SAE AE-7 Aerospace Electrical Power & Equipment Committee

SAE AE-7 Aerospace Electrical Power & Equipment Committee
AE-7 Meeting SAE AE-7 Aerospace Electrical Power & Equipment Committee Phoenix, AZ October 10th – 12th 2017 Please provide your inputs, even if your not attending the meeting.

Meeting Agenda Overview
Tuesday October 10th AE-7 General Sessions/Breakout 8:00 AM to 5:00 PM Encanto 1 / Breakout Sessions - Boardroom Wednesday October 11th AE-7 and WG80 joint meeting 9:00 AM to 11:00 PM Encanto 2 Wednesday October 11th AE-7 General Sessions/Breakout 1:00 PM to 5:00 PM Thursday October 12th AE-7 - AE-8B Joint Meeting 8:00 AM to 10:00 PM Encanto 1 or Dining room Thursday October 12th AE-7 General Sessions/Breakout 10:00 PM to 5:00 PM Briefly go over the meeting agenda with the group.

October 10th A.M. Welcome and Introductions Call to Order
Introduction of Members and Visitors Circulation of Attendance and Membership Roster SAE Announcements and Administrative Items Call to Order – Welcome all who are attending this meeting. Go around the room with introductions. Welcome new members. Circulate the roster. Ask for a volunteer to take notes for the meeting. Have Dorothy make any SAE announcements as required Review the last meeting minutes, Note any changes and call of a motion to accept them, and someone else to second the motion. Update status on 5-year review document on the next slide

AE-7 Committee Status Report – Spring 2017
Name: AE-7 Aerospace Electrical Power & Equipment Chair: Jon Fifield, Astronics AES Length of Chair’s Term of Office: 2 years # Meetings per Year – 2 # Participants on Roster – 373 # Documents Maintained – 80 # Works in Progress – 19 # Documents Past 5-Year Review Date – 46 # Voting Members attending Last Meeting – 23 (All Committee Rosters) Metrics Average % member response to ballots – 46.08% Average time from WIP to publication – 222 days % Voting members attending meetings – 21% # WIPs More than 4 Years Old – 4 # Ballots conducted – 34 Emerging Technologies Li-ion Batteries for Aircraft Applications Real-time Hardware-in-the-loop Requesting Participation Airbus Boeing Lockheed Martin Government Academia Membership – 154 Voting Members Member User: 64% Member Producer: 29% Member General Interest: 7% Country # Mbrs Brazil 3 Canada 1 United States 62 Belgium France 11 Germany 7 Spain Sweden 2 Switzerland United Kingdom

October 10th A.M. Review and approval of Last Meeting Minutes
Call to Order – Welcome all who are attending this meeting. Go around the room with introductions. Welcome new members. Circulate the roster. Ask for a volunteer to take notes for the meeting. Have Dorothy make any SAE announcements as required Review the last meeting minutes, Note any changes and call of a motion to accept them, and someone else to second the motion. Update status on 5-year review document on the next slide

Document(s) in Need of Five-Year Overview
We will review the highlighted titles in committee, some of the documents can be found in a WIP folder AE-7 Aerospace Electrical Power and Equipment Committee Document Title Status Published WIP Date AS81099 Electric Devices, Simple, General Specification For Issued 07 Jun, 2004 12 Apr, 2012 AE-7A Generators and Controls Motors and Magnetic Devices Document Title Status Published WIP Date AIR34A Penalties in Performance of Three-Phase, Four-Wire, 400-Cycle Motors Causes By the Opening of One Phase Reaffirmed 06 Jul, 2010 AIR857A Speed Variation of D-C Motors ARP497A Precision Control Motors Cycles ARP826 Electrical Computing Resolvers AS8020 Minimum Performance Standards for Engine Driven Dc Generators/ Starter-Generators and Associated Voltage Regulators 16 May, 2011

