Jang, Jiann-Woei Alaniz, Abran Hall, Robert Bedossian, Nazareth Hall, Charles Jackson, MarkĪ launch vehicle represents a complicated flex-body structural environment for flight control system design. Each of these control center architectures have similarities in basic structure, and differences in functional distribution of responsibilities for the phases of operations: (a) Launch vehicles in the international community vary greatly in configuration and process (b) Each launch site has a unique processing flow based on the specific configurations (c) Launch and flight operations are managed through a set of control centers associated with each launch site, however the flight operations may be a different control center than the launch center and (d) The engineering support centers are primarily located at the design center with a small engineering support team at the launch site.ĭesign of Launch Vehicle Flight Control Systems Using Ascent Vehicle Stability Analysis Tool This analysis is a survey of control center architectures of the NASA Space Launch System (SLS), United Launch Alliance (ULA) Atlas V and Delta IV, and the European Space Agency (ESA) Ariane 5. Epps, Amy Woodruff, Van Vachon, Michael Jacob Monreal, Julio Williams, Randall McLaughlin, Tom Launch Vehicle Control Center Architectures Envelope expansion and robustness enhancement is obtained through the use of a multiplicative forward gain modulation law based upon a simple model reference adaptive control scheme. The architecture supports active in-flight disturbance compensation through the use of nonlinear observers driven by acceleration measurements.

The algorithm also relies on a pseudo-optimal control allocation scheme to maximize the performance capability of multiple vectored engines while accommodating throttling and engine failure contingencies in real time with negligible impact to stability characteristics. The SLS flight control architecture combines a digital three-axis autopilot with traditional bending filters to support robust active or passive stabilization of the vehicle's bending and sloshing dynamics using optimally blended measurements from multiple rate gyros on the vehicle structure. The present design concept is intended to leverage existing NASA and industry launch vehicle design experience and maintain the extensibility and modularity necessary to accommodate multiple vehicle configurations while relying on proven and flight-tested control design principles for large boost vehicles. It was recognized early in the program that a new, generalized autopilot design should be formulated to fulfill the needs of this new space launch architecture. The SLS configurations represent a potentially significant increase in complexity and performance capability when compared with other manned launch vehicles. Hall, Charles E.Ī robust and flexible autopilot architecture for NASA's Space Launch System (SLS) family of launch vehicles is presented. Space Launch System Ascent Flight Control Design

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