Design of Launch Vehicle Flight Control Augmentors and Resulting Flight Stability and Control (Center Director's Discretionary Fund Project 93-05, Part III) PDF Download
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Author: National Aeronautics and Space Administration (NASA) Publisher: Createspace Independent Publishing Platform ISBN: 9781722342364 Category : Languages : en Pages : 76
Book Description
This publication presents the control requirements, the details of the designed Flight Control Augmentor's (FCA's), the static stability and dynamic stability wind tunnel test programs, the static stability and control analyses, the dynamic stability characteristics of the experimental Launch Vehicle (LV) with the designed FCA's, and a consideration of the elastic vehicle. Dramatic improvements in flight stability have been realized with all the FCA designs; these ranged from 41 percent to 72 percent achieved by the blunt TE design. The control analysis showed that control increased 110 percent with only 3 degrees of FCA deflection. The dynamic stability results showed improvements with all FCA designs tested at all Mach numbers tested. The blunt TE FCA's had the best overall dynamic stability results. Since the lowest elastic vehicle frequency must be well separated from that of the control system, the significant frequencies and modes of vibration have been identified, and the response spectra compared for the experimental LV in both the conventional and the aft cg configuration. Although the dynamic response was 150 percent greater in the aft cg configuration, the lowest bending mode frequency decreased by only 2.8 percent. Barret, C. Marshall Space Flight Center...
Author: National Aeronautics and Space Administration (NASA) Publisher: Createspace Independent Publishing Platform ISBN: 9781722342364 Category : Languages : en Pages : 76
Book Description
This publication presents the control requirements, the details of the designed Flight Control Augmentor's (FCA's), the static stability and dynamic stability wind tunnel test programs, the static stability and control analyses, the dynamic stability characteristics of the experimental Launch Vehicle (LV) with the designed FCA's, and a consideration of the elastic vehicle. Dramatic improvements in flight stability have been realized with all the FCA designs; these ranged from 41 percent to 72 percent achieved by the blunt TE design. The control analysis showed that control increased 110 percent with only 3 degrees of FCA deflection. The dynamic stability results showed improvements with all FCA designs tested at all Mach numbers tested. The blunt TE FCA's had the best overall dynamic stability results. Since the lowest elastic vehicle frequency must be well separated from that of the control system, the significant frequencies and modes of vibration have been identified, and the response spectra compared for the experimental LV in both the conventional and the aft cg configuration. Although the dynamic response was 150 percent greater in the aft cg configuration, the lowest bending mode frequency decreased by only 2.8 percent. Barret, C. Marshall Space Flight Center...
Author: C. Barret Publisher: ISBN: Category : Flight control Languages : en Pages : 63
Book Description
This report is Part III, the final part, of the Center Director's Discretionary Fund (CDDF) Project 93-05, in which the author as Principal Investigator has proposed and designed forward and aft, all-movable, blunt trailing-edge (TE), flight control augmentors (FCA's) to provide the required control augmentation for a family of aft center-of-gravity (cg) launch vehicles that could not be adequately controlled using engine gimbaling alone. This comprehensive flight mechanics research effort has been partially documented in previous publications. NASA TP-3635 (Barret, C.; February 1995) has presented the state-of-the-art assessment of smart materials and advanced composites directly applicable to the innovative design of the FCA's. NASA TP-3615 (Barret, C.; April 1996) has presented the developmental stages of the program, the comprehensive reviews of our national heritage of launch vehicles that have used aerodynamic surfaces, and the current use of these by other nations. This publication presents the control requirements, the details of the designed FCA's, the static stability and dynamic stability wind tunnel test programs, the static stability and control analyses, the dynamic stability characteristics of the experimental LV with the designed FCA's, and a consideration of the elastic vehicle. Dramatic improvements in flight stability have been realized with all the FCA designs; these ranged from 41 percent to 72 percent achieved by the blunt TE design. The control analysis showed that control increased 110 percent with only 3 degrees of FCA deflection. The dynamic stability results showed improvements with all FCA designs tested at all Mach numbers tested. The blunt TE FCA's had the best overall dynamic stability results. Since the lowest elastic vehicle frequency must be well separated from that of the control system, the significant frequencies and modes of vibration have been identified, and the response spectra compared for the experimental LV in both the con
Author: C. Barret Publisher: ISBN: Category : Flight control Languages : en Pages : 63
Book Description
