Flight investigation of steep instrument approach capabilities of a c-47 airplane under manual control
Flight test of steep instrument approach performance of manually controlled C- 47 aircraft
AIRCRAFT PERFORMANCE↗
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Preliminary study of steep instrument approach of three conventional aircraft
Steep instrument approaches with conventional aircraft
OPERATIONAL PROBLEM↗
Band-pass filters with steep skirt selectivity.
Band pass filters with low passband insertion loss and steep skirt selectivity by use of resonators with moderate Q values
BAND PASS FILTER↗
Flight investigation of steep instrument approach capabilities of a T-33 airplane under manual control
Steep instrument approach capabilities of T-33 airplane under manual control from glide slope to touchdown
GLIDE SLOPE↗
Effect of thrust and altitude in steep approaches on ground track noise
Thrust and altitude effects on ground track noise during steep approaches of four engine, medium range, turbojet transports
Zalovcik, J. A.↗
Operational aspects of steep VTOL approaches as determined from helicopter tests under simulated IFR conditions
Operational aspects of steep VTOL approaches as determined by helicopter tests under simulated instrumental flight rules conditions
Gracey, W.↗
Program for Optimization of Two-impulse Transfers by Contouring and Steep Descent
Computer program for optimization of two-impulse transfers by contouring and steep descent
Bender, D. F.↗
Flight evaluation of a display for steep approach
Vertical situation display concept for alleviating problems of inadequate guidance and display information for making steep approaches
Dunham, R. E., Jr.↗
Televised graphic displays for steep approach- to-landing research
Steep approach to landing for jet transport aircraft noise abatement, using ground based equipment and onboard TV display
Elkins, H. C.↗
Factors affecting handling qualities of a lift- fan aircraft during steep terminal area approaches
Handling qualities of V/STOL research vehicles during steep terminal area approaches, discussing powered lift fan VTOL aircraft limitations and instrument landing approach
Gerdes, R. M.↗
Development of an optimal automatic control law and filter algorithm for steep glideslope capture and glideslope tracking
A digital automatic control law to capture a steep glideslope and track the glideslope to a specified altitude is developed for the longitudinal/vertical dynamics of a CTOL aircraft using modern estimation and control techniques. The control law uses a constant gain Kalman filter to process guidance information from the microwave landing system, and acceleration from body mounted accelerometer data. The filter outputs navigation data and wind velocity estimates which are used in controlling the aircraft. Results from a digital simulation of the aircraft dynamics and the control law are presented for various wind conditions.
Halyo, N.↗
Development of a digital automatic control law for steep glideslope capture and flare
A longitudinal digital guidance and control law for steep glideslopes using MLS (Microwave Landing System) data is developed for CTOL aircraft using modern estimation and control techniques. The control law covers the final approach phases of glideslope capture, glideslope tracking, and flare to touchdown for automatic landings under adverse weather conditions. The control law uses a constant gain Kalman filter to process MLS and body-mounted accelerometer data to form estimates of flight path errors and wind velocities including wind shear. The flight path error estimates and wind estimates are used for feedback in generating control surface commands. Results of a digital simulation of the aircraft dynamics and the guidance and control law are presented for various wind conditions.
Halyo, N.↗
Development of a digital guidance and control law for steep approach automatic landings using modern control techniques
The development of a digital automatic control law for a small jet transport to perform a steep final approach in automatic landings is reported along with the development of a steady-state Kalman filter used to provide smooth estimates to the control law. The control law performs the functions of localizer and glides capture, localizer and glideslope track, decrab, and place. The control law uses the microwave landing system position data, and aircraft body-mounted accelerators, attitude and attitude rate information. The results obtained from a digital simulation of the aircraft dynamics, wind conditions, and sensor noises using the control law and filter developed are described.
Halyo, N.↗
Numerical simulation of flow near steep mountains with a potential enstrophy conserving scheme for the shallow water equations
Numerical experiments show that use of a potential enstrophy conserving scheme drastically improves numerical simulation of flow near steep mountains.
Arakawa, A.↗
Non-Maxwellian velocity distribution functions associated with steep temperature gradients in the solar transition region. Paper 1: Estimate of the electron velocity distribution functions
It was shown that, in the presence of the steep temperature gradients characteristic of EUV models of the solar transition region, the electron and proton velocity distribution functions are non-Maxwellian and are characterized by high energy tails. The magnitude of these tails are estimated for a model of the transition region and the heat flux is calculated at a maximum of 30 percent greater than predicted by collision-dominated theory.
Roussel-Dupre, R.↗
Development of a digital integrated automatic landing system /DIALS/ for steep approach and landing
This paper describes the development of a three-dimensional digital integrated automatic landing system (DIALS) for a small commercial jet transport. The system uses the Microwave Landing System (MLS), body-mounted accelerometers, as well as on-board sensors usually available on commercial aircraft, but does not require inertial platforms. The system development uses modern digital control techniques. The phases of flight considered are the localizer and glideslope capture, which may be performed simultaneously or sequentially, localizer and glideslope track (hold), crab/decrab, and flare to touchdown. The system captures, tracks and flares from steep glideslopes (2.5 - 5.5 deg) selected prior to glideslope capture. The results of a nonlinear simulation are presented.
Halyo, N.↗
Efficient Algorithms for Computing Trim and Small-Disturbance Equations of Motion of Aircraft Coordinated and Uncoordinated, Steady, Steep Turns
The development of computational algorithms that permit efficient calculation of aircraft trim states and of the associated small disturbance equations of motion for a systematic investigation of the statics and dynamics of aircraft in coordinated and uncoordinated, steady, steep turning flight is reported. The efficiency in the trim computation is realized by decoupling the governing equations. The small disturbance equations of motion, which are given in a general body axis system, include aerodynamic acceleration derivatives; they are cast in a familiar first order, vector matrix format of modern system theory. These algorithms were applied to a variety of rotorcraft simulation models. Results pertaining to a simulated hingeless rotor helicopter are also presented
Chen, Robert T. N.↗
Sensitivity analysis of helicopter IMC decelerating steep approach and landing performance to navigation system parameters
The present investigation is concerned with a sensitivity analysis of the Decelerated Steep Approach and Landing (DSAL) maneuver to on-board and ground-based navigation system parameters. The Instrument Meteorological Conditions (IMC) DSAL maneuver involves decelerating to zero range rate while tracking the localizer and glideslope. The considered study investigated the performance of the navigation systems using Constant Deceleration Profile (CDP) guidance and a six degrees glideslope trajectory. A closed-loop computer simulation of the UH1H helicopter DSAL system was developed for the sensitivity analysis. Conclusions on system performance parameter sensitivity are discussed.
Karmali, M. S.↗