| タイトル | Predictor-Corrector Entry Guidance for Reusable Launch Vehicles |
| 本文（外部サイト） | http://hdl.handle.net/2060/20010067392 |
| 著者（英） | Youssef, Hussein; Brandon, Larry; Zimmerman, Curtis; Chowdhry, Rajiv; Lee, Howard |
| 著者所属（英） | NASA Marshall Space Flight Center |
| 発行日 | 2001-01-01 |
| 言語 | eng |
| 内容記述 | An online entry guidance algorithm has been developed using a predictor-corrector approach. The algorithm is designed for the Reusable Launch Vehicle (RLV) and is demonstrated by using, the X-33 model. The objective of the design is to handle widely dispersed entry conditions and deliver the vehicle at the Terminal Area Energy Management (TAEM) interface box within an acceptable tolerance and without violating any of the vehicle physical constraints. Combination of several control variables is used in testing the performance and computational requirement of the algorithm. The control variables are the bank angle, angle-of-attack and the time for roll reversal. The bank angle and angle-of-attack profiles are the nominal profiles plus the perturbations in each direction. The initial guess of the bank profile is a 45 degrees bank angle with reversal at 360 seconds from liftoff. A six-element state vector is propagated to the TAEM interface box through the integration of the equations of motion (EOM). Altitude, heading and range errors are computed between the desired and the achieved state at the TAEM interface. These errors are used to correct the initial guess of the control variables. This process is repeated until the errors meet an acceptable level at the TAEM interface. Several numerical optimization methods are used to evaluate the convergent property of the predictor-predictor methodology. Successful results are demonstrated using the X-33 model. |
| NASA分類 | Launch Vehicles and Launch Operations |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/226106 |
