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Journal Article

Common Helmet Design for Launch, Entry, & Abort and EVA Activities – A Discussion on the Design and Selection Process of Helmets for Future Manned Flight

2008-06-29
2008-01-1991
Effective helmet performance is a critical component to achieving safe and efficient missions along the entire timeline; from launch and entry events to operations in a micro-gravity environment to exploration of a planetary surface, the helmet system is the capstone of the pressurized space suit assembly. Each phase of a mission requires uncompromising protection in the form of a robust pressure vessel and adequate protection from impact, both interior and exterior, all while remaining relatively comfortable and providing excellent visual interaction with the environment. Historically there have been large voids between these critical characteristics with the primary focus concerning the pressure vessel first and impact protection and crew comfort second. ILC Dover, NASA-JSC, Gentex Corporation, and Hamilton Sundstrand formed an Integrated Product Team (IPT) and conducted a NASA funded study to research and evaluate new concepts in helmet design.
Technical Paper

Shuttle Abort Landing Site Emergency Medical Services

1991-07-01
911570
Shuttle Transoceanic Abort Landing (TAL) sites, located on the African coast and in Spain, require an emergency medical capability for astronauts who may be injured in an abort landing. ...Shuttle Transoceanic Abort Landing (TAL) sites, located on the African coast and in Spain, require an emergency medical capability for astronauts who may be injured in an abort landing. The remote African TAL sites present unusual medical planning and logistical problems. ...When you add to that a bailout capability, the extreme remoteness of some of the foreign abort sites, the lack of accessibility to adequate medical care, and the virtual celebrity status of the astronauts, all of the elements of a medical contingency planning nightmare are in place.
Standard

Gas Motor

2013-06-17
CURRENT
ARP719B
It is intended that this SAE Aerospace Recommended Practice (ARP) will set down guidelines for the development and test of gas motors to provide a practical and reliable hot gas rotary actuation mechanism. Specific operational and test requirements shall be specified in a detail specification.
Standard

PRECISION MOTOR TACHOMETER GENERATOR

1970-04-15
CURRENT
ARP667
This recommended practice establishes objectives for high performance control motor tachometer generators to be used with aeronautical and associated equipment in protective enclosures or completely within the shell of the aircraft so that they are subjected only to the internal climatic conditions of heat, cold, shock, vibration, and humidity. ...Control motor tachometer generators larger than size 23 are not covered in this document.
Standard

AIRCRAFT HYDRAULIC START MOTOR

1980-06-15
CURRENT
AS714A
This Aerospace Standard (AS) establishes the requirements for hydraulic start motors suitable for use in starting a gas turbine engine, and the methods to be used for demonstrating compliance with these requirements.
Technical Paper

Brushless Motor Space Optimization with Drive Electronics Contained in the Motor

1987-08-01
871567
Recent advancements in power electronics, electronics integration and packaging, and motor system design have made possible the inclusion of the drive electronics for electronically commutated motors in the housing of the motor itself. Motor volume and packaging depend upon interacting systems of mechanical, thermal, electromagnetic, and electronic constraints. ...Several examples of integrated motors are given. Recent advancements in several technologies upon which brushless motors depend allow inclusion of the drive electronics in the motor housing, resulting in a single, integrated mechanical part. ...Recent advancements in several technologies upon which brushless motors depend allow inclusion of the drive electronics in the motor housing, resulting in a single, integrated mechanical part. The motor as a system, thus consists of an electric machine plus an electronic driver.
Technical Paper

Solid Propellant Rocket Motor Thermal Analysis

1962-01-01
620330
This paper discusses how analog and digital computers are used to finalize solid propellant rocket motor thermal design calculations, with emphasis on the effect of propellant-liner incremental thickness lumped with the motor case, and how it is selected. The effect of neglecting the motor case heat storage on final temperature distribution is indicated for both ground and flight analyses. ...This paper discusses how analog and digital computers are used to finalize solid propellant rocket motor thermal design calculations, with emphasis on the effect of propellant-liner incremental thickness lumped with the motor case, and how it is selected.
Technical Paper

High Power Induction Motor for Aircraft Spoiler

1996-10-01
965525
This paper presents the design, fabrication, and testing of a 50HP, 30000 rpm induction motor for a next generation large aircraft spoiler. The motor is characterized by high power density, developing over 8.5 pounds per square inch of airgap surface area with only 13 pounds electromagnetic weight. ...Testing was obtained using a high speed hydraulic dynamometer with digital data acquisition. The motor and actuator are designed and built by AlliedSignal for participation in the NASA Redundant Effector Program and NASA Power-by-Wire Electromechanical Actuation (EMA) Spoiler Program. ...The program emphasizes the demonstration of power electronic motor drive and actuation technologies for aerospace applications. In addition to NASA LeRC other participants include Lockheed Martin Astronautics, Advanced Launch Systems (program management), General Electric Corporate Research (Auxiliary Resonant Commutated Pole Inverter, DSP digital motor control technology, laboratory drive testing), Lockheed Martin Controls Systems (actuator control electronics, system integration), and Boeing Commercial Aircraft Company (spoiler actuation and aircraft requirements).
Technical Paper

