Aviation research, sourced & cited.

Fog dispersion

The concept of using the charged particle technique to disperse warm fog at airports is investigated and compared with other techniques.

The role of the research simulator in the systems development of rotorcraft

The potential application of the research simulator to future rotorcraft systems design, development, product improvement evaluations, and safety analysis is examined.

Civil helicopter wire strike assessment study. Volume 2: Accident analysis briefs

A description and analysis of each of the 208 civil helicopter wire strike accidents reported to the National Transportation Safety Board (NTSB) for the ten year period 1970-1979 is given.

Civil helicopter wire strike assessment study. Volume 1: Findings and recommendations

Approximately 208 civil helicopter wire strike accidents for a ten year period 1970 to 1979 are analyzed. It is found that 83% of the wire strikes occurred during bright clear weather.

Helicopter propulsion system reliability and engine monitoring assessments

The major short life, unreliable, and high maintenance engine and power components and subsystems in current civil helicopters were identified.

Modular disposable can (MODCAN) crash cushion: A concept investigation

A conceptual design investigation of an improved highway crash cushion system is presented. The system is referred to as a modular disposable can (MODCAN) crash system.

Finite Element Stability Analysis for Coupled Rotor and Support Systems

The effects of fuselage motions on stability and random response were analytically assessed. The feasibility of adequate perturbation models from non-linear trim conditions was studied by computer and hardware experiment…

Wake vortex encounter hazards criteria for two aircraft classes

An investigation was conducted using a piloted, motion-base simulator to determine wake vortex hazard criteria for two classes of jet transport aircraft.

Quick look analysis of an emergency separation for ALT captive-inert flight 1

Emergency separation capability for the landing configuration of ALT Captive Inert Flight Number One was investigated. The quick look analysis confirms emergency separation capability under nominal conditions for the ALT…

Research requirements for emergency power to permit hover-one-engine-inoperative helicopter operation

The research and technology demonstration requirements to achieve emergency-power capability for a civil helicopter are documented. The goal for emergency power is the ability to hover with one engine inoperative, transi…

Dynamic stability characteristics of the combination space shuttle orbiter and ferry vehicle

Subsonic forced-oscillation tests of a 0.015 scale model of the space shuttle orbiter/747 ferry vehicle were conducted in the Langley high speed 7- by 10-foot tunnel at Mach numbers of 0.2, 0.4, and 0.5 for angles of att…

Pilot workload and fatigue: A critical survey of concepts and assessment techniques

The principal unresolved issues in conceptualizing and measuring pilot workload and fatigue are discussed. These issues are seen as limiting the development of more useful working concepts and techniques and their applic…

Instructor and student pilots' subjective evaluation of a general aviation simulator with a terrain visual system

Ten student pilots were given a 1 hour training session in the NASA Langley Research Center's General Aviation Simulator by a certified flight instructor and a follow-up flight evaluation was performed by the student's o…

Development and analysis of a modular approach to payload specialist training

A modular training approach for Spacelab payload crews is described. Representative missions are defined for training requirements analysis, training hardware, and simulations.

STOL aircraft transient ground effects. Part 2: Experimental techniques feasibility study

Procedures for simulating transient effects associated with STOL aircraft landings and takeoffs were examined and a basis was developed for selection of an experimental approach based on consideration of simulation requi…

Solid rocket booster thrust vector control subsystem test report (D-1)

The results of the sequence of tests performed on the space shuttle solid rocket booster thrust vector control subsystem are presented.

Calibration of a pitot-static rake

A five-element pitot-static rake was tested to confirm its accuracy and determine its suitability for use at Langley during low-speed tunnel calibration primarily at full-scale tunnel.

Electrical power requirements analysis. Single failure tolerant entry

The results of an analysis of the orbiter electrical power system for the case of a single failure tolerant (SFT) entry are presented.

Flight evaluation of two-segment approaches using area navigation guidance equipment

A two-segment noise abatement approach procedure for use on DC-8-61 aircraft in air carrier service was developed and evaluated. The approach profile and procedures were developed in a flight simulator.

Helicopter sling load accident/incident survey: 1968 - 1974

During the period considered a mean of eleven accidents per year occurred and a mean of eleven persons were killed or seriously injured per year.

Full-scale crash test of a CH-47C helicopter

A full-scale crash test of a large troop/cargo carrying CH-47C helicopter was conducted at the Langley impact dynamics research facility. The crash test of this large helicopter was performed as part of a joint U.S.

Bridle Attachment for Aircraft Spin-Recovery Parachute

Antispin rolling moment produced by chute drag force. Parachute stowed prior to deployment. At deployment, bridle attachment produces antispin rolling moment.

Concepts for a theoretical and experimental study of lifting rotor random loads and vibrations (further experiments with progressing/regressing rotor flapping modes), Phase 7-C

The experiments with progressing/regressing forced rotor flapping modes have been extended in several directions and the data processing method has been considerably refined.

An unsteady wake model for a hingeless rotor

A simple nonsteady wake model derived from the unsteady moment of the momentum equation for zero advance ratio is correlated with cyclic pitch frequency response tests conducted with a small hingeless rotor model.

Analysis of vortex wake encounter upsets

The problem of an airplane being upset by encountering the vortex wake of a large transport on takeoff or landing is currently receiving considerable attention.

