Propulsion Controls and Diagnostics Research at NASA GRC Status Report

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1 Propulsion Controls and Diagnostics Research at NASA GRC Status Report Dr. Sanjay Garg Branch Chief Ph: (216) FAX: (216) Presented at: Aerospace Guidance and Control System Committee Meeting Cocoa Beach, FL, Oct. 2007

2 Mission Strategic Goals Mission Directorates NASA Program Structure To pioneer the future in space exploration, scientific discovery, and aeronautics research Values: Safety, Teamwork, Integrity, Mission Success 1. Fly the shuttle safely till Complete the International Space Station 3. Develop a balanced program of science, exploration and aeronautics 4. Bring a new Crew Exploration Vehicle into service ASAP 5. Encourage the pursuit of partnership with commercial space sector 6. Establish a lunar return program with utility for mission to Mars Aeronautics Research Science Exploration Space Operations Centers Programs Projects Sub-Proj. Tasks

3 NASA Aeronautics Program Structure Aeronautics Research Mission Directorate Fundamental Aeronautics Program Aviation Safety Program Airspace Systems Program Hypersonics Supersonics Subsonic Fixed Wing Subsonic Rotary Wing Integrated Vehicle Health Management Aging Aircraft Integrated Resilient Aircraft Control Integrated Flight Deck Technologies Super-Density Surface Management Next Generation Air Transportation System

4 Propulsion Control and Diagnostics Research Under NASA Aeronautics Research Mission Programs November 6-7, 2007 Ohio Aerospace Institute OBJECTIVES Disseminate information to the research community about the propulsion control and diagnostics research being done at NASA GRC in support of various projects under the NASA Aeronautics Research Mission programs. Get feedback from peers on value of the research and validity of the technical approach. Identify opportunities for potential collaboration and sharing of tools and methods.

5 Propulsion Control and Diagnostics for Aviation Safety Aviation Safety Program Integrated Vehicle Health Management Propulsion Health Management Integrated Resilient Aircraft Control IIFD Integrated Propulsion Control and Dynamics AAD Self awareness and prognosis of gas path, combustion, and overall engine state; fault-tolerant system architecture Gas Path health management.. How to use the propulsion system as an effective flight control actuator in abnormal situations allow safe and controllable flight for limited time and safe landing in the presence of airframe damage

6 IRAC System Concept Integrated Adaptive Flight/Structural/Propulsion Control Fast Inverse FEM algorithm identifies damage and predicts deformations in real time Direct FEM models 2.819e e e-01 compute e-01 internal loads e e-01 & AE Effects in real time Strain sensors provide discrete measurements in real time Adaptive Flight Control - Decisions Based on Failures/Impairment/Damage, Remaining Control/Engine Capabilities, Risks Associated with Accommodation/Recovery, Flight Safety Margins - Combinations of Internal & External Loss-of-Control Factors - Includes Upset Recovery under Failures/Damage/Disturbance Conditions and Adaptive Guidance Flight Control Commands - Engine Operation Mode - Engine Performance Requirements Engine Status Report - Engine Failure/Damage Condition - Engine Performance Limits - Performance/Life Trade-off Curve % 100% 110% 120% - Engine Failure/Damage Assessment - Survival Operation Mode for Damaged Engine - Optional Operation Beyond Designed Envelope

7 Current Engine Control and Limits A Full Authority Digital Engine Control (FADEC) system adjusts fuel flow to set power management - Speed Control limits - Acceleration/Deceleration speed limits - Fuel Flow limits - Pressure Control Power Management Schedule Core Speed T41 Limits Accel/ Decel Fan Accel/ Decel Core Accel/ Decel PS3 Fuel Flow Over Speed Fuel Control Designed Limits: Burner Pressure, Temperatures, Speed Red Line Many of these limits can be relaxed to enhance the performance at the cost of shortened operating life.

8 Structural Damage Assessment Scenario Requirements 75, Thrust [lb] 70,000 65,000 60,000 55,000 45, Time before failure [min] 40, Station Temperature [ F] Example : Thrust Station Temperature Sustainable Time Duration

9 IRAC Approach Baseline engine simulation to: Include representative engine control limits Simulate engine response time throughout the flight envelope Flight/propulsion study to determine high level requirements Concentrate on fast response engine control Studies on: Effects of relaxing various control limits Operating margin estimation and management Engine life monitoring and prognosis Stochastic component life models Prognostic model to predict risk Control strategy for performance/life trade-off Risk management Optimum control for selected acceptable risk level Flight/propulsion integration Flight simulator implementation

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