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Meeting	ACGS Committee Meeting 100 - Cocoa Beach - October 2007
Agenda Location	7 SUBCOMMITTEE A – AERONAUTIC AND SURFACE VEHICLES 7.3 Autonomous Flight Safety – Onboard Flight Termination System
Title	Autonomous Flight Safety – Onboard Flight Termination System
Presenter	Michelle Amos
Affiliation	Kennedy Space Center
Available Downloads*	presentation
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Abstract	The Autonomous Flight Safety System (AFSS) is a joint NASA WFF/KSC project to develop an autonomous on-board range safety system that can augment or replace the functions of the traditional human-in-the-loop system. Redundant AFSS processors evaluate data from onboard Global Positioning System (GPS) and inertial navigation unit (IMU) navigation sensors: configurable rule-based algorithms are used to make flight termination decisions. The mission rules are developed by the local Range Safety Authorities using the inventory of rule types taken from current human-in-the-loop operational flight safety practices. AFSS is most applicable for small expendable launch vehicles (ELV’s) and is particularly attractive where conventional systems for range coverage are prohibitively expensive and/or difficult. AFSS also has potential applications as a crew advisory system for manned flights and as an adjunct and training tool for traditional human-based flight termination systems. The main benefit of the AFSS is to decrease the need for permanent ground-based range safety assets with a corresponding savings in operational costs and to increase the number of potential launch sites and corridors. The ultimate goal of this project is to produce a certified automonous flight safety system that may be licensed to industry for production. OSMA at NASA/HQ realizes the benefits of AFSS and continues to provide basic project funding. DARPA's involvement has provided funds and vital test flight opportunities. The joint partnership between WFF and KSC provides a unique partnership in skills, capabilities (WFF with sounding rocket and rapid hardware development and KSC with software development and larger vehicle experience), and cost sharing that overcome many scheduling and labor issues. The AFSS testing and development philosophy is a graduated approach emphasizing bench tests and flight tests of incremental system changes with available resources and clearly defined objectives. Data from each test is carefully analyzed and used to identify the current system’s performance and any issues that need to be resolved before changes are made. AFSS is in its third phase. Phase I was a one-year feasibility demonstration in 2000. Phase II was a one-year Bench Prototype demonstration in 2002 that resulted in simulation testing of various failure modes. Phase III began in 2003 with the goal of producing a flight qualifiable unit with new configurable rule-based algorithms. Phase III has produced new algorithms and a redundant hardware design. During 2005, there was the first moving ground test on a van and the first aircraft test. These tests were successful and the algorithms and hardware performed as expected. These test reports are available upon request. Technical Approach In April 2006, a proof-of-concept test article was flown on a two-stage sounding rocket at White Sands Missile Range, successfully demonstrating key elements of the AFSS concept of operations and flight software design. During the next year, a flight processor redundancy management subsystem was prototyped, and the AFSS was ported to a ruggedized conduction cooled COTS platform. In March 2007, the latest AFSS test article was flown on the two-stage Falcon 1 expendable launch vehicle at the Reagan Test Site at Kwajalein that demonstrated the new and additional aspects of the system design. Post-test reports of these flights are also available upon request. The next major step is to add an inertial navigation solution (INS) using a self-contained inertial measurement unit (IMU). The INS will be combined with the GPS navigation solution using a newly developed Kalman filter. This new hardware and navigation solution will be tested on an F-104 in November 2007 at KSC before being integrated into the reminder of the AFSS for the proposed sounding rocket flight. The advantages of the INS are to provide direct measurements of the vehicle's acceleration which are vital for detecting liftoff and staging events and to provide a navigation solution that is synergistic with the GPS solution. This synergy exists because INS and GPS hardware fail in completely different ways: the INS will fail only if the hardware itself malfunctions while the GPS solution can drop out from intentional or unintentional jamming, if the satellites are blocked or if the vehicle dynamics are too great. Moreover, the INS errors have a nonzero mean but zero standard deviation--the INS is very smooth but tends to drift with time--while the GPS errors have a zero mean but non-zero standard deviation--the GPS solution is centered on the true solution but is somewhat noisy. The GPS solution can be used to correct the INS and the INS can be used to help the GPS reacquire after losing lock. The primary software changes other than the integrated GPS/INS involve system timing. The first is the need to properly deal with a day change during launch or liftoff. The second is to use the GPS time message to initially synchronize the internal timing before using a GPS receiver-generated square wave for subsequent synchronization. Flight opportunites help advance the technology to the next phase, which will feature dual chasses cross-strapped together and a TDRSS transmitter for telemetering the AFSS data and outputs to the ground where they can be monitored and used for post-flight analysis without the need for additional ground-based assets. The final goal of the AFSS project is to produce a flight certifiable system that meets all Range Commanders Council and local Range requirements for redundancy and reliabilty. The AFSS team maintains close working relationships with the Eastern and Western Ranges and regularly briefs the Range Commanders Council of its progress.