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  • 1
    Publication Date: 2019-07-13
    Description: Dynamic-inversion-based flight control laws present an attractive alternative to conventional gain-scheduled designs for high angle-of-attack maneuvering, where nonlinearities dominate the dynamics. Dynamic inversion is easily applied to the aircraft dynamics requiring a knowledge of the nonlinear equations of motion alone, rather than an extensive set of linearizations. However, the robustness properties of the dynamic inversion are questionable especially when considering the uncertainties involved with the aerodynamic database during post-stall flight. This paper presents a simple analysis and some preliminary results of simulations with a perturbed database. It is shown that incorporating integrators into the control loops helps to improve the performance in the presence of these perturbations.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 92-4330 , AIAA Guidance, Navigation and Control Conference; Aug. 10-12, 1992; Hilton Head Island, SC; United States
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  • 2
    Publication Date: 2019-07-13
    Description: In this paper, the control laws for the lateral-directional dynamics of a supermaneuverable aircraft is analyzed with a view to reducing the levels of lateral acceleration and sideslip, which are encountered during aggressive rolling maneuvers at high angles of attack. The analysis uses a linearized model of the lateral-directional dynamics and thus H-free-flow techniques can be applied. It is shown that trade-offs exist between simultaneously minimizing lateral acceleration measured at the pilot's station, ny(p), minimizing sideslip and minimizing tracking errors between the roll-rate about the velocity vector and its command. The paper concludes that a significant reduction in ny(p) is only attainable by compromising the roll-rate performance.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 91-2711 , AIAA Guidance, Navigation and Control Conference; Aug. 12-14, 1991; New Orleans, LA; United States
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  • 3
    Publication Date: 2019-07-13
    Description: This paper describes the use of nonlinear dynamic inversion for the design of a flight control system for a supermaneuverable aircraft. First, the dynamics to be controlled were separated into fast and slow variables. The fast variables were the angular rates and the slow variables were the attitude angles. Then a nonlinear inversion controller was designed for the fast variables. This stabilized the longitudinal short-period and improved the lateral-directional responses over a wide range of angle of attack by making use of a combination for aerodynamic surfaces and thrust vectoring control. Outer loops were then closed to allow the pilot to control the slow dynamics, the angle of attack, side-slip angle and the velocity bank angle. Nonlinear inversion was also used to design of the outer loop control laws. The dynamic inversion control laws were compared with more conventional, gain-scheduled control laws and were shown to yield much better performance.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 90-3406 , AIAA Guidance, Navigation and Control Conference; Aug. 20-22, 1990; Portland, OR; United States
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  • 4
    Publication Date: 2019-06-28
    Description: Techniques for the design of control systems for manually controlled, high-performance aircraft must provide the following: (1) multi-input, multi-output (MIMO) solutions, (2) acceptable handling qualities including no tendencies for pilot-induced oscillations, (3) a tractable approach for compensator design, (4) performance and stability robustness in the presence of significant plant uncertainty, and (5) performance and stability robustness in the presence actuator saturation (particularly rate saturation). A design technique built upon Quantitative Feedback Theory is offered as a candidate methodology which can provide flight control systems meeting these requirements, and do so over a considerable part of the flight envelope. An example utilizing a simplified model of a supermaneuverable fighter aircraft demonstrates the proposed design methodology.
    Keywords: Aircraft Stability and Control
    Type: NASA/CR-97-207152 , NAS 1.26:207152 , AIAA Paper 97-3778
    Format: application/pdf
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  • 5
    Publication Date: 2019-07-12
    Description: This paper describes the application of nonlinear quadratic regulator (NLQR) theory to the design of control laws for a typical high-performance aircraft. The NLQR controller design is performed using truncated solutions of the Hamilton-Jacobi-Bellman equation of optimal control theory. The performance of the NLQR controller is compared with the performance of a conventional P + I gain scheduled controller designed by applying standard frequency response techniques to the equations of motion of the aircraft linearized at various angles of attack. Both techniques result in control laws which are very similar in structure to one another and which yield similar performance. The results of applying both control laws to a high-g vertical turn are illustrated by nonlinear simulation.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: International Journal of Control (ISSN 0020-7179); 56; 4; p. 799-812.
