Longitudinal-control design approach for high-angle-of-attack aircraft

Longitudinal-control design approach for high-angle-of-attack aircraft Download PDF EPUB FB2

Get this from a library. Longitudinal-control design approach for high-angle-of-attack aircraft. [Aaron J Ostroff; Melissa S Proffitt; United States. National Aeronautics and Space Administration. Scientific and Technical Information Program.].

aircraft with typical Iy values of about slug-ft 2, Longitudinal-control design approach for high-angle-of-attack aircraft book curve shows a pitch angular acceleration requirement of rad/sec 2. Ina cooperative McDonnell Aircraft/NASA Langley program was conducted to study high angle of attack flight dynamics and control law design issues on a generic supersonic cruise fighter airplane Size: KB.

In addition, the book is addressed to the aerodynamicist interested in a comprehensive reference to methods of analysis and computations of high angle of attack flow phenomena and is written for the aerospace scientist and engineer who is familiar with the basic concepts of viscous and inviscid flows and with computational methods used in fluid.

We use cookies to offer you a better experience, personalize content, tailor advertising, provide social media features, and better understand the use of our services. This aircraft is representative of the class of mixed-flow remote-lift concepts that was identified as the preferred design approach by the U.S./U.K.

STOVL Joint Assessment and Ranking Team. Roll-Yaw Control at High Angle of Attack by Forebody Tangential Blowing, Jour. of Aircraft, Vol. 35, No.

1, pp. 69–77 Ward, Greta N. and Ly, Uy-Loi Stability Augmentation Design of a Large Flexible Transport Using Nonlinear Parameter Optimization, Jour. of Guidance, Control, and Dynamics, Vol.

19, No. 2, pp. –Author: Malcolm J. Abzug, E. Eugene Larrabee. [] Berger T., Tischler M. B., Hagerott S. G., Gangsaas D. and Saeed N., “ Longitudinal Control Law Design and Handling Qualities Optimization for a Business Jet Flight Control System,” AIAA Guidance, Navigation and Control Conference, AIAA PaperAug.

Link Google ScholarCited by: These special conditions are issued for Airbus Model A series airplanes. These airplanes will have novel or unusual design features, associated with flight-envelope protection in icing and non- icing conditions, that use low-speed incidence protection and an alpha- floor function that.

American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA AIAA J Guidance, Control, Dyn ; 24(5): ± Bugajski DJ, Enns DF, Hendrick RC.

Nonlinear control law design for high angle-of-attack NASA High Angle-of-Attack Projects and Technology Conference,Vol. 4, NASA Cp Bugajski DJ, Enns DF. Nonlinear control laws with applications to high angle-of-attack flight. Corrections Dependent on Operation. Estimation of.

[53] Munk, M.M., â The Minimum Induced. angles, ranging from aircraft design to pilot training, regulatory oversight to change management.

11 hours of flight time, the wide-body aircraft is descended towards approach and landing at the flight crew’s home airport. It is clear weather in the very early hours of the morning. apply the longitudinal control so that the speed. Aircraft Flight Dynamics MAEFall Robert F. Stengel. Princeton University School of Engineering and Applied Science Department of Mechanical and Aerospace Engineering.

Aircraft Flight Dynamics is an undergraduate course that presents theory and methods for describing and predicting the motions of aircraft. The course introduces. PIOs have been around since the time of the Wright brothers, giving them an unambiguous seniority among flying qualities* problems.

42 In terms of severity and consequences, pilot-vehicle oscillatory phenomena comprise a complete spectrum. The oscillations may be of the temporary, easily corrected, low-amplitude variety often encountered by pilots when getting the feel of a new configuration.

In considering the development of all-wing aircraft I would like first to distinguish between all-wing and tailless airplanes. Most tailless airplanes are not all-wing by our definition. There is a tremendous background of development in tailless types, which has been fully reported by.

lations, and experimental aircraft, which must meet the 51 percent rule, LSA have fewer federally man-dated hurdles and fewer regulations to adhere to. LSA must show compli-ance with the applicable standards before they can be approved for sale as ready-to-fly aircraft or as a kit-built aircraft.

The standard that appliesFile Size: KB. The intent of the language in § (b) is to have a specific FTD, identified by the sponsor, used at least once in an FAA-approved flight training program for the airplane simulated during the month period described.

The identification of the specific FTD may change from one month period to the next month period as long as that sponsor sponsors and uses at least one FTD at least. Design for Air Combat by Ray Whitford.

Takes a deeper look at the details, again without equations and with lots of good graphics showing typical data to use deciding on design options. I continue to contend that the title suggests a much narrower focus than the book has.

Aircraft Design: A Conceptual Approach, by Daniel Raymer. Chapter 8,File Size: 1MB. Longitudinal control tests. Longitudinal trim. Data may be acquired through use of an inertial measurement system and a synchronized video of flight deck controls position (previously calibrated to show related surface position) and engine instrument.

AGARD FLIGHT TEST MANUAL VOLUME II, CHAPTER 9 HIGH SPEED STABILITY AND CONTROL PROBLEMS By Malcolm J. Abzug Douglas Aircraft Company, Inc. VOLUME II, CHAPTER 9 CHAPTER CONTENTS Page TERMINOLOGY INTRODUCTION GENERAL REMARKS ON HIGH SPEED STABILITY AND CONTROL FLIGHT TESTING (a) (b) (c) Coordination of Analytical Author: Malcolm J.

Abzug. (3) At a power level necessary to maintain level flight at V SR1, where V SR1 is the reference stall speed with the flaps in the approach position, the landing gear retracted, and with the aircraft at its maximum landing weight.The main concern of this chapter is the continuous closed-loop control tasks which are usually the most demanding for the pilot.

Figure gives a general illustration of such a task. The pilot is shown to sense (or observe) information about the vehicle (from displays and other cues), interpret and structure that information so as to determine the appropriate action, and then execute the.during non-normal flaps up, manual flight, high angle of attack maneuvers to provide a desirable increase in stick force gradient and a reduced pitch up tendency.

Similar to the Speed Trim function, the MCAS function is also a flight control law10 contained within each of the two FCCs.