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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.

Sundstrand has been investigating 270-Vdc/hybrid 115-Vac electrical power generating systems (EPGS) technology in preparation for meeting the electrical power generating system (EPGS) requirements for future aircraft (1). Systems such as the one being investigated are likely to be suitable for the More-Electric Aircraft (MEA) concepts presently under industry and military study. The present Sundstrand single-channel testbed is being further expanded to better understand the electrical system performance characteristics and power quality requirements of an MEA in which traditional mechanical subsystems are replaced by those of a “more-electric” nature. This paper presents the most recent Sundstrand 270-Vdc system transient performance data, and describes the modifications being made to the 270-Vdc/hybrid 115-Vac testbed.

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.

Vertical-Junction-Field-Effect-Transistors (VJFETs) are currently the most mature SiC devices for high power/temperature switching. High-voltage VJFETs are typically designed normally-on to ensure voltage control operation at high current-gain. However, to exploit the high voltage/temperature capabilities of VJFETs in a normally-off high-current voltage-controlled switch, high-voltage normally-on and low-voltage normally-off VJFETs were connected in the cascode configuration. In this paper, we review the high temperature DC characteristics of VJFETs and 1200 V normally-off cascode switches. The measured parameter shifts in the 25°C to 300°C temperature range are in excellent agreement with theory, confirming fabrication of robust SiC VJFETs and cascode switches.

The 757/767 Flight Management System provides the initial operational implementation of an integrated guidance, control and display equipments based upon digital technology for commercial transport airplanes. The applied equipments are based upon the new ARINC 700 series characteristics developed by the Industry over the past five years. These characteristics were developed on the basis of limited operational experience with selected elements of the system and upon R&D efforts within the Industry. The System features automatic/manual flight profiles for optimum economics, all weather landing including rollout guidance, electronic primary flight instruments based on color (shadow mask) CRTs, inertial attitude/velocity reference based upon laser gyros, improved caution/warning and other improved performance/functional features. The system also provides significant improvements in line and shop maintenance features.

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。

In the course of CRYOSYSTEM phase B (development phase) financed by the European Space Agency, AIR LIQUIDE (France) and Astrium Space Infrastructure (Germany) have developed an optimized design of a −183°C freezer to be used on board the International Space Station for the freezing and storage of biological samples. The CRYOSYSTEM facility consists of the following main elements: - the CRYORACK, an outfitted standard payload rack (ISPR) accommodating up to three identical Vial Freezers - the Vial Freezer, a dewar vessel capable of fast and ultra-rapid freezing, and storing up to approximately 900 vials below −183°C; the dewar is cooled by a Stirling machine producing > 6 W at 90 K. The Vial Freezer is operational while accommodated in the CRYORACK or attached to the Life Science Glovebox (LSG). One CRYORACK will remain permanently on-orbit for several years while four Vial Freezers and two additional CRYORACKs support the cyclic upload/download of samples.

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.

Some of the methods used for experimental detection and examination of wake vortices are presented. The aim of the article is to provide the reader a brief overview of the available methods. The material is divided into two major sections, one dealing with methods used primarily in the laboratory, and the second part devoted to those used in field operations. Over one hundred articles are cited and briefly discussed.

Europe has embarked on a new programme of space exploration involving the development of rover, lander and probe missions to visit planets, moons and near Earth objects (NEOs) throughout the Solar System. Rovers and landers will require testing under simulated planetary, and NEO conditions to ensure their ability to land on and traverse the alien surfaces. ESA has begun work on a building project that will provide an enclosed and controlled environment for testing rover and lander functions such as landing, mobility, navigation and soil sampling. The facility will first support the European ExoMars mission due for launch in 2013. This mission will deliver a robotic rover to the Martian surface. This paper, the first of several on the project, gives an overview of its design configuration and construction phasing. Future papers will cover its applications and operations.

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.