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Integrated Electrohydraulic Control Actuation System with Centralized Power Plant for the Reusable Launch Vehicle Technology Demonstrator


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

An electrohydraulic control actuation system for actuating eight aerodynamic control surfaces of the two-stage technology demonstrator of the Indian reusable launch vehicle (RLV-TD) was developed, validated by extensive testing in various test beds, simulation runs and flight proven in the RLV-TD HEX-01 mission flight on 23 May 2016. A centralized hydraulic power generating unit (HPU) was used for powering the eight actuators located in two stages. The network of plumbings and control components of this actuation system were required to be laid out over the entire length and breadth of the vehicle measuring 17 m in length, to distribute the hydraulic power to all the actuators. The hydraulic actuation system had to work for the longest ever duration of 833 s for an Indian launch vehicle. Many challenges arose due to a single HPU for two stages, long complex network of plumbings, longest ever operating duration, thermal issues, second-stage structure resembling an aircraft, limited occupancy for operations at the launch pad, limited power source, etc. Necessary provisions were incorporated in the design to successfully overcome them. This article describes the development of the control actuation system.

Keywords

Aerodynamic Control Surfaces, Control Electronics, Electrohydraulic Actuation System, Hydraulic Power Unit, Servo Design.
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  • Merritt, H. E., Hydraulic Control Systems, John Wiley, New York, USA, 1967.

Abstract Views: 383

PDF Views: 134




  • Integrated Electrohydraulic Control Actuation System with Centralized Power Plant for the Reusable Launch Vehicle Technology Demonstrator

Abstract Views: 383  |  PDF Views: 134

Authors

V. Masilamani
Vikram Sarabhai Space Centre, Indian Space Research Organization, Thiruvananthapuram 695 022, India
Manoj Kumar
Vikram Sarabhai Space Centre, Indian Space Research Organization, Thiruvananthapuram 695 022, India
S. Sankar Narayan
Vikram Sarabhai Space Centre, Indian Space Research Organization, Thiruvananthapuram 695 022, India
N. Raghu
Vikram Sarabhai Space Centre, Indian Space Research Organization, Thiruvananthapuram 695 022, India
M. N. Namboodiripad
Vikram Sarabhai Space Centre, Indian Space Research Organization, Thiruvananthapuram 695 022, India
T. Mookiah
Vikram Sarabhai Space Centre, Indian Space Research Organization, Thiruvananthapuram 695 022, India

Abstract


An electrohydraulic control actuation system for actuating eight aerodynamic control surfaces of the two-stage technology demonstrator of the Indian reusable launch vehicle (RLV-TD) was developed, validated by extensive testing in various test beds, simulation runs and flight proven in the RLV-TD HEX-01 mission flight on 23 May 2016. A centralized hydraulic power generating unit (HPU) was used for powering the eight actuators located in two stages. The network of plumbings and control components of this actuation system were required to be laid out over the entire length and breadth of the vehicle measuring 17 m in length, to distribute the hydraulic power to all the actuators. The hydraulic actuation system had to work for the longest ever duration of 833 s for an Indian launch vehicle. Many challenges arose due to a single HPU for two stages, long complex network of plumbings, longest ever operating duration, thermal issues, second-stage structure resembling an aircraft, limited occupancy for operations at the launch pad, limited power source, etc. Necessary provisions were incorporated in the design to successfully overcome them. This article describes the development of the control actuation system.

Keywords


Aerodynamic Control Surfaces, Control Electronics, Electrohydraulic Actuation System, Hydraulic Power Unit, Servo Design.

References





DOI: https://doi.org/10.18520/cs%2Fv114%2Fi01%2F84-100