Document(s) in Need of Five-Year Overview
AE-7B Power Management, Distribution and Storage Document Title Status Published WIP Date AS4805 Solid State Power Controller, General Standard For Issued 23 Jul, 2007 15 Apr, 2015 AS8033 Nickel Cadmium Vented Rechargeable Aircraft Batteries (Non-Sealed, Maintainable Type) Reaffirmed 06 Jul, 2010 ARP5584 Document for Electric Power Management 16 May, 2011 AIR5709 SAE AE-7 High Temperature Components Survey, 2005 15 Oct, 2012 AE-7C Systems Document Title Status Published WIP Date AIR1213 Radioisotope Power Systems Reaffirmed 06 Jul, 2010 ARP4729 Document for 270 Voltage Direct Current (270 V DC) System AS1831A Electrical Power, 270 V Dc, Aircraft, Characteristics and Utilization Of AS5698 Space Power Standard Issued 11 Apr, 2012 16 Dec, 2015

Old Business Status WIP and Plan out Breakout Sessions
Committee AE-7A – Generators / Controls / Magnetic Devices Committee AE-7B – Power Management Committee AE-7C – Systems Committee AE-7M – Aerospace Model Based Engineering Committee AE-7EU – Europe We will briefly go over the following topics to plan breakout groups to work on these tasks in more detail. Some of the tasks will have dedicated time slots for status presentations. Next four slides are for reviewing on-going group activates or document in-development What you are soliciting from the group is to determine the general interest of the group or small breakout group to work on any of the particular documents and when they should met.

Committee AE-7A – Generators / Controls / Magnetic Devices
AE-7A, WG-80, Fuel Cell Standards Panel – Joint Meeting in October 11th 2017 Aircraft Control and protection Interface requirements definition AE-7A, AIR6505 Electrical Load Characterization Nick Bunt to lead this effort Update Status on document revisions IF someone attended the Fuel cell committee meeting, please have them provide a status on what was discussed at AeroTech. AIR Arthur Schuetze

Committee AE-7A – Generators / Controls / Magnetic Devices
New Co-Chair Nominations This committee will see the biggest growth regarding the subject of All-electric and Electric propulsion devices being developed. IF someone attended the Fuel cell committee meeting, please have them provide a status on what was discussed at AeroTech. AIR Arthur Schuetze

Committee AE-7B – Power Management
AE-7B/AE-8 Arc Fault Protection – Revise AS ARC Fault Interrupter, 270 VDC - Michael Walz AIR Design and Development of Rechargeable Aerospace Lithium Battery Systems AIR Lithium Battery Systems – Prognostics and Health Management - Work with HM-1 AS6087 – Chris Severns AS Michael Waller – A copy can be downloaded from the AE-7B WIP folder AS5625A – NAVAIR if present.

Committee AE-7B – Power Management
AE-7B, AS4805A Solid State Power Controller Joint Working group meeting Thursday morning AS5625A - Minimum Performance Standards for Static Electric Power Frequency Converters AS Minimum Performance Standard (MPS) for an AC to AC converter FAA has requested some additional information to be added to the standard. AS6087 – Chris Severns AS Michael Waller – A copy can be downloaded from the AE-7B WIP folder AS5625A – NAVAIR if present.

Committee AE-7C – Systems
ARP for AIR Status progress, plan sub-session meeting AE-7C, AIR-6198 Considerations for Future Aircraft Electric Power Systems Review updated document and plan sub-session meeting. AE-7C, AS5698A - Space Power Standard - Review updated document and plan sub-session meeting Break-out session to review changes New Co-Chair Nominations AIR6127 _Ian Cotton AIR-6198 – Kamiar/ Philippe

Committee AE-7M – Aerospace Model Based Engineering
AE-7M, AIR AIRCRAFT ELECTRICAL POWER SYSTEMS. MODELING AND SIMULATION. DEFINITIONS Validation and Verification (V&V) Numerical Integration Methods for EPS M&S Models Documentation New Electrical Power System Stability AIR - Design Considerations for evaluating generator stability effects Serhiy Bozhko

Committee AE-7EU– Europe
What’s next? Next joint meeting in 2017

Break Time Write 2 using only seven 2’s.
What is a third and a half of a third of 4?

