1、Standard AIAA S-133-5-2013 1 S-102.2.5-2009 Space Plug-and-Play Architecture Standard 28V Power Service AIAA standards are copyrighted by the American Institute of Aeronautics and Astronautics (AIAA), 1801 Alexander Bell Drive, Reston, VA 20191-4344 USA. All rights reserved. AIAA grants you a licens
2、e as follows: The right to download an electronic file of this AIAA standard for storage on one computer for purposes of viewing, and/or printing one copy of the AIAA standard for individual use. Neither the electronic file nor the hard copy print may be reproduced in any way. In addition, the elect
3、ronic file may not be distributed elsewhere over computer networks or otherwise. The hard copy print may only be distributed to other employees for their internal use within your organization. AIAA S-133-5-2013 Space Plug-and-Play Architecture Standard 28V Power Service Sponsored by American Institu
4、te of Aeronautics and Astronautics Approved November 2012 Abstract The SPA 28V power service is a battery-clamped power bus that may vary with battery charge from 22V to 34V during normal operations. This power service is subject to transient behavior, such as voltage ripple, spikes, and surges, whi
5、ch must be accounted for in the design of SPA components. The SPA 28V Power Service Standard establishes requirements for SPA component and spacecraft grounding, bonding, and isolation. AIAA S-133-5-2013 ii Published by American Institute of Aeronautics and Astronautics 1801 Alexander Bell Drive, Re
6、ston, VA 20191 Copyright 2013 American Institute of Aeronautics and Astronautics All rights reserved No part of this publication may be reproduced in any form, in an electronic retrieval system or otherwise, without prior written permission of the publisher. Printed in the United States of America I
7、SBN 978-1-62410-233-2 AIAA S-133-5-2013 iii Contents Foreword v Introduction vii 1 Scope 1 2 Tailoring. 1 3 Applicable Documents . 1 4 Vocabulary 1 4.1 Acronyms and Abbreviated Terms 1 4.2 Terms and Definitions . 2 5 SPA 28V Power Service 2 6 General Power Performance Requirements 3 6.1 Main Power B
8、us Voltage . 3 6.2 SPA Endpoint Current Limits . 3 6.3 Use of Multiple SPA Endpoints 3 6.4 Main Bus Voltage Ripple . 4 6.5 Main Bus Current Ripple . 4 6.6 Main Bus Impedance . 5 6.7 Main Bus Sustained Under-Voltage Condition 6 6.8 Main Bus Sustained Over-Voltage Condition 6 6.9 Main Power Bus Voltag
9、e Transients . 6 7 4.5A Power Service . 7 7.1 SPA 4.5A Device In-Rush Current Limits . 7 7.2 4.5A SPA Endpoint Over-Current Fault Conditions . 7 8 30A Power Service 7 8.1 SPA 30A Device In-Rush Current Limits . 7 8.2 SPA 30A Endpoint Over-Current Fault Conditions 7 9 50A Power Service 8 9.1 SPA 50A
10、Device In-Rush Current Limits . 8 9.2 SPA 50A Endpoint Over-Current Fault Conditions 8 10 SPA Grounding and Bonding 8 10.1 Grounding 8 10.2 SPA Component Bonding 9 Figures Figure 1 SPA power subsystem configuration 3 AIAA S-133-5-2013 iv Figure 2 MIL-STD-461E (CE102) EMC requirements . 4 Figure 3 MI
11、L-STD-461E (CE101) EMC requirements . 5 Figure 4 Power bus source impedance limits 6 Figure 5 SPA spacecraft arounding approach 9 AIAA S-133-5-2013 v Foreword This standard was developed through a partnership of the Air Force Research Laboratory Space Vehicles Directorate, the Air Force Office of Op
12、erationally Responsive Space, numerous government contractor teams, independent contractor teams, and academic experts. The Space Plug-and-Play Architecture (SPA) is a collection of standards developed to facilitate rapid constitution of spacecraft systems using modular components. In order for a SP
13、A system to meet expected performance requirements, the SPA components and spacecraft must conform to a consistent and widely agreed upon grounding approach. This document includes specifications for SPA component and spacecraft grounding, bonding, and isolation. The Power standard identifies signif
14、icant features and grounding approaches for SPA power systems. The intent of this document is to allow SPA designers and manufacturers to provide components and/or subsystems that successfully interface with SPA-enabled spacecraft. This particular volume of the SPA 28V Power Service Standard contain
15、s information not recorded in previous documentation. It is part of a set of 10 documents describing other components of the standard: SPA Guidebook SPA Networking Standard SPA Logical Interface Standard SPA Physical Interface Standard SPA System Timing Standard SPA Ontology Standard SPA Test Bypass
16、 Standard SPA SpaceWire Subnet Adaptation Standard SPA System Capability Guide At the time of approval, the members of the AIAA SPA Committee on Standards were: Fred Slane, Chair Space Infrastructure Foundation Jeanette Arrigo Sierra Nevada Corporation Scott Cannon Utah State University Ken Center P
17、nP Innovations Don Fronterhouse* PnP Innovations Rod Green Design Group Jane Hansen HRP Systems Doug Harris Operationally Responsive Space Office Paul Jaffe Naval Research Laboratory Stanley Kennedy* Comtech Aero-Astro Ronald Kohl R.J. Kohl & Associates Bill Kramer Independent AIAA S-133-5-2013 vi R
