AIAA - American Institute of Aeronautics and Astronautics

AIAA SP-084

1999-01-01T00:00:00Z

AIAA SP-084; Fire, Explosion, Compatibility, and Safety Hazards of Hypergols - Hydrazine AIAA - American Institute of Aeronautics and Astronautics Hydrazine is a colorless, corrosive, strongly reducing liquid compound. Current aerospace applications include its use in the Space Transportation System as a fuel for the auxiliary power units, in satellites as a monopropellant for thrusters, and in jet aircraft as fuel for auxiliary power sources. Although hydrazine is immensely useful in these applications, there are also drawbacks. For example, hydrazine vapor is flammable and detonable; both liquid and vapor hydrazine are corrosive, react with many materials, and are susceptible to catalytic decomposition; and hydrazine is highly toxic. The users and designers of hydrazine systems must be aware of these hazards and safeguard against them.
This AIAA Special Report preserves the text of NASA document RD-WSTF-0002 Rev A, December 17, 1998, "Fire, Explosion, Compatibility, and Safety Hazards of Hydrazine," developed by the NASA White Sands Test Facility for the Propulsion and Power Division of the Lyndon B. Johnson Space Center and the Air Force Space Division. In the interests of technology transfer, custody of the material was assigned to AIAA through of Memorandum of Understanding dated February 1999. One of the purposes of this Memorandum is to provide broader distribution of the valuable information developed and published in the original manual.
The authors of the NASA Revision A manual, dated December 16, 1998 are: Stephen S. Woods, Donald B. Wilson, Dennis D. Davis, Michelle Barragan, Walter Stewart, Radel L. Bunker, and David L. Baker. Authors to the earlier 1990 edition are: Michael D. Pedley, David L. Baker, Harold D. Beeson, Richard C. Wedlich, Frank J. Benz, Radel L. Bunker, and Nathalie B. Martin.
AIAA Special Reports are a part of the AIAA Standards Program and frequently serve as precursors to formal consensus documents. This publication is under the purview of the Liquid Propulsion Committee on Standards, the group responsible for determining the future of the publication and for maintaining it in a technically current state.
The AIAA Standards Procedures provide that all approved standards, recommended practices, and guides are advisory only. Their use by anyone engaged in industry or trade is entirely voluntary. There is no agreement to adhere to any AIAA standards publication and no commitment to conform to or be guided by any standards report. In formulating, revising, and approving standards publications, the Liquid Propulsion Committee on Standards will not consider patents that may apply to the subject matter. Prospective users of the publications are responsible for protecting themselves against liability for infringement of patents, or copyrights, or both.

AIAA G-043A

2012-01-01T00:00:00Z

AIAA G-043A; Guide to the Preparation of Operational Concept Documents AIAA - American Institute of Aeronautics and Astronautics This Guide outlines the operational concept definition process and how it may be applied. The main emphasis of this document is to provide practical recommendations on how to perform an operational concept definition activity with the focus on the OCD because that is the physical product in which the results of the work are captured.
This Guide is applicable for the procurement of systems, including ground systems, and associated equipment/subsystems.
Purpose
The purpose of this Guide is twofold. First, the Guide describes a time-tested process for operational concept development. Second, it is intended to recommend how to compile the information developed during operational concept development into one or more Operational Concept Documents (OCDs) encompassing the full range of the product lifecycle (Haskins, 2010): concept, development, production, utilization, support, and retirement stages.

AIAA S-133-4

2013-01-01T00:00:00Z

AIAA S-133-4; Space Plug-and-Play Architecture Standard Physical Interface AIAA - American Institute of Aeronautics and Astronautics Mechanical, thermal and electrical connector interface requirements are contained in this document. These requirements include details of the mounting hole pattern, fastener clearance-hole sizes, and thermal control approaches.
Reporting requirements for mechanical and thermal design data, such as mass, center of gravity, envelope, radiator and heater locations, and so forth are described.
This standard does provide some limited electrical interface requirements. Electrical power service requirements are included in AIAA S-133-5-2013. A more extensive common reference for both standards is AIAA S-122-2007, Electrical Power Systems for Unmanned Spacecraft. This document identifies the significant features of the SPA interface connector(s) and the associated cabling to allow SPA device and cable manufacturers to build systems that interconnect successfully with SPA-enabled spacecraft. The connector type and pin assignments are described, along with definitions of connector gender and mechanical mounting. Requirements are provided for the associated cabling, including details of shielding, shield termination, insulation and cable impedance
Optional SPA connector interfaces are described in the following sections by type (i.e., Type A, Type B, etc.)

AIAA S-102.1.5

2009-01-01T00:00:00Z

AIAA S-102.1.5; Performance-Based Failure Review Board (FRB) Requirements AIAA - American Institute of Aeronautics and Astronautics This document, when followed in its entirety, will yield a robust EPS design suitable for very high-reliability space missions. This document specifies general design practices and sets minimum verification and validation requirements for power systems of unmanned spacecraft. The focus of the document is on earth orbiting satellites using traditional photovoltaic/battery power, but does not exclude other primary power generation and storage methods. This document does not address specific launch vehicle requirements however much of the design philosophy used here is applicable to launch vehicle power systems.