Ascent, transition, entry, and abort guidance algorithm design for the X-33 vehicle

John Hanson, Dan Coughlin, Gregory Dukeman, John Mulqueen, James McCarter
1998 Guidance, Navigation, and Control Conference and Exhibit   unpublished
jz/-oY, One of the primary requirements for X-33 is that it be capable of flying autonomously. That is, onboard computers must be capable of commanding the entire flight from launch to landing, including cases where a single engine failure abort occurs. Guidance algorithms meeting these requirements have been tested in simulation and have been coded into prototype flight software. These algorithms must be sufficiently robust to account for vehicle and environmental dispersions, and must issue
more » ... mmands that result in the vehicle operating within all constraints. Continual tests of these algorithms (and modifications as necessary) will occur over the next year as the X-33 nears its first flight. This paper describes the algorithms in use for X-33 ascent, transition, and entry flight, as well as for the powered phase of PowerPack-out (PPO) aborts (equivalent in thrust impact to losing an engine). All following discussion refers to these phases of flight when discussing guidance. The paper includes some trajectory results and results of dispersion analysis to demonstrate the technologies necessary to develop the Reusable Launch Vehicle (RLV), eventually replacing the Space Shuttle. The X-33 has the capability to launch vertically, achieve Mach 11, shutdown
doi:10.2514/6.1998-4409 fatcat:gsxcl6jsofhcjhudv7gjaqlfd4