October 10th P.M. 1:00- 5:00 pm AE-7 session - Encanto 1/ Boardroom Review and edit working group agenda for Fuel Cell Standards meeting AIR-6198 Considerations for Future Aircraft Electric Power Systems ARP Electrical Load Characterization and ELA Standardization Joint AE-7 & AE-8 Meeting action item New AIR - Aerospace Electrical Power System Stability Call to Order – Welcome all who are attending this meeting. Go around the room with introductions. Welcome new members. Circulate the roster. Ask for a volunteer to take notes for the meeting. Have Dorothy make any SAE announcements as required Review the last meeting minutes, Note any changes and call of a motion to accept them, and someone else to second the motion. Update status on 5-year review document on the next slide

Review and edit working group agenda for Fuel Cell Standards meeting
Fuel Cell WG80 standards road map: work in progress and what's next - Discussion topics : • Physical interface requirements and constraints • Communication interface requirements and constraints • FAA/EASA coordination concerns • Other things? - Help need from AE-7A/B/C

AIR-6198 Considerations for Future Aircraft Electric Power Systems Status

AIR6505 Electrical Load Characterization
Scope - This AIR intends to better document and tabulate electrical load dynamics that influence power source capacity, power quality and stability. Rationale - Recommend updates to Mil-E-7016 (Analysis of Aircraft Electric Load and Power Source Capacity) to include consideration of electrical load dynamics and their effect on power sources. Now changed to ARP Electrical Load Characterization and ELA Standardization

AE-7A, AIR6505 Electrical Load Characterization
Link to the SAE ARP 6505 Blog

Things to fix or add in the ELA format?

Joint AE-7 & AE-8 Meeting action
AE7 is asking for a list of requirements for a wire standard that they could fill in and give to the 8D committee o Provide a list of things that 8D can do and can’t  Where should the ‘high voltage’ limit be placed. o Will be unique to aerospace? o Could be part of AE-7, AE-8D group is not suited to do the research to develop the project. AE-7 should come to committee with a particular configuration for the committee. The goal is to get AE-7 (Power Systems Committee) to agree on what they need in the interconnect system to support the 270VDC, 230VAC, and the massive KVA rated Power Systems in the More Electric Aircraft. AE-8 is looking for the Power Systems folks to tell us what level of testing (rating) they will require for wiring system components and wire/cable. We also want to get standards written for commercial connectors, terminals, wire, or whatever they are using.

Review Slides from the Spring meeting
Legacy voltages 115 VAC LN, 200 VAC LL 26 VAC 28 VDC 270 VDC 230 VAC Variable frequency, LN, 398 VAC LL + 130 VDC Newest Voltage 540 VDC (+ 270 VDC) What’s Next 1000 – 5000 VAC, 1K -3k Hz 400 to 800 VDC Very Light Rotorcraft and Electrically Powered Sailplane Component voltage ratings

Voltage Testing required for EWIS components
Now 540 VDC (+ 270 VDC) Near-term 400 to 800 VDC – Very Light Rotorcraft and Electrically Powered Sailplane Other considerations IEC medium voltage limits of 1,000 VAC and 1,500 VDC will be exceeded when propulsion is considered for large transport and passenger aircraft. Electrical installation above 600VAC limits needs new standards Should consider transients testing up to two or three times the rated voltages need to be anticipated.

Hybrid-Electric Voltage Road Map
Superconducting region Estimated time frame Hybrid-Electric aircraft will require MV voltages. Standards should be developed to accommodate a range of operating voltages. Mark Husband Nov Presentation, Bridging the Technology Gap for Hybrid-Electric © Rolls-Royce plc 2016 Time frame estimates add by Jon Fifield, Astronics AES 2017

Electric Propulsion

High Voltage Design drivers
Advance Insulation materials Voltage and Ampacity Limits/capabilities Chop and Pules voltage waveforms Voltage Surface potential concerns Low/High Temperature Superconductors Pin/Terminal distance separation Creepage and Clearance standards Safety and maintenance requirements Increased Energy Storage capacity Robust Energy/Power management schemes Protection and switches methodologies Power Electronics and motor drives Continued advances in Semiconductor technologies Superconducting motors TRL and MRL Readiness timeline

