Browse Topic: Protective clothing

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This SAE Aerospace Recommended Practice (ARP) provides recommended practices for the cleaning of aircraft oxygen equipment, both metallic and non-metallic articles, such as oxygen lines (tubes, hoses, etc.), components (including regulator and valve parts), cylinders, and ground-based equipment that may be used to support aircraft oxygen systems. This document also specifies work area details, methods for selecting suitable cleaning agents, cleaning methods, and test methods for verifying levels of cleanliness. The cleanliness coding scheme specified in this document provides a method for documenting minimum cleanliness level requirements and for identifying compliance.
A-10 Aircraft Oxygen Equipment Committee
ABSTRACT Previous efforts demonstrated the ability to achieve a 30% weight reduction for a MIL-DTL-27422D Phase I test cube construction with Protection Level A gunfire performance, using a lightweight 2-ply exoskeleton design to replace the 4-ply construction otherwise required to meet crash impact test requirements. An additional 20% reduction in weight was projected by replacing the natural gum rubber (NGR) used in conventional fuel bladder constructions with a lightweight formulation. This paper reviews the technical efforts executed to support the transition of the lightweight exoskeleton construction to the Apache AH-64 helicopter. The fuel bladders made with the lightweight sealant were 15.5% lighter for the AH-64 FWD fuel bladder and 13.2% lighter for the AFT. Additional weight savings based on the 2-ply exoskeleton construction was not realized as the existing AH-64 fuel bladders are already relatively lightweight constructions. The final AH-64 fuel bladders demonstrated the ability to be qualified to all MIL-DTL-27422E performance requirements; however, the program concluded without demonstrating Protection Level A gunfire performance. Importantly, there did not appear to be any discernable difference in the self-sealing performance of the fuel bladders made with the lightweight sealant and the constructions based on conventional NGR sealant. While additional work may be required to address this performance deficiency, there were several issues that were noted during the Phase II gunfire testing that should be reviewed and resolved prior to additional testing.
Heater, KennethPilati, BryanWhipple, Matt
Metering structures of remote sensing instruments often have large openings or access holes. Shear panels that are X-shaped, such as those proposed for the Neutron Star Interior Composition Explorer (NICER), generally consist of C-channels and L-brackets to minimize structural distortion. This type of metering structure has large openings on the sides. Structural panels that have large access holes, such as those studied for the Landsat Operational Land Imager (OLI), generally consist of aluminum honeycomb panels with composite facesheets. Both types of metering structure require multilayer insulation (MLI) blankets to shield the internal components such as optics from sunlight and Earth albedo, and to minimize heat loss to 3K space by radiation. The issues of conventional MLI blankets for these metering structures include MLI sagging, stray light, and risk of micrometeoroid damage to optics.
Currently, lead and lead-based materials are used to fabricate shields not only for X-rays, but also for other types of radiation. With the growing environmental concern about the toxicity of lead, and the high costs associated with transporting heavy lead-based shields in spacecraft, alternatives are needed for fabricating X-ray shields that are less toxic and lighter.
ABSTRACT One of the most famous of Augustine's Laws involved the ever-escalating costs of aircraft over time. Law Number XVI states, "In the year 2054, the entire defense budget will purchase just one aircraft. This aircraft will have to be shared by the Air Force and Navy 3- 1/2 days each per week except for leap year, when it will be made available to the Marines for the extra day." This particular reference involved tactical aircraft but the same trend can be observed for other types of military hardware. This paper addresses and attempts to explain this phenomenon as it applies to the rotorcraft industry. For example, increasing demand for more survivable rotorcraft, and more survivable payloads that must be carried by rotorcraft (eg., HMMWVs, soldier body armor, etc.), result in not only higher unit costs but in higher mission costs.
Streich, Eric
Effects of Sinusoidal Whole Body Vibration Frequency on Drivers' Muscle Responses2015-01-13964/14/2015
Low back pain has a higher prevalence among drivers who have long term history of vehicle operations. Vehicle vibration has been considered to contribute to the onset of low back pain. However, the fundamental mechanism that relates vibration to low back pain is still not clear. Little is known about the relationship between vibration exposure, the biomechanical response, and the physiological responses of the seated human. The aim of this study was to determine the vibration frequency that causes the increase of muscle activity that can lead to muscle fatigue and low back pain. This study investigated the effects of various vibration frequencies on the lumbar and thoracic paraspinal muscle responses among 11 seated volunteers exposed to sinusoidal whole body vibration varying from 4Hz to 30Hz at 0.4 g of acceleration. The accelerations of the seat and the pelvis were recorded during various frequency of vibrations. Muscle activity was measured using electromyography (EMG). The results demonstrated that peak muscle response from both upper and low back occurred at 5-6 Hz frequencies, which are also reported frequencies of peak transmissibility in vertical direction. The peak muscle response occurred at frequencies of peak transmissibility indicates that higher stretch amplitude of spinal muscle during resonant frequencies mainly induce the greater muscle activity. Those findings help us better understand the fundamental mechanism of driving discomfort and low back pain and avoid noxious vibration during NVH (noise-vibration-harshness) designs.