This report is Part III, the final part, of the Center Director's Discretionary Fund (CDDF) Project 93-05, in which the author as Principal Investigator has proposed and designed forward and aft, all-movable, blunt trailing-edge (TE), flight control augmentors (FCA's) to provide the required control augmentation for a family of aft center-of-gravity (cg) launch vehicles that could not be adequately controlled using engine gimbaling alone. This comprehensive flight mechanics research effort has been partially documented in previous publications. NASA TP-3635 (Barret, C.; February 1995) has presented the state-of-the-art assessment of smart materials and advanced composites directly applicable to the innovative design of the FCA's. NASA TP-3615 (Barret, C.; April 1996) has presented the developmental stages of the program, the comprehensive reviews of our national heritage of launch vehicles that have used aerodynamic surfaces, and the current use of these by other nations. This publication presents the control requirements, the details of the designed FCA's, the static stability and dynamic stability wind tunnel test programs, the static stability and control analyses, the dynamic stability characteristics of the experimental LV with the designed FCA's, and a consideration of the elastic vehicle. Dramatic improvements in flight stability have been realized with all the FCA designs; these ranged from 41 percent to 72 percent achieved by the blunt TE design. The control analysis showed that control increased 110 percent with only 3 degrees of FCA deflection. The dynamic stability results showed improvements with all FCA designs tested at all Mach numbers tested. The blunt TE FCA's had the best overall dynamic stability results. Since the lowest elastic vehicle frequency must be well separated from that of the control system, the significant frequencies and modes of vibration have been identified, and the response spectra compared for the experimental LV in both the con
Author: National Aeronautics and Space Administration (NASA) Publisher: Createspace Independent Publishing Platform ISBN: 9781722723873 Category : Languages : en Pages : 76
Book Description
Marshall Space Flight Center has a rich heritage of launch vehicles that have used aerodynamic surfaces for flight stability and for flight control. Recently, due to the aft center-of-gravity (cg) locations on launch vehicles currently being studied, the need has arisen for the vehicle control augmentation that can be provided by these flight controls. Aerodynamic flight control can also reduce engine gimbaling requirements, provide actuator failure protection, enhance crew safety, and increase vehicle reliability and payload capability. As a starting point for the novel design of aerodynamic flight control augmentors for a Saturn class, aft cg launch vehicle, this report undertakes a review of our national heritage of launch vehicles using aerodynamic surfaces, along with a survey of current use of aerodynamic surfaces on large launch vehicles of other nations. This report presents one facet of Center Director's Discretionary Fund Project 93-05 and has a previous and subsequent companion publication. Barret, C. Marshall Space Flight Center...
Author: National Aeronautics and Space Administration (NASA) Publisher: Createspace Independent Publishing Platform ISBN: 9781722612924 Category : Languages : en Pages : 62
Book Description
The Marshall Space Flight Center has a rich heritage of launch vehicles that have used aerodynamic surfaces for flight stability such as the Saturn vehicles and flight control such as on the Redstone. Recently, due to aft center-of-gravity locations on launch vehicles currently being studied, the need has arisen for the vehicle control augmentation that is provided by these flight controls. Aerodynamic flight control can also reduce engine gimbaling requirements, provide actuator failure protection, enhance crew safety, and increase vehicle reliability, and payload capability. In the Saturn era, NASA went to the Moon with 300 sq ft of aerodynamic surfaces on the Saturn V. Since those days, the wealth of smart materials and advanced composites that have been developed allow for the design of very lightweight, strong, and innovative launch vehicle flight control surfaces. This paper presents an overview of the advanced composites and smart materials that are directly applicable to launch vehicle control surfaces. Barret, C. Marshall Space Flight Center...
Author: N.V. Kadam Publisher: Allied Publishers ISBN: 9387997812 Category : Technology & Engineering Languages : en Pages : 380
Book Description
This book gives in a concise and easy to understand form the various aspects of Practical Design of Flight Control Systems for Launch Vehicles and Missiles. It covers almost every aspect of Flight Control System Design which a designer would like to know, such as mission considerations, control requirements for various segments of the flight trajectory and different types of control effectors. It further gives generalized equations of motion with a novel method of incorporating structural flexibility and propellant sloshing which does not require rederivation, and very easy and common sense approach to deriving slosh and gimballed engine dynamic equations. Subsequently it gives the control system configurations, power plant sizing, loop design for linearised system and detailed analysis and design of on-off reaction control systems. It also covers various software features which are necessary for actual implementation of the design in flight missions, robustness features to avoid malfunctioning in some circumstances, design validation aspects including end-to-end sign checks and describes some flight experiences which called for design updates. The book is unique for its strong practical flavour and is directly useful to the working engineers in the field and post graduate students in Aerospace Engineering.
Author: National Aeronautics and Space Administration (NASA)
Author: National Aeronautics and Space Administration (NASA)
Author: C. Barret
Author: C. Barret
Author: 
Author: National Aeronautics and Space Administration (NASA)
Author: C. Barret
Author: National Aeronautics and Space Administration (NASA)
Author: Chris Barret
Author: N.V. Kadam
Author: Chris Barret