An Alternative Entry Guidance Algorithm for Suborbital Launch Vehicle
- Paper number
IAC-08.C1.5.8
- Author
Mr. Xiaodong Yan, China
- Coauthor
Prof. Shuo Tang, China
- Coauthor
Mrs. Guihua Ma, China
- Year
2008
- Abstract
Entry guidance is primary for SLV‘s (Suborbital Launch Vehicle) return to the landing site in safety. The paper presents entry guidance algorithms for SLV, which involves entry trajectory design and tracking law design. Entry trajectory was divided into initial descent phase and transition phase according to the prominence of aerodynamics forces. At the initial descent phase, constant bank angle was employed. At the transition phase, desired height vs. velocity profile was built by a 4th order polynomial, and constraint boundaries were derived through denoting constraints to height vs. velocity space. Coefficients of the polynomial were obtained by meeting the constraints boundaries. Finally, the desired nominal trajectory was achieved after modulating range error to null. Tracking law is obtained via feedback linearization. This tracking law is shown to achieve bounded tracking of the output variables. The simulation results indicates that the guidance algorithm is effectiveness for entry of SLV.
- Abstract document
- Manuscript document
(absent)