Meng, XiangjieTao, XinWang, WenjunZhang, ChaofeiCheng, BoWang, BoZhou, ChengpengJin, XiaopingZeng, ChaoCavanaugh, JohnChen, Chaoyang
Improved Mobility with a Neutral, Motion-Amplifying Controller for an Experimental Exoskeleton2015-01-14004/14/2015
The number of seniors is rising worldwide. Exoskeleton devices can help seniors regain their lost power, balance, and agility, thus improving their quality of life. Exoskeleton devices and control strategies assist human gait. A common strategy is to use oscillator-based controllers, which “lock in” with the gait and help the subject walk faster using a phase lead characteristic. Such strategies are limited to gait assist only and are less effective in more general movements. These controllers can be detrimental in critical cases such as when the leg needs to execute a fast reactive stepping to stop a fall. We present a control strategy for a hip exoskeleton, which assists human leg motion by providing motion amplification at the hip joint. The controller is “neutral” because it assists any leg motion, not only a gait, and can help avoid falls by assisting reactive stepping. Our control strategy modifies the joint dynamics of the coupled human-exoskeleton system such that the desired dynamic response is achieved while guaranteeing stability. We define assistance as reducing the impedance and increasing the admittance of the coupled system. The dynamic response of the leg is defined by the frequency response profile of the magnitude of integral admittance (torque-to-angle relationship) of the coupled human-exoskeleton system, and assistance occurs when this profile is higher than that of the unassisted leg for all frequencies of interest. Our controller produces hip joint motion amplification and results in larger and faster leg swing motions, and can help recover the seniors' power and agility.
Nagarajan, UmashankarGoswami, Ambarish
Proposed Androgynous Docking Airlock/Utility Module2009-01-25857/12/2009
The objective of this paper is to detail a proposal for an Androgynous Docking Airlock/Utility Module (ADAM) that would allow extravehicular (EVA) crews, working from the Orion spacecraft, to avoid depressurizing the command module of the Orion vehicle for planned EVA repair, maintenance and interdiction of orbital structures. Unlike the Space Shuttle, Russian Soyuz vehicle or the Chinese Shenzhou manned spacecraft, the proposed Orion space vehicle has no airlock. This necessitates the depressurizing of the entire Command Module cabin during EVA activity. It also means that all crewmembers will have to wear space suits during contingency and planned EVAs. This inordinately dangerous situation will require all crewmembers to be exposed to the space vacuum for as much as seven hours or more if a working EVA becomes necessary. It also means that if an airlock is not employed on Orion, as indeed none is presently envisioned, the space suits the crew wears will be severely compromised in design as they will have to be employed as EVA suits and emergency launch/escape suits as well, a function that is preclusive on design, engineering and optimization levels. The ADAM module, which is a lightweight, disposable, inflatable airlock/utility carrier, could be launch separately by SpaceX Corporation from launch Complex 40 at Cape Canaveral Air Force Station. Following the successful launch and orbit of the manned Orion spacecraft, ADAM would be launched into a similar orbit. Upon reaching orbit ADAM would automatically inflate, initiate its beacon and radar transponder. With the Orion orbiter acting as the active vehicle, the two spacecraft would rendezvous and dock in a manner not unlike that of the old Gemini/Agena docking system of the 1960s. The ADAM module is deflated and tightly packed during the launch phase. This allows the module to impose the least stowage penalty within the launch shroud and also the least mass, thus, it can be launched by a relatively small booster utilizing the smallest payload fairing dimensions. On the forward and aft ends of the inflatable, cylindrical ADAM module are rigid structural hemispheres with a docking adaptor on the side interfacing to the Orion Vehicle. On the opposite end is an airlock hatch/docking adaptor. Between the two hemispherical ends the ADAM module is composed of a rugged fabric outer restraint layer (to hold the module into a cylindrical shape) and underneath is a polyurethane/Nylon bladder to hold in airlock life support gasses/pressure. Covering both is a thermal-micrometeoroid layer. When the ADAM module is sealed off from the Orion Command Module and deflated during EVA activity, aerobeams running longitudinally (as part of the inner bladder) along the modules fore-aft length, would maintain the shape/geometry of the inflatable structure. Stowed inside the ADAM module hemispherical ends are two EVA space suits, and their supporting equipment and tools, etc. Also stowed in the ADAM module would be a lightweight fan and carbon dioxide scrubber to enhance and work with the Orion's life support system. When the planned EVA activity is completed at mission termination, tools, etc. are stowed inside the upper torsos of the EVA space suits and they are then transferred into the Orion Command Module, strapped into two unused seats, and are deorbited, along with the Orion vehicle, to be used again for future missions. The ADAM module is undocked from the Orion vehicle and allowed to deorbit and burn up upon eventual atmospheric reentry.
Harris, Gary L.de León, Pablo
Development and Testing of the First Full Pressure Suit for Non-Governmental Commercial Spaceflight2009-01-24977/12/2009
The objective of this paper is to detail the development of the DL/H-1 full pressure suit, which was developed by De Leon Technologies LLC, with the assistance of the University of North Dakota. The DL/H-1 was specifically developed to fulfill the needs for a full pressure suit for private spaceflight in case of decompression or in the need of bailout of the spacecraft. This work also details the objectives, basis for design, problems encountered by the designers, final development of the DL/H-1 full pressure suit and testing in the high altitude chamber at the School of Aerospace Sciences at the University of North Dakota. The authors believe that during experimental flights of private spaceflight, orbital or suborbital a full pressure suit will be required to augment safety during all flight phases where in the case of cabin pressure loss, without personal protection, the loss of crew and vehicle could result. This paper explains the different steps being performed by the authors, who designed and built a flight hardware pressure suit that can meet the physiological and comfort requirements of the tourist suborbital industry and the early commercial private spaceflight community. The suborbital tourist and commercial spaceflight industry have unique problems confronting the pressure suit builder, such as unpressurized comfort, reasonable expense, unique sizing of the general population, decompression complications of persons not fitting a military physiology profile and equipment weight issues.
de León, PabloHarris, Gary L.
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