Designing the terminal guidance algorithm of a typical air-launched launch vehicle

Document Type : Research Paper

Authors

1 Assistant Professor / Faculty of Aerospace Engineering, Malek Ashtar University of Technology

2 Malek Ashtar University

3 Department faculty university Graduated Malek Ashtar.

Abstract

Generally, the guidance and the control are designed as separate modules, which are suitable for many common and normal applications, but in order to achieve less error in deploying the satellite into the orbit increase the accuracy in performing the mission, we need to develop integrated Guidance and Control algorithms (IGC). By using such algorithms, it is possible to design the closed loop guidance for the last stage of the launch vehicle in vacuum condition. Examples of this are iterative guidance mode (IGM) and power explicit guidance (PEG). In this paper, the guidance of the final phase along with the guidance of the first and second stages of a typical solid rocket launch vehicle is modeled and simulated. The results of this article show that the IGM guidance can be well compatible with the Pitch Program guidance of the previous steps and successfully complete the deployment in the orbit.

Keywords

Main Subjects

References

[1]  M. Aelaei, F.Ommi, and Karimian S. Accuracy Evaluation of Semi-empirical and Numerical Methods in Estimation of Aerodynamic Coefficients for air-launch-to-orbit delta wing (in Persian), Modarres Mechanical Engineering, Vol. 17, No. 9, pp. 207-216, 2017 (in persian)
[2] P. Bartolotta, W. Alan, S. Mark, T. Randall, Voland, and Larry H., Horizontal Launch:A Versatile Concept for Assured Space Access, 2011.
[3] D. F. Lawden, optimal rocket trajectories, Jet propulsion 27, 1263, December 1957.
[4] R. Battin, Space Guidance Evolution, A Personal Narrative, Journal of Guidance, Control and Navigation, March-April 1982.
[5] D. C. Chandler, I..E. Smith, Development of the Iterative Guidance Mode with Its Application to Various Vehicles and Missions" Journal of Spasecraft and Rockets 4: 898-903, 1967.
[6] H. J. Horn and D.C. Chandler and V. L. Buckelew Iterative Guidance Mode to Generalized Missions. Journal of Spacecraft and Rocket 6 page 4-8, 1969.
[7] Z. Qian and Zhi and Bei H. X. A Guidance Scheme for Air-Launched Solid Launch Vehicle. 21st AIAA International Space Planes and Hypersonic Technologies Conference. Xiamen. March 2017.
[8] S. Turabi, J. Roshniyan and H. Arabshahi, "Online design of optimal integrated guidance and control algorithm for a Launch Vehicle," JSST, volume 8, number 2, pp. 67-78, (in persian)
[9] A. Mohammadi, M. Taeifi and c. Roshnian, "Integration of presetting methods and IGM in the guidance of Launch Vehicles," in the 8th annual conference of the Iran Aerospace Society, Isfahan, 2017.pp. 67-78, (in persian)
[10] M. M. Saatian, V. N. Baranov, Design and application of multi-stage terminal guidance system in satellite rocket, The 5th national conference and the second international conference of Iran Aerospace Association, Tehran, 2003 (in persian)

Files

Share

How to cite

Statistics