Studies of uncontrolled air traffic patterns, phase 1

The general aviation air traffic flow patterns at uncontrolled airports are investigated and analyzed and traffic pattern concepts are developed to minimize the midair collision hazard in uncontrolled airspace.

A simulator investigation of engine failure compensation for powered-lift STOL aircraft

A piloted simulator investigation of various engine failure compensation concepts for powered-lift STOL aircraft was carried out at the Ames Research Center.

A study of carburetor/induction system icing in general aviation accidents

An assessment of the frequency and severity of carburetor/induction icing in general-aviation accidents was performed. The available literature and accident data from the National Transportation Safety Board were collect…

Fixed-base simulation study of decoupled controls during approach and landing of a STOL transport airplane

A fixed-base visual simulation study has been conducted to evaluate the use of decoupled controls as a means for reducing pilot workload during approach and landing of an externally blown jet-flap short take-off and land…

Terminal area considerations for an advanced CTOL transport aircraft

Projected future conditions at large urban airports were used to identify design objectives for a long-haul, advanced transport airplane introduced for operation in the mid-1980s.

Air pollution from future giant jetports

Because aircraft arrive and depart in a generally upwind direction, the pollutants are deposited in a narrow corridor extending downwind of the airport.

A simple model of evaporatively driven downdraft - Application to microburst downdraft

It is pointed out that the physics of a downdraft are very different from that of an updraft. An updraft is virtually saturated, while the downdraft can be unsaturated.

The collisionless macroscopic Kelvin-Helmholtz instabiity. I Transverse electrostatic mode

The electrostatic limit of the Kelvin-Helmholtz instability in a collisionless plasma is investigated for a magnetic field perpendicular to the velocity flow.

Simulator for training remote-manipulator operators

Six-degree-of-freedom simulator uses economical components. Reduction in complexity makes this or similar system cost-effective for training manipulator operators, such as those in industries handling nuclear wastes and …

Actuator digital interface unit (AIU)

Alternate versions of the actuator interface unit are presented. One alternate is a dual-failure immune configuration which feeds a look-and-switch dual-failure immune hydraulic system.

Implications of equipping a DC-8-61 fleet with RNAV/two-segment approach avionics

Due to the costs of implementing two-segment approaches with special purpose computers, and the fact that such systems rely on special ground equipment not generally in use today, it is useful to consider the possibility…

An atlas of volcanic ash

Volcanic ash samples collected from a variety of recent eruptions were studied, using petrography, chemical analyses, and scanning electron microscopy to characterize each ash type and to relate ash morphology to magma c…

Correlation energy in triplet states - Comparison of many-body perturbation theory and configuration interaction for CH2 and O2

Effects of various runway lighting parameters upon the relation between runway visual range and visual range of centerline and edge lights in fog

Thirty six students and 54 commercial airline pilots were tested in the fog chamber to determine the effect of runway edge and centerline light intensity and spacing, fog density, ambient luminance level, and lateral and…

Apparatus for aiding a pilot in avoiding a midair collision between aircraft

An apparatus for aiding a pilot in avoiding a midair collision between aircraft is described. A protected aircraft carries a transmitter, a transponder, a receiver, and a data processor; and an intruding cooperating airc…

Preliminary design study of quiet integral fan lift engines for VTOL transport applications in the 1980s

Preliminary designs of three integral lift fan engines suitable for commercial certification in the 80's were completed. Emphasis was placed on low cost, simplicity, low noise, low emissions, minimum weight, and design f…

Water/glycol temperature control circuit failed in the automatic mode: Apollo 16

An anomaly report concerning failure of the water/glycol temperature control circuit during the Apollo 16 flight is presented. The anomaly is described and diagrams of the system are presented.

Active-standby servovalue/actuator development

A redundant, fail/operate fail/fixed servoactuator was constructed and tested along with electronic models of a servovalve. It was found that a torque motor switch is satisfactory for the space shuttle main engine hydrau…

Variation in the annual general aviation accident rate as it relates to flight training.

Annual general aviation aircraft accident rate variation related to annual variations in pilot flight training activity

Ballistic wake of turbulence in a plasma shock wave.

Ballistic wake structure and jump conditions for plane plasma shock waves with electrostatic turbulence

Concepts for a theoretical and experimental study of lifting rotor random loads and vibrations. Phase 6-A: Effects of blade torsion, of blade flap bending flexibility and of rotor support flexibility on rotor stability and random response

The effects of lifting rotor blade torsion, blade flap bending flexibility and rotor support flexibility on rotor stability and random response are described.

Concepts for a theoretical and experimental study of lifting rotor random loads and vibrations. Phase 6-B: Experiments with progressing/regressing forced rotor flapping modes

A two bladed 16-inch hingeless rotor model was built and tested outside and inside a 24 by 24 inch wind tunnel test section at collective pitch settings up to 5 deg and rotor advance ratios up to .4.

Aerodynamic characteristics of vehicle bodies at crosswind conditions in ground proximity

Aerodynamic characteristics of vehicle bodies at crosswind conditions in ground proximity

Prediction of lift and drag for slender sharp-edge delta wings in ground proximity

Predicting lift and drag for slender sharp-edge Delta wings in ground proximity

Effects of ground proximity on the longitudinal aerodynamic characteristics of an unswept aspect-ratio-10 wing

Ground proximity effects of unswept aspect ratio 10 wing on longitudinal aerodynamic characteristics