Airframe Structure, Integrated Design Cycle, Reusable Launch Vehicle, Thermal Protection System.
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  • Niu, M. C. Y., Airframe Structural Design, Hong Kong Conmilit Press Ltd, 1988.
  • Bruhn, E. F., Analysis and Design of Flight Vehicle Structures, Jacobs Publishers, 1973.

Abstract Views: 327

PDF Views: 132




  • An End-To-End Airframe Structural System Design

Abstract Views: 327  |  PDF Views: 132

Authors

B. P. Deepak
Vikram Sarabhai Space Centre/Indian Space Research Organization, Thiruvananthapuram 695 022, India
T. Manojkumar
Vikram Sarabhai Space Centre/Indian Space Research Organization, Thiruvananthapuram 695 022, India
A. Prashanthan
Vikram Sarabhai Space Centre/Indian Space Research Organization, Thiruvananthapuram 695 022, India
R. Suresh
Vikram Sarabhai Space Centre/Indian Space Research Organization, Thiruvananthapuram 695 022, India
Philip K. Mathew
Vikram Sarabhai Space Centre/Indian Space Research Organization, Thiruvananthapuram 695 022, India
M. I. Junaidh
Vikram Sarabhai Space Centre/Indian Space Research Organization, Thiruvananthapuram 695 022, India
S. Rajendran
Vikram Sarabhai Space Centre/Indian Space Research Organization, Thiruvananthapuram 695 022, India
B. S. Raju
Vikram Sarabhai Space Centre/Indian Space Research Organization, Thiruvananthapuram 695 022, India
C. K. Krishnadasan
Vikram Sarabhai Space Centre/Indian Space Research Organization, Thiruvananthapuram 695 022, India

Abstract


Design of aerospace reusable launch vehicle (RLV) structures offers diverse challenges due to stringent specifications in geometry, structural mass, integrity for thermal protection system and interfaces with propulsion, avionics and power systems. Airframe structures for RLVs should cater to the specified strength, stiffness and stability, and meet the functional and integration requirements of aerospace vehicles. To address these challenges, an integrated design cycle comprising load estimation, layout design, torsion box analysis and sizing of structural components is devised and presented. Verification of structural design is done by structural and thermo-structural analyses of the integrated airframe. Qualification of the airframe by integrated airframe test, thermo-structural test and acoustic test is also discussed.

Keywords


Airframe Structure, Integrated Design Cycle, Reusable Launch Vehicle, Thermal Protection System.

References





DOI: https://doi.org/10.18520/cs%2Fv114%2Fi01%2F123-130