System Design Effects Higher Frequency Power Generating Systems
AC Inductance impedance increase the voltage drop by a 1.8X from 400Hz to 1200Hz. Large voltage drops on power feeders increase the internal heat load in the generator. Dielectric heating increase in the power feeder. Power Feeder design – Increase Wire Temperature Rating 800 VDC, 1.2MW, 100ft length, Wire Rating 260C = 2 - AWG 4/O 800 VDC, 1.2MW, 100ft length, Wire Rating 360C = 2- AWG 3/O 26% weight reduction, 43% increase in voltage drop 3-Phase 800 VAC, 800Hz 1.2MW, 100ft length, Wire Rating 260C - AWG 4/O 50% weight reduction, 4X increase in voltage drop 3-Phase 800 VAC, 800Hz, 1.2MW, 100ft length, Wire Rating 360C - AWG 3/O 60% weight reduction, 4.3X increase in voltage drop Examine increasing wire temperature to enable reducing system weight

At What Voltage Should We Be Concerned About Partial Discharge?
The existing fleet of more-electric aircraft are operating at voltages nominally set to 540V DC (+/-270V DC) and 230V AC RMS phase to earth (325V AC RMS phase to phase / 563V AC peak phase to phase). Should we be concerned about electrical discharge at these voltages / should we only consider partial discharge (corona) at voltages above 900V? Yes – we can get partial discharge or breakdown in any system with a voltage approximately higher than Paschen’s minimum, 327V The exact voltage at which partial discharge takes place will be defined by: The geometry and materials used in the insulation system The environmental conditions (temperature, pressure and various others) Any partial discharge that has previously taken place in that system

At What Voltage Should We Be Concerned About Partial Discharge?
We should note the need to consider voltages either side of nominal. They can go up for a range of reasons. However, we could potentially accommodate limited amounts of partial discharge as long as this is extinguished when the voltage returns to the nominal value (image from PhD of Benjamin Cella – Laplace) Some objects can fail extremely quickly if PD inception takes place (an IGBT module for example), others will likely have a long time to failure (PTFE based cabling for example).

Action items from the meeting
AE-7 to provide the specification and testing requirements for high voltage components Provide the testing methods for wire insulation systems for >600 V. For this meeting we will work on requirements for HV wire and connectors.

Wire Specification requirements
Electrical requirements Wire gauge [AWG] Nominal current [A] Voltage [V] EMI - shielding [dB] Lightning [kA] Dielectrical withstanding voltage [V] Insulation resistance [GW] cable construction wire type / standard

Mechanical requirements Thermal Vibration Shock

Environmental Temperature range [°C] Area / Description of location Sealing Corrosion resistant Fluids resistant Fungus resistant RoHS REACH Fire, Smoke & Toxicity

Testing for over 600V wire Thermal Shock Moisture Resistance Durability Salt Spray (Corrosion) Vibration High Impact Heat Rise Fluid Immersion Water Immersion

Connector Specification requirements
Electrical requirements Wire gauge [AWG] Contact gauge [AWG] Nominal current [A] Circuit breaker / peak current Voltage [V] EMI - shielding [dB] Shell conductivity requirements [mW] Lightning [kA] Dielectrical withstanding voltage [V] Insulation resistance cable construction Contact resistance

Mechanical requirements Thermal Mating cycles Vibration Shock Mating & Unmating forces Material / Finish Contact technology

Environmental Temperature range [°C] Area / Description of location Sealing Corrosion resistant Fluids resistant Fungus resistant RoHS REACH Fire, Smoke & Toxicity

Testing Thermal Shock Moisture Resistance Durability Salt Spray (Corrosion) Vibration High Impact Heat Rise Fluid Immersion Water Immersion

Break Time Some horses and chickens are in a barn; the total number of heads and wings equals the number of feet. How many horses and how many chickens are there? This and that and a half of this and that is what percent of three fourths of this and that?