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  • 6
    Publication Date: 2019-07-13
    Description: This paper describes a technique which may be used to design the flight control system for a highly maneuverable aircraft. The control system was provided to stabilize the dynamics of the aircraft model and allow it to fly simulated, poststall 'supermaneuvers'. Although the aircraft dynamics are highly nonlinear under these conditions, the gain-scheduled, flight control system was designed using basically linear techniques. A manuever generator was implemented to pilot the mathematical model through prescribed optimal trajectories. The control system design performed well while executing maneuvers involving small angular rates where the governing dynamics could be considered linear. However, the performance deteriorated once the model was subjected to high angular rates at high angle of attack.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 89-3486 , AIAA Guidance, Navigation and Control Conference; Aug. 14-16, 1989; Boston, MA; United States
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  • 7
    Publication Date: 2019-07-12
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 15; 4 Ju; 976-984
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  • 8
    Publication Date: 2019-07-13
    Description: Actuator rate saturation is an important factor adversely affecting the stability and performance of aircraft flight control systems. It has been identified as a catalyst in pilot-induced oscillations, some of which have been catastrophic. A simple design technique is described that utilizes software rate limiters to improve the performance of control systems operating in the presence of actuator rate saturation. As described, the technique requires control effectors to be ganged such that any effector is driven by only a single compensated error signal. Using an analysis of the steady-state behavior of the system, requirements are placed upon the type of the loop transmissions and compensators in the proposed technique. Application of the technique to the design of a multi-input/multi-output, lateral-directional control system for a simple model of a high-performance fighter is demonstrated as are the stability and performance improvements that can accrue with the technique.
    Keywords: Aircraft Stability and Control
    Type: NASA/CR-97-207117 , NAS 1.26:207117 , Journal of Guidance, Control and Dynamics; 20; 1; 90-96
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  • 9
    ISSN: 0006-3525
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Pyridoxylated adult human hemoglobin (HbAo) was prepared using a one molar equivalent of pyridoxal 5-phosphate (PLP) per heme and reduced with either NaCNBH3 or NaBH4. A separate sample was pyridoxylated and passed through a mixed-bed ion exchange column without reduction. All three preparations had a P50 of 29 ± 2 torr and a cooperativity of n = 2.4 ± 0.1. These preparations, in both the oxy and deoxy forms, were then treated with 7 equivalents of glutaraldehyde per tetramer at pH 6.8 at 4°C and at room temperature. The polymerization invariably reduced the P50 to 18 ± 2 torr with Hill coefficients of less than 2. These solutions, with or without further reduction using NaCNBH3, all retained the PLP in differing amounts (2-3 moles/tetramer). Methemoglobin concentrations were increased during the polymerization reaction. The normal pyridoxylation procedure, using sodium borohydride reduction, resulted in a number of different molecular species. Polymerization with glutaraldehyde caused a further proliferation of molecular species that could not be separated by anion exchange chromatography or by isoelectric focusing. The extent of polymerization, estimated by gel exclusion chromatography and SDS polyacrylamide gel electrophoresis, was from 40 to 50%. Analysis of the reverse phase chromatograms, which separate the heme and the α- and β-chains, showed extensive polymerization and distribution of the radioactively labeled PLP on the protein for all preparations. All of the polymerized and pyridoxylated samples were unstable, and showed different chromatographic patterns after storage at 4°C for 1 month. Attempts to stabilize these preparations by further reduction with NaCNBH3 gave products with a lower P50 and lower cooperativity. When the reactions were conducted with a purified HbAo, heterogeneity was somewhat decreased compared to the normally used stroma-free hemoglobin, but a large number of molecular species were still formed.
    Additional Material: 8 Ill.
    Type of Medium: Electronic Resource
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  • 10
    ISSN: 0006-3525
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: A number of chemically modified hemoglobin preparations have been proposed for use as an emergency resuscitation fluid. The purpose for forming these hemoglobin derivatives is to decrease the oxygen binding (i.e., to increase the P50) and to increase the intravascular retention time. These goals have been met with various degrees of success by using the reaction with pyridoxyl 5-phosphate to raise the P50, followed by the addition of glutaraldehyde to increase circulating half-life by polymerization.1,2 Other derivatives have been formed with polyethylene glycol,3,4 bis-(3,5-dibromosalicyl) fumarate,5,6 glycolaldehyde,7 and 2-nor-2-formylpyridoxal 5-phosphate,8,9 as well as with other compounds. All these derivatives introduce a foreign molecule into the hemoglobin, which may not always be desirable. Recently Tharp and Day10 used cyanogen to form intersubunit amide cross-links in hemoglobin without the incorporation of cyanogen. This approach is attractive if the appropriate functional properties can be attained. Takeda et al.11 showed that equimolar concentrations of amino acids and disuccinimidyloxalate could form peptide bonds in high yield. We report the characteristics of the hemoglobin molecule modified by internal covalent amide bonds, which may be a suitable candidate for a resuscitation fluid.
    Additional Material: 3 Ill.
    Type of Medium: Electronic Resource
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