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An integration study was performed coupling an SP-100 reactor with either a Brayton or Stirling power conversion subsystem. A power level of 100 kWe was selected for the study. The power system was to be compatible with both the lunar and Mars surface environment and require no site preparation. In addition, the reactor was to have integral shielding and be completely self-contained, including its own auxiliary power for start-up. Initial reliability studies were performed to determine power conversion redundancy and engine module size. Previous studies were used to select the power conversion optimum operating conditions (ratio of hot-side temperature to cold-side temperature). Results of the study indicated that either the Brayton or Stirling power conversion subsystems could be integrated with the SP-100 reactor for either a lunar or Mars surface power application.

This SAE Aerospace Information Report (AIR) describes procedures for use in the field to determine if 115/200 Volt, 400 Hz aircraft external electrical power connectors are excessively worn, which may result in the inability of the external power plug to be retained, intermittent electrical performance and arcing.

This SAE Aerospace Information Report (AIR) describes procedures for use in the field to determine if 115/200 Volt, 400 Hz aircraft external electrical power connectors are excessively worn, which may result in the inability of the external power plug to be retained, intermittent electrical performance and arcing.

Governmental assurance documentation bibliography updated; new tabulation effective as of April 1, 1967. Latest revision indicated in all instances, but no attempt was made to list supplements or amendments. Department of Defense Index of Specifications and Standards (DODISS) published annually in three parts (alphabetic, numerical, and listing of Federal Supply Classification following unclassified documents.

In order to take full advantage of SiC, a high temperature package for power module using SiC devices was designed, developed, fabricated and tested. The details of the material selection and fabrication process are described. High temperature reliability test and power test shows that the package presented in this paper can perform well at the high junction temperature.

The objective of this project was to replace electromechanical power line contactors with a Static Transfer Switch (STS) to improve the transfer of electrical power between aircraft generators and decrease required maintenance. The switch requirements include high reliability, lightweight, and high speed (less than 15mS) power transfer. An STS can shorten the bus transfer time to less than the “ride-through” of aircraft electronic loads and therefore have the ability to control and transfer electrical power while maintaining critical mission requirements. The content of this paper and presentation will discuss the initial problem, the research and development approach, design, and initial testing of the STS.

이 문서는 공급자가 9100의 조항을 준수하고자 할 때 AQAP-2110을 적용하는 것에 관한 정보와 지침을 제공하기 위해 작성 및 발행된 것이다. 이 문서는 AQAP-2110-SRD.2 및 IA9137로 간행된다. 이는 NATO와 산업계에서 AQAP-2110과 9100 간의 관계에 대한 이해와 활용을 촉진하기 위해 NATO와 산업계 대표들이 공동으로 작성한 것이다. 획득 국가가 자국의 조달 방법으로 대외군사판매(FMS)를 이용할 때는 AQAP가 필요할 수 있다. 이 문서는 획득 국가와 9100을 준수하고자 하는 공급 국가의 AQAP-2110 요구사항 해석에 있어 공통성을 제공하는 데에 목적을 두고 있다. 이 문서의 내용은 법적 또는 계약상의 지위를 갖지 않으며, 일체의 AQAP-2110 또는 9100 요구사항을 대체하거나 그 요구사항에 추가되는 것도 아니다. 있을 수 있는 조건의 다양성(작업 또는 공정의 유형, 사용 기기 및 관련 인원의 역량에 따르는) 때문에, 이 지침이 모든 것에 적용되는 것으로 간주하거나, 계약 요구사항 충족에 필요한 특정 수단 또는 방법을 강요하는 것으로 간주해서는 안 된다. 이해당사자들은 이러한 요구사항을 충족하기 위해 다른 수단 또는 방법을 사용할 수도 있다는 점을 알고 있어야 한다. 이 지침 사용자는 계약서에 명시되는 바와 같이 AQAP 2110 요구사항이 공급자와 하청업체가 지켜야 하는 의무사항임을 명심해야 한다.

この文書は、供給者が9100の規定を遵守する場合の、AQAP-2110の適用に関する情報及びガイダンスを提供するために作成され、発行された。この文書は、AQAP-2110-SRD.2及びIA9137として発行されている。この文書は、NATO及び業界によるAQAP-2110及び9100の関係の理解及び利用を容易にするために、NATO及び業界の代表者が協同で策定した。AQAPは、調達国が対外有償軍事援助（FMS）を調達手段として利用する場合に、必要となる場合がある。 この文書の目的は、調達者及びその9100供給者によるAQAP-2110要求事項の解釈の共通化に寄与することである。 この文書の内容は法的位置づけも契約上の位置づけも有せず、AQAP-2110の要求事項又は9100の要求事項のいずれに対しても取って代わるものでも、追加するものでも、削除するものでもない。 様々な状況が、作業、工程の種類、又は使用される機器、及び関わる要員のスキルのような要因に左右されて存在し得るため、このガイダンスは網羅的なものと見なされることも、また、契約書の要求事項を満たすための特定の手段や方法を義務付けるものと見なされることも望ましくない。ステークホルダーは、これらの要求事項を満たすために、他の手段や方法が使用され得ることを認識すべきである。 このガイダンスの利用者は、AQAP 2110要求事項が、契約書に引用されているとおり、供給者や二次供給者に義務付けられていることに留意することが望ましい。

Certain standard parts in the aerospace industry require qualification as a prerequisite to manufacturing, signifying that the manufacturer’s capacity to produce parts consistent with the performance specifications has been audited by a neutral third-party auditor, key customer, and/or group of customers. In at least some cases, a certifying authority provides manufacturers with certificates of qualification which they can then present to prospective customers, and/or lists qualified suppliers in a Qualified Parts List or Qualified Supplier List available from that qualification authority. If this list is in an infrequently updated and/or inconsistently styled format as might be found in a print or PDF document, potential customers wishing to integrate qualification information into their supplier tracking systems must use a potentially error-prone manual process that could lead to later reliance on out-of-date or even forged data.

