A B C D E F G H I J K L M N O P Q R S T U V W X Y Z All
Krishnadasan, C. K.
- An End-To-End Airframe Structural System Design
Authors
1 Vikram Sarabhai Space Centre/Indian Space Research Organization, Thiruvananthapuram 695 022, IN
Source
Current Science, Vol 114, No 01 (2018), Pagination: 123-130Abstract
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.Full Text
References
- 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.
- Structural Design, Qualification and Post-Flight Assessment of Crew Module Fairing
Authors
1 Structural Engineering Entity, Vikram Sarabhai Space Centre, Thiruvananthapuram 695 022, IN
Source
Current Science, Vol 120, No 1 (2021), Pagination: 129-140Abstract
Crew Module Fairing (CMF) for Pad Abort Test (PAT) of Crew Escape System (CES) is configured and designed with the objective of flight qualifying necessary features like external aerodynamic shape, thermal protection system, along with Escape Motors (namely Low-altitude Escape Motor (LEM) and Highaltitude Escape Motor (HEM)), with interfaces simulated as in actual flight. For improving the aerodynamic stability of the vehicle, four grid fins are attached at the aft end of CMF. Interfaces for mounting LEM, HEM, grid fins along with its deployment mechanisms and Crew Module through CM–CES attachment have been provided on CMF.
The design was supported by rigorous analysis, both 2D as well as 3D, of different sub-assemblies and interface joints for the respective critical load cases. To meet the challenges of launch requirements and schedule, the feasibility of combining tests of varying nature has been explored. By meticulous planning of the test scheme, set-up, load cases and instrumentation, and through a judicious combination of test and analysis, structural qualification of CMF could be achieved meeting the mission schedule. CMF has been successfully flown in PAT, as evident from radar monitoring. Post-flight analysis of strain data indicates the integrity and good health of CMF during the entire phase of the mission.
Keywords
Aerodynamic Stability, Crew Module Fairing, Grid Fins, Pat Abort Test.Full Text
References
- Isogrid Design Handbook, NASA CR-124075, February 1973.
- Analysis and Design of Flight Vehicles Structure, E. H. Bruhn.
- Shigley’s Mechanical Engineering Design, 8th edition.