18、amon Krosley Independent Denise Lanza SAIC James Lyke Air Force Research Laboratory Joseph Marshall BAE Systems Gerald Murphy* Design Group Gary Rodriguez sysRand Steven Schenk Comtech Aero-Astro Robert Vick* SAIC The above consensus body approved this document in June 2012. The AIAA Standards Execu
19、tive Council (VP-Standards, Laura McGill, Chairperson) accepted the document for publication in November 2012. The AIAA Standards Procedures dictates that all approved Standards, Recommended Practices, and Guides are advisory only. Their use by anyone engaged in industry or trade is entirely volunta
20、ry. There is no agreement to adhere to any AIAA standards publication and no commitment to conform to or be guided by standards reports. In formulating, revising, and approving standards publications, the committees on standards will not consider patents that may apply to the subject matter. Prospec
21、tive users of the publications are responsible for protecting themselves against liability for infringement of patents or copyright or both. _ *Alternate CoS ParticipantAIAA S-133-5-2013 vii Introduction The SPA 28V power service is a battery-clamped power bus that may vary with battery charge from
22、22V to 34V during normal operations. This power service is subject to transient behavior, such as voltage ripple, spikes, and surges, which must be accounted for in the design of SPA components. The voltage reference system (VRS) associated with the spacecraft power service follows a single-point gr
23、ound (SPG) architecture. AIAA S-133-5-2013 1 1 Scope This standard is applicable to systems operating under the Space Plug-and-Play Architecture. The SPA 28V Power Service Standard establishes specifications regarding the quality of the power service such as voltage ripple, transients, and interrupt
24、ions. The scope of this document is limited to the interface between a SPA-equipped spacecraft and SPA-compliant device. This interface is implemented at a physical SPA endpoint connector, specified in AIAA S-133-4-2013 SPA Physical Interface Standard, which contains details of the connector type, p
25、in assignments, and wiring harnesses. Details of the design of a specific spacecraft electrical power subsystem, including power sources such as solar arrays and power storage devices such as batteries, are not relevant to the SPA power interface described in this document. 2 Tailoring When viewed f
26、rom the perspective of a specific program or project context, the requirements defined in this standard may be tailored to match the actual requirements of the particular program or project. Tailoring of requirements shall be undertaken in consultation with the procuring authority where applicable.
27、NOTE Tailoring is a process by which individual requirements or specifications, standards, and related documents are evaluated and made applicable to a specific program or project by selection, and in some exceptional cases, modification and addition of requirements in the standards. For the purpose
28、s of this standard, one must exercise caution in that any tailoring may lead to non-SPA compliant devices. 3 Applicable Documents The following documents contain provisions which, through reference in this text, constitute provisions of this standard. For dated references, subsequent amendments to,
29、or revisions of, any of these publications do not apply. However, parties to agreements based on this standard are encouraged to investigate the possibility of applying the most recent editions of the normative documents indicated below. For undated references, the latest edition of the normative do
30、cument referred to applies. AIAA S-133-4-2013 Space Plug-and-Play Architecture Standard Physical Interface AIAA A-122-2007 Electrical Power Systems for Unmanned Spacecraft Standard MIL-STD-461E EMC Requirements (CE101,102) 4 Vocabulary 4.1 Acronyms and Abbreviated Terms AIAA American Institute of Ae
31、ronautics and Astronautics ASIM Appliqu Sensor Interface Module SAR solar array regulator SPA Space Plug-and-Play Architecture SPG single-point ground VRS voltage reference system AIAA S-133-5-2013 2 4.2 Terms and Definitions ASIM a small chip that may be incorporated in a device to allow the device
32、 to communicate using standard SPA messaging protocols. The ASIM contains information about the device and its functions. This is similar to the idea of using a USB chip to make components compatible with USB standards. NOTE Devices may be made compliant with SPA protocols and standards without the
33、use of an ASIM by designing the device to function according to the SPA messaging and ontology standards. ASIMs are available to make legacy components compatible with SPA systems. SPA application a software SPA component SPA compliant adheres to applicable SPA standards SPA component a SPA complian