This paper discusses various engine installations in Naval aircraft, looking especially at their costs of maintenance. Fuel systems, fuel control systems, and several engine accessories are discussed for present and future engines. It is concluded that simple, reliable equipment is necessary to keep aircraft in the air instead of in maintenance areas on the ground.

An electrical system composed of an integral main engine electrical starter/generator and a power management and distribution system for a high performance more electric airplane is presented. The paper emphasizes the fault tolerance and high reliability requirements and discusses the necessary architecture to satisfy them. A number of critical technical issues associated with the more electric airplane, such as severe EMI environment, regenerative power, and system integration and stability are discussed.

A number of specimen life performance tests were conducted on three test lubricants selected to demonstrate their gross ranking capabilities. The results indicated that the test rigs should be used only for gross ranking. A large difference in magnitude of life values were obtained even though agreement in gross ranking was obtained by three out of the five participating laboratories. Further testing is recommended under preselected test conditions and lubricants.

Several quite different waste-water processing subsystems have been tested for space mission applications. Mission choice, and choice of priority for further development, involves processor requirements for (electrical) power, launch and resupply weights, and space occupied, and developmental factors of reliability and reparability. For each subsystem one can identify theoretical power, etc., requirements, and current realistic requirements, and potential realistic subsystem requirements. Compared are reverse osmosis, vapor-compression-distillation, and TIMES processes, in terms of power, weight, and space requirements. Discussions of electrodialysis and CELSS are included as components of water treatment systems.

The paper defines a “best” estimate of system effectiveness or reliability as one that minimizes the potential loss due to either overestimating or underestimating such a system figure of merit. A loss function is expressed in terms of the decision maker's order of preference for the consequences of either overestimation (underkill) or underestimation (overkill). However, in order for an estimate to be optimal, sufficient information at the system level should be provided. This lack or abundance of information is reflected in the variability of the measurement of system effectiveness or reliability. The variability and central tendency of this measurement are obtained from the variability and central tendency of the component data. This is achieved through the combined use of effectiveness or reliability models, Monte Carlo simulation and/or probability moments, and Bayesian statistics.

The Hubble Space Telescope (HST) was designed to be serviced from the shuttle by astronauts performing extravehicular activities (EVA). During the first HST Servicing Mission (STS-61) two types of power tools were flown, the Power Ratchet Tool (PRT) and the HST Power Tool. Each tool had both benefits and drawbacks. An objective for the second HST servicing mission was to combine the reliability, accuracy, and programmability of the PRT with the pistol grip ergonomics and compactness of the HST Power Tool into a new tool called the EVA Pistol Grip Tool (PGT). The PGT is a self-contained, microprocessor controlled, battery powered, 3/8-inch drive hand-held tool. The PGT may also be used as a non-powered ratchet wrench. Numerous torque, speed, and turn or angle limits can be programmed into the PGT for use during various servicing missions. Batteries Modules are replaceable during ground, Intravehicular Activities (IVA), and EVA operations.

A general computer program has been developed for analytic fatigue crack growth. It is designed so that the user does not need to have an extensive background in Fracture Mechanics Theory. This FORTRAN program can analyze the growth of most common types of cracks and accounts for the transition from part-thru to completely thru-the-thickness crack. The input loading may be a mission profile or arbitrary cyclic stresses with or without concentrated loads and may be repeated a number of times. There are built-in corrections for geometry, plastic-zone size, plane-stress vs. plane-strain and applicability of Linear-Elastic-Fracture-Mechanics, and there are options available for crack growth rate calculations, retardation models and plastic zone corrections.

The technological advances which have been made in the computer hardware industry, from interactive computer graphics systems to numerically controlled manufacturing and inspection machines, has resulted in major changes in the impeller design process. The contents of this paper describes an “Interactive CAD/CAM Geometric Modeling System for Impellers” developed to integrate aerodynamic design, mechanical design, structural and dynamics analysis, manufacturing and quality assurance into an integrated CAD/CAM impeller system. The system allows for more design and analysis iterations to take place in a short time frame, resulting in optimized impeller designs. The system also reduces the lead time required for part fabrication and inspection from many months to a few weeks.

Future vehicle power systems must achieve greater flexibility and reliability than those used in previous generations. New functions that enhance safety, such as arc detection and wiring integrity verification, are essential for new systems. Embedded autonomous control, and fault correction can be built into Fault Tolerant Processors that integrate into a vehicle Open System Architecture. This approach will provide status and fault detection information to maintenance interfaces and provide fault correction. Safety is enhanced by the prevention of dangerous restarts from crew and personnel. The embedded features allow for pre-flight mission configuration to setup systems before takeoff and on-board and off-board maintenance control. This enables operators to evaluate power system health and history to help reduce turn around time.