October 11th 9:00 – 11:00 pm AE-7 and WG80 joint meeting Group dinner tonight? 11:30 – 1:00 pm Lunch 1:00- 5:00 pm AE-7 Breakout session - Encanto 1/ Boardroom Call to Order – Welcome all who are attending this meeting. Go around the room with introductions. Welcome new members. Circulate the roster. Ask for a volunteer to take notes for the meeting. Have Dorothy make any SAE announcements as required Review the last meeting minutes, Note any changes and call of a motion to accept them, and someone else to second the motion. Update status on 5-year review document on the next slide

New Business Hybrid-electric propulsion systems
Minimum Performance Standards for DC Propulsion Motor and Associated Voltage Regulators

Hybrid-electric propulsion systems

Aurora Overview Mission
eVTOL aircraft will provide on-demand transportation to minimize long commutes due to heavy traffic and urbanization in populated areas. The infrastructure plan includes urban “vertiports” for passenger boarding and vehicle servicing. eVTOL aircraft will operate a “hub-to-hub” service between designated vertiports. The first test bed flights are scheduled to begin in 2020 in Dallas, Texas, USA and Dubai, The United Arab Emirates.

Operational Overview The eVTOL aircraft includes eight lift rotors for vertical takeoff and cruise propeller and wing to transition to high-speed forward cruise. At destination hub, the aircraft transitions back to rotor-borne flight for vertical landing. Fully electric operation decreases or eliminates emissions and noise pollution for a quieter flight. While initially operated with a safety pilot, the eVTOL aircraft is designed for fully autonomous operations. The flight capability for eVTOL aircraft is three times more efficient than a multi-copter aircraft.

Aurora Flight Sciences XV-24A “LightningStrike
At 300 pounds, Honeywell’s megawatt generator is five times smaller in size and weight compared to other generators that produce similar power, said Tom Konicki, Honeywell Aerospace director of business development. Rolls-Royce is bringing to bear capabilities for hybrid electric power generation and distributed control systems, plus experience as an engine supplier on various VTOL platforms. Boeing has announced that it's buying Aurora Flight Sciences

Minimum Performance Standards for DC Propulsion Motor and Associated Voltage Regulators
A distributed electric propulsion system for a VTOL aircraft can exploit aerodynamic benefits that increase the lift to drag ratio by 4- to 5-times that of conventional helicopters ( This yields a fourfold increase in range while maintaining the VTOL and hover capabilities of a conventional helicopter. (LaunchPoint Technologies) There are many advantages for using electric propulsion on aircraft: power to weight (P/W) ratios exceeding 5HP/lb, direct drive propulsion, compact form factor, high efficiency over the majority of motor speed range, ability to overpower motors over 2x the continuous power ratings for short bursts, and the most significant, electric motors are effectively scale-free meaning the power to weight ratios, efficiencies, etc. are the same independent of motor scale. Elon Musk -- who has designed his own electric plane, of course -- said the necessary battery density threshold is about 400 Wh/kg, compared to around Wh/kg available in current Tesla models.

ASTM F Standard Practice for Design and Manufacture of Electric Propulsion Units for Light Sport Aircraft Significance and Use 3.1 This specification provides designers and manufacturers of electric propulsion for light sport aircraft design references and criteria to use in designing and manufacturing EPUs. 3.2 Declaration of compliance is based on testing and documentation during the design, ground testing and flight testing of the EPU by the manufacturer or under the manufacturers’ guidance. 3.3 Manufacturers of the EPUs are encouraged to review and incorporate appropriate standards and lessons learned from ground based systems as documented in SAE J2344 and EASA CRI F-58 (see Appendix X2). 3.4 Electric aircraft may contain potentially hazardous level of electrical voltage or current. It is important to protect persons from exposure to this hazard. Under normal operating conditions, adequate electrical isolation is achieved through physical separation means such as the use of insulated wire, enclosures, or other barriers to direct contact. There are conditions or events that can occur outside normal operation that can cause this protection to be degraded. Some means should be provided to detect degraded isolation or ground fault. In addition, processes or hardware, or both, should be provided to allow for controlled access to the high voltage system for maintenance or repair. A number of alternative means may be used to achieve these electrical safety goals including automatic hazardous voltage disconnects, manual disconnects, interlock systems, special tools and grounding. The intention of all these means is either to prevent inadvertent contact with hazardous voltages or to prevent damage or injury from the uncontrolled release of electric energy. Lightning strikes are not addressed in this Standard Practice because LSA aircraft are limited to VMC flight only.