Advanced Pintle-Controlled Motor with Thrust Vector Control

1971-02-01
710763
The development of a motor combining a pintle-controlled nozzle with gimbaled supersonic splitline thrust vector control (TVC) was undertaken in an effort to exploit the increased performance flexibility of a rocket system which is offered by thrust magnitude and thrust vector control. ...The major objective is to demonstrate the effectiveness of a controllable solid-propelled rocket motor which features variable thrust, attitude control, and high propulsion efficiency. To date, three half-duration motors have been static-fired, two at sea level and one which contained a thrust vector control system at simulated altitude. ...To date, three half-duration motors have been static-fired, two at sea level and one which contained a thrust vector control system at simulated altitude.
Technical Paper

Fault-Tolerant Electrical Motor Drives for Aerospace Application

2010-11-02
2010-01-1743
The requirements of such machines will be reviewed and different motor topologies will be compared. Three examples of fault-tolerant drive system demonstrators will then be described including a novel flux-switching, permanent magnet, synchronous machine topology.
Technical Paper

The Development of a New Drill Motor Concept

2011-10-18
2011-01-2727
The design concept is completely modular, which offers unique versatility in a drill motor which quickly can be configured to meet any application in its niche. Designed to meet today's torque requirements, PFD 1500 mitigates many of the quality problems normally experienced with the use of positive feed drills.
Technical Paper

Selection of a Brushless DC Motor Employed to Propel an Electric Car

2011-10-04
2011-36-0246
This work presents the results of the development of a small electric car and the study of a Brushless DC Motor, employed to propel the electric car. The aim was selecting a motor with characteristics of operation suited to propel the electric car at a speed from 12 to 20 km/h. ...The propulsion system has a brushless DC motor and an electronic control unit. The electronic control unit was designed and constructed based on the characteristics of the selected brushless motor. ...The electronic control unit was designed and constructed based on the characteristics of the selected brushless motor. Tests were carried out on the electric car, with the purpose of determining the behavior of the mechanical power required by it, as a function of speed.
Journal Article

Modeling of Ducted-Fan and Motor in an Electric Aircraft and a Preliminary Integrated Design

2018-10-04
For the state-of-the-art electric ducted-fan, motor cooling restricts the power density increase. A motor design model based on the fan hub-to-tip ratio proposed in this article reveals that the thermal coupling effect between fan aerodynamic design and motor cooling design has great potential to increase the power density of the motor in an electric propulsion system. ...A motor design model based on the fan hub-to-tip ratio proposed in this article reveals that the thermal coupling effect between fan aerodynamic design and motor cooling design has great potential to increase the power density of the motor in an electric propulsion system. ...Parametric study on a current 6 kW electric ducted-fan system shows that the highest motor power density could be increased by 246% based on the current technology. Finally, a preliminary design was obtained and experiments were conducted to prove the feasibility of the model.
Technical Paper

Design, Development, and Demonstration of a High-Pressure, Overcenter, Variable-Displacement Hydraulic Motor

1990-09-01
901794
This approach contrasts with traditional systems that are normally controlled through a large servovalve which throttles flow across the motor control ports. By connecting the variable-displacement hydraulic motor (VDHM) motor directly to supply and return and controlling through wobbler modulation, the need for a large throttling servovalve with its associated flow losses is eliminated. ...This document presents and discusses the design, development, and demonstration of a 3,000 to 8,000 psi (207 to 552 bar) electronically controlled, overcenter, variable-displacement hydraulic motor (VDHM) in which output speed and position control are effected solely through wobbler position control.
Technical Paper

Development of a Hot Gas Vane Motor for Aircraft Starting Systems

1986-10-01
861714
Design, analyses, and tests have been conducted on a double-cavity (pressure-balanced) hot gas vane motor suitable for aircraft APU starting over the temperature range of −65°F to +130°F (−54° to +54°C). ...Testing of the motor was accomplished with H-70 (70% hydrazine, 30% water) monopropellant hot gas decomposition products. ...Testing of the motor was accomplished with H-70 (70% hydrazine, 30% water) monopropellant hot gas decomposition products. Motor development focused on testing minor modifications aimed at eliminating vane breakage. The performance goals (zero to 8,800 rpm in 8 to 10 seconds) were achieved after approximately 40 tests.
Technical Paper

Automation of the Space Shuttle Solid Rocket Motor Assembly Process

1997-06-03
972234
The Space Shuttle's Solid Rocket Motor (SRM) processing equipment for motor assembly at NASA's John F. Kennedy Space Center, was designed in the mid 1980's. ...The SRM Stacking Enhancement Tool (SSET) project was initiated to update and automate the motor assembly process. The SSET project is replacing the existing segment processing data acquisition panels and incorporating the Segment Shape Prediction Program (SSPP) into a single panel providing updated processors and an intuitive “smart” graphical user interface with the capability of recording all data.
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