United States National Aeronautics and Space Administration Scientific and Technical Information Program

Supersonic flying qualities experience using the SR-71 by Timothy H Cox( )

6 editions published in 1997 in English and held by 315 WorldCat member libraries worldwide

Approximately 25 years ago NASA Dryden Flight Research Center, Edwards, California, initiated the evaluation of supersonic handling qualities issues using the XB-70 and the YF-12. Comparison of pilot comments and ratings with some of the classical handling qualities criteria for transport aircraft provided information on the usefulness of these criteria and insight into supersonic flying qualities issues. A second research study has recently been completed which again addressed supersonic flying qualities issues through evaluations of the SR-71 in flight at Mach 3. Additional insight into supersonic flying qualities issues was obtained through pilot ratings and comments. These ratings were compared with existing military specifications and proposed criteria for the High Speed Civil Transport. This paper investigates the disparity between pilot comments and the Neal/Smith criteria through a modification of the technique using vertical speed at the pilot station. The paper specifically addresses the pilot ability to control flightpath and pitch attitude in supersonic flight and pilot displays typical of supersonic maneuvering

A model for Space Shuttle orbiter tire side forces based on NASA Landing Systems Research Aircraft test results by John F Carter( )

3 editions published in 1997 in English and held by 311 WorldCat member libraries worldwide

Least squares best fit method for the three parameter Weibull distribution : analysis of tensile and bend specimens with volume or surface flaw failure by Bernard Gross( )

4 editions published in 1996 in English and held by 311 WorldCat member libraries worldwide

Development and flight test of an augmented thrust-only flight control system on an MD-11 transport airplane by Frank W Burcham( )

3 editions published in 1996 in English and held by 310 WorldCat member libraries worldwide

An emergency flight control system using only engine thrust, called Propulsion-Controlled Aircraft (PCA), has been developed and flight tested on an MD-11 airplane. In this thrust-only control system, pilot flightpath and track commands and aircraft feedback parameters are used to control the throttles. The PCA system was installed on the MD-11 airplane using software modifications to existing computers. Flight test results show that the PCA system can be used to fly to an airport and safely land a transport airplane with an inoperative flight control system. In up-and-away operation, the PCA system served as an acceptable autopilot capable of extended flight over a range of speeds and altitudes. The PCA approaches, go-arounds, and three landings without the use of any normal flight controls have been demonstrated, including instrument landing system-coupled hands-off landings. The PCA operation was used to recover from an upset condition. In addition, PCA was tested at altitude with all three hydraulic systems turned off. This paper reviews the principles of throttles-only flight control; describes the MD-11 airplane and systems; and discusses PCA system development, operation, flight testing, and pilot comments

Structural dynamic model obtained from flight use with piloted simulation and handling qualities analysis by Bruce G Powers( )

4 editions published in 1996 in English and held by 310 WorldCat member libraries worldwide

Flight test of a propulsion-based emergency control system on the MD-11 airplane with emphasis on the lateral axis by John J Burken( )

4 editions published in 1996 in English and held by 309 WorldCat member libraries worldwide

A large, civilian, multiengine transport MD-11 airplane control system was recently modified to perform as an emergency backup controller using engine thrust only. The emergency backup system, referred to as the propulsion-controlled aircraft (PCA) system, would be used if a major primary flight control system fails. To allow for longitudinal and lateral-directional control, the PCA system requires at least two engines and is implemented through software modifications. A flight-test program was conducted to evaluate the PCA system high-altitude flying characteristics and to demonstrate its capacity to perform safe landings. The cruise flight conditions, several low approaches and one landing without any aerodynamic flight control surface movement, were demonstrated. This paper presents results that show satisfactory performance of the PCA system in the longitudinal axis. Test results indicate that the lateral-directional axis of the system performed well at high altitude but was sluggish and prone to thermal upsets during landing approaches. Flight-test experiences and test techniques are also discussed with emphasis on the lateral-directional axis because of the difficulties encountered in flight test

Effect of actuated forebody strakes on the forebody aerodynamics of the NASA F-18 HARV by David F Fisher( )

2 editions published in 1996 in English and held by 309 WorldCat member libraries worldwide

Output data formatter for the Electronically Scanned Thinned Array Radiometer (ESTAR) instrument by William A Chren( )

5 editions published in 1993 in English and held by 309 WorldCat member libraries worldwide

A gas chromatograph/mass spectrometer system for ultralow-emission combustor exhaust studies by Chowen Chou Wey( )

2 editions published in 1996 in English and held by 309 WorldCat member libraries worldwide

High-alpha handling qualities flight research on the NASA F/A-18 High Alpha Research Vehicle by Keith D Wichman( )

2 editions published in 1996 in English and held by 309 WorldCat member libraries worldwide

A flight research study of high-angle-of-attack handling qualities has been conducted at the NASA Dryden Flight Research Center using the F/A-18 High Alpha Research Vehicle (HARV). The objectives were to create a high-angle-of-attack handling qualities flight database, develop appropriate research evaluation maneuvers, and evaluate high-angle-of-attack handling qualities guidelines and criteria. Using linear and nonlinear simulations and flight research data, the predictions from each criterion were compared with the pilot ratings and comments. Proposed high-angle-of-attack nonlinear design guidelines and proposed handling qualities criteria and guidelines developed using piloted simulation were considered. Recently formulated time-domain Neal-Smith guidelines were also considered for application to high-angle-of-attack maneuvering. Conventional envelope criteria were evaluated for possible extension to the high-angle-of-attack regime. Additionally, the maneuvers were studied as potential evaluation techniques, including a limited validation of the proposed standard evaluation maneuver set. This paper gives an overview of these research objectives through examples and summarizes result highlights. The maneuver development is described briefly, the criteria evaluation is emphasized with example results given, and a brief discussion of the database form and content is presented