Electric Propulsion Units (EPU) Standards
ASTM Standards F2245 Specification for Design and Performance of a Light Sport Airplane F2972 Specification for Light Sport Aircraft Manufacturers Quality Assurance System Other Standards EASA CRI F-58 Lithium Battery Installations Available from European Aviation Safety Agency (EASA), Postfach , D Koeln, Germany, SAE J2344 Guidelines for Electric Vehicle Safety Available from SAE International (SAE), 400 Commonwealth Dr., Warrendale, PA ,

AE-7A Document outline Contacted Launchpoint, Joby and Lilium on currently used electric motor design standards. What’s next?

New Business AIR on EPS Design Myths and Constraints

EPS Design Myths and Constraints
1. “One size fits all”; a single architecture or design fits all aircraft applications 2. Any commercial off the shelf (COTS) components can be used in military applications 3. If a design meets all ‘spec’ requirements during test, it will work as expected in the ‘field’ 4. An optimized design always results in weight & volume savings 5. Integration of optimized components always results in an optimized integrated systems design 6. The EPS does not have to interface or interact with other systems to perform its functions 7. Building and testing hardware is cheaper than using model based design during development 8. Use of automated design tools always saves time and money 9. Once the prototype design or schematics are complete, the hard work is over Please provide your inputs; the goal is to publish an AIR document.

EPS Design Myths and Constraints
10. Prototype designs are always good for final production Components can be placed anywhere in an architecture and the design will be ‘effective’ Power management and distribution functions are not critical for safe designs Grouping or locating components together is a good use of space and good design practice Sizes of conductors, feeders, and connectors can be one size fits all Sizing for average or continuous electrical loads is sufficient for all operating modes Requirements never grow; the first design will never change Steady-state, point designs (and testing) are sufficient to meet all requirements

Pre-AIR Aerospace Electrical Power System Stability Analysis
Review Spring 2017 notes What’s next?

October 12th 8:00 – 10:00 pm AE-7/AE-8B Joint Meeting - Encanto 1 12:00 – 1:00 pm Lunch 1:00- 5:00 pm AE-7 Combined Meeting - Royal Palm Salon E Review Task assignments Call to Order – Welcome all who are attending this meeting. Go around the room with introductions. Welcome new members. Circulate the roster. Ask for a volunteer to take notes for the meeting. Have Dorothy make any SAE announcements as required Review the last meeting minutes, Note any changes and call of a motion to accept them, and someone else to second the motion. Update status on 5-year review document on the next slide

New Business AIR - Fundamentals in selecting Wire Sizes in Aerospace Applications SAE AE2 Lightning Committee working group AIR XXXX, Comparisons of EMI Requirements and Test Procedures Characterized in Commercial Aerospace Standards and MIL-STD-461G ARP for Bus Bar design? Power Quality comparison document

Document review and comments
AIR Fundamentals in selecting Wire Sizes in Aerospace Applications Document review and comments The scope of this report is to capture the fundamental principles of selecting a wire size for an aerospace application using the method prescribed in SAE AS50881 standard. Also, provided in this report are additional calculations to ensure the wire selection will adequately perform in a particular design function including meeting environment constraints. Some of the calculations in this report have been simplified to demonstrate the process for validating the wire size selections for a particular design application. More precise calculations should be investigated and evaluated to ensure proper assessment of each individual calculation in this report. Go to Ballot?