34、t hardware or software component SPA core component a SPA component that provides one or more SPA service SPA device a hardware SPA component 5 SPA 28V Power Service The SPA power system shall supply power to all SPA devices (including SPA payloads) over a single, battery-clamped 28V power bus. The
35、power system shall contain one or more power distribution modules that service multiple SPA endpoint connection points. EXAMPLE 1 A main power bus serves to interconnect the multiple power distribution modules which may be distributed over several locations on the spacecraft bus structure. The power
36、 distribution module shall interface, control, and distribute bus power originating from solar arrays and batteries to the rest of the spacecraft. It provides full 28V bus load management as well as special power for heaters, actuators, deployable release mechanisms, and high current payloads. Once
37、distributed to each individual spacecraft instrument, 28V bus power is routed within each instrument package by a SPA compatible interface. (This interface may be implemented by a standard adapter such as an ASIM or designed into the SPA device.) The SPA interface shall perform all additional instru
38、ment-specific power sequencing and provide load control management capability over the common SPA interface. The 28V bus power is distributed using standard SPA endpoint connectors and pin assignments. EXAMPLE 2 An example of a SPA power system implementation, provided for information only, is shown
39、 below in Figure 1. In this example, power flows out of the illuminated solar array panels through one or more solar array control components, such as solar array regulators (SARs). These devices deliver peak power from the solar array panels independent of illumination level, temperature, and elect
40、rical load. Power then flows to one or more modular batteries that supply supplemental spacecraft power when the panels are not fully illuminated. AIAA S-133-5-2013 3 Figure 1 SPA power subsystem configuration 6 General Power Performance Requirements 6.1 Main Power Bus Voltage The spacecraft power s
41、ystem shall maintain the main power bus voltage during normal operations to a voltage range of +22V to +34V as measured at the SPA endpoint connector on the spacecraft. Battery over-voltage limiting and under-voltage limiting shall be provided by the SPA power system through hardware or software con
42、trol of battery state-of-charge or the applicable load management software. 6.2 SPA Endpoint Current Limits Endpoint steady-state current draw limits for SPA components are defined at three different levels: 4.5A, 30A, and 50A. The 4.5A power service is provided through combined signal and power 25-
43、pin connectors and the 30A and 50A service shall be provided directly to corresponding instruments using a dedicated high power connector as described in the SPA Physical Interface Standard. An equal number of power and return pins shall be utilized such that de-rated connector pin current levels ca
44、n be maintained. 6.3 Use of Multiple SPA Endpoints A SPA component may use multiple endpoints for power and data connectivity. The SPA component shall comply with all specified requirements for each individual endpoint connection. Load balancing must be utilized when using multiple SPA endpoints to
45、limit the maximum steady-state current flow to 4.5A or less for each shared endpoint connector. AIAA S-133-5-2013 4 6.4 Main Bus Voltage Ripple Under steady-state solar array and load conditions, the bus induced voltage ripple induced by each instrument and avionics unit connected directly to the pr
46、imary SPA power bus shall meet all requirements of the MIL-STD461 (CE102) Specification as show in Figure 2. Figure 2 MIL-STD-461E (CE102) EMC requirements 6.5 Main Bus Current Ripple Conducted emissions requirements of the MIL-STD-461 (CE101) specification govern noise generated by a SPA-devices DC
47、-DC converter and conducted onto the SPA power bus. This noise is defined in terms of input ripple current and consists of a fundamental component at the switching frequency in addition to its harmonics. All SPA devices connected directly to the main power bus must have internal input filters, which
48、 limit the amplitude of the fundamental frequency component to a value such that the instrument meets or exceeds the MIL-STD-461 (CE101) Specification as show in Figure 3. AIAA S-133-5-2013 5 Figure 3 MIL-STD-461E (CE101) EMC requirements 6.6 Main Bus Impedance A sufficient number of connector pins
49、and harness wire gauge shall be utilized in order to maintain the SPA main power bus impedance to be less than the limits shown in Figure 4. The worst-case DC impedance as measured from any SPA device back to the spacecraft battery shall be 130m or less in order to ensure that the maximum voltage offset between SPG and endpoint is 0.50V or less. AIAA S-133-5-2013 6 00 . 511 . 522 . 533 . 544 . 551 . E + 0 0 1 . E + 0 1 1 . E + 0 2 1 . E + 0 3 1 . E + 0 4 1 . E + 0 5Impedance(Ohm)F r e q u e n c y ( H z )1 3 0 mil l i
