Advertisement

Attitude Determination of a Powered Launch Vehicle Stage with Conventional Satellite Sensors

  • K. Harendra Nath
  • A. S. Ganeshan
  • K. K. Achary
  • S. C. Rathanakara
Conference paper
Part of the Astrophysics and Space Science Library book series (ASSL, volume 127)

Abstract

One of the main objectives of the first of the Stretched Rohini Satellite series SROSS-1, planned to be put into a 400 km near circular orbit by ASLV, is to assess the performance of the last stage of the launch vehicle. The inertial measurement unit (IMU) which provides the attitude information from lift-off will be separated from the last stage at the end of AS3 long coast. Hence, no further information of attitude of the fourth stage boost phase will be available through the IMU. In ASLV-SROSS-1 mission, it is proposed to determine and study the behaviour of the attitude of the composite (last stage of ASLV and SROSS) using horizon sensors, magnetometer and sun sensor, put together called the ALPHA package, housed on the satellite. Additionally, a single accelerometer along the longitudinal axis of the composite is also proposed to meet the objective. The methodology proposed here is a point-to-point coupled trajectory reconstruction using the sensor and velocity encoder data. Typical data of sensors and velocity encoder have to be generated so that a real life situation can be evolved for testing the near real time software required for attitude determination of the last stage powered flight. The behaviour of the composite during the AS4 boost phase with dynamic imbalance and thrust misalignment is a complex phenomenon which warrants a detailed simulation exercise.

Keywords

Inertial Measurement Unit Body Frame Attitude Determination Velocity Encoder Translational Equation 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

Preview

Unable to display preview. Download preview PDF.

Unable to display preview. Download preview PDF.

References

  1. Adimurthy and Ganeshan: 1983, Launch Vehicle Dynamics.Google Scholar
  2. Ganeshan et al.:l979a, PEGASUS — A mini Computer Program for Launch Vehicle Simulation Under Ideal Control Mode.Google Scholar
  3. Ganeshan et al.: 1979b, Cygnus — A Real Time Hybrid Computer Trajectory Program on Actual Control Mode.Google Scholar
  4. Ganeshan et al.:1980, Trajectory Simulation Program for Multi-Engine Configuration Vehicles.Google Scholar
  5. Caneshan, and Rathanakara: 1985, Composite Simulation and Near Real Time Trajectory Reconstruction.Google Scholar
  6. Ghosh,and Ganeshan: 1979, Determination of Velocity Increment During Stage 4 Thrust Phase Using Velocity Encoder.Google Scholar
  7. Harendra Nath,and Achary : 1985a, SROSS-1 Mission Software:Attitude DeterminationGoogle Scholar
  8. Harendra Nath, and Achary : 1985b, SROSS-1 Attitude Determination for Composite Phase and Spin Phase.Google Scholar
  9. Jayaraman et al.: 1982, Frames of Reference for Launch Vehicle Trajec-tory Simulation.Google Scholar
  10. Shivananda, and Ganeshan,A.S.: 1983, Preliminary Report on Composite Attitude Determination and Stage Performance Evaluation.Google Scholar
  11. Vasagam Committee: 1983, Report of the Selection Committee on the Choice of Payload for the First ASLV/SROSS Mission.Google Scholar

Copyright information

© D. Reidel Publishing Company 1986

Authors and Affiliations

  • K. Harendra Nath
    • 1
  • A. S. Ganeshan
    • 1
  • K. K. Achary
    • 1
  • S. C. Rathanakara
    • 1
  1. 1.Mission Planning and Development GroupISRO Satellite CentreBangaloreIndia

Personalised recommendations