SAE AE2 Lightning Committee working group Coordination
AIR XXXX, Comparisons of EMI Requirements and Test Procedures Characterized in Commercial Aerospace Standards and MIL-STD-461G Current proliferation of commercial aircraft modified to perform military missions (Commercial Derivatives) has established the need to assess the suitability, from an airworthiness and performance perspectives, of using equipment qualified to commercial electromagnetic interference (EMI) standards in military applications This Aerospace Information Report (AIR) will document the results of detailed comparisons of individual requirements and test methods in MIL-STD-461G with similar aerospace equipment commercial standards. The information that will be part of this report will facilitate cognizant EMI personnel to determine if equipment qualified to commercial standards is appropriate for use in military applications/missions or if it requires additional EMI certification testing Likewise, this AIR will facilitate the assessment of equipment certified to the requirements and test methods of MIL-STD-461G for their use in commercial aviation

SAE AE2 Lightning Committee working group Coordination
Equipment focused EMI equipment requirements for airborne applications only (Initially USAF Only) Supports airworthiness assessments/certification Assessment to include only the requirements and test methods of MIL-STD-461G and the corresponding sections of the RTCA DO- 160 Not to include EMI requirements from CISPRs, FCC, etc. Final Product (AIR XXXX) is for guidance only; not to be contractually binding Review Draft: 1QTR 2018 Incorporate comments & Complete Final Version: 3rd QTR 2018 Submit for publication – End of 2018

ARP for Bus Bar design Why do we need this?

Power Quality comparison document
Document outline Power Quality Definitions Effects of Power Quality Problems Standards Comparison matrix Retesting tables Task assignments Schedule

Anything new to start working on?

Task Leaders AE-7A, AIR6505 Electrical Load Characterization Nick Bunt AE-7A, AIR-6198 MEA Electric Power Systems - Philippe Naneix AE-7B AIR Design and Development of Rechargeable Aerospace Lithium Battery Systems M Waller AIR Lithium Battery Systems – Prognostics and Health Management - Work with HM-1 AE-7B/AE-8 Arc Fault Protection new ARP? M Walz AE-7C, New ARP outline review for follow-on to AIR6127 Managing Higher Voltage Systems Review – Ian Cotton Aerospace Electrical Power System Stability - Philippe Naneix &Serhiy Bozhko AIR Safety Consideration for a 48/60 VDC Aircraft distribution system – Jon Fifield

October 12th P.M. Closing New Business Next Meeting Adjournment
Spring 2018 Europe GE to Host Cheltenham, United Kingdom Fall – Joint Meeting with AE-8? Not at ASTC Adjournment Out brief from all breakout session. Collect meeting notes and action items. Discuss interest in forming a group to address an AIR for Mil-Std-704. May not have all the right people for this meeting. Update AS 5698 – if anyone is interested in updating this standard please contact Robert Scheidegger

Cheltenham, United Kingdom

October 12th P.M. AE-7 Charters review in work for Spring 2017 AE-7A - Francis DELHASSE AE-7B - Christopher Severns AE-7C – Philippe Naneix AE-7M - Serhiy Bozhko

SAE Statements Anti-Trust Statement Patent Disclosure
In discharging their responsibilities, members of the Technical Standards Board, Councils/Division, and Technical Committees function as individuals and not as agents or representatives of any organization with which they may be associated, except that government employees participate in accordance with governmental regulations. Members are appointed to SAE Technical Committees on the basis of their individual qualifications which enable them to contribute to the work of the Committee. Patent Disclosure Each SAE Technical Committee or SAE working group member would be required to disclose at specified times during a development process all patents and patent applications that are owned, controlled or licensed by the member, member’s employer or third party and that the member believes may become essential to the draft specification under development. The member would make this disclosure based on the member’s good faith and reasonable inquiry. If SAE International receives a notice that a proposed SAE Technical Report may require the use of an invention claimed in a patent, the respective part of the SAE Technical Standards Board Policy will be followed.

SAE AE-7 Aerospace Electrical Power & Equipment Committee

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