hycarus - 1-system-specification_r4.0.docxhycarus generic application hycarus public 5 11/04/14...

HYCARUS D1.1 HYCARUS Generic Application Definition

Contract no HYCARUS – FCH JU 325342

Due date of deliverable 31.10.2013

Submission Date 11.04.2014

Abstract Generic Application Definition

Author, company Lothar Kerschgens, ZCC

Loïc Bouillo, AET

Confidentiality level PUB

Filing code HYC-ZCC-D1.1-Generic Application Definition

Related items HYC-ZCC-D1.2-Safety Analysis Report

DOCUMENT HISTORY

Release Date Reason of Change Status Distribution

R2.0 09.12.2013 Initial Report Draft PUB

R3.0 28.03.2014 Final changes Draft DEL leaders

R3.1 31.03.2014 Reviewed Report Draft PUB

R4.0 11.04.2014 Final Report

HYC-ZCC-D1 1-SYSTEM-SPECIFICATION_R4.0.docx HYCARUS GENERIC APPLICATION

HYCARUS Public 2 11/04/14

Table of Content

Table of Content .................................................................................................................... 2

1. General .......................................................................................................................... 4

1.1. Purpose of the document ......................................................................................... 4

1.2. Context description................................................................................................... 4

1.3. Requirements identification ...................................................................................... 4

2. Terminology and Abbreviations ...................................................................................... 6

2.1. Acronyms ................................................................................................................. 6

2.2. Glossary ................................................................................................................... 8

3. Executive Summary ......................................................................................................10

4. System / Equipment Description ....................................................................................12

4.1. Aircraft characteristics ............................................................................................ 12

4.2. Description and function on aircraft ........................................................................ 12

4.2.1. General ........................................................................................................... 12

4.2.2. Function .......................................................................................................... 13

4.2.3. Life situations .................................................................................................. 13

4.2.4. Definition of Generic Fuel Cell System ............................................................ 13

4.2.5. Integration ....................................................................................................... 16

4.2.6. Perimeter ........................................................................................................ 18

4.2.7. Partners scope ................................................................................................ 19

5. Documents ....................................................................................................................21

5.1. Applicable documents ............................................................................................ 21

5.2. Reference documents ............................................................................................ 21

6. Description ....................................................................................................................22

6.1. Aircraft related specification ................................................................................... 22

6.1.1. Flight envelope ................................................................................................ 22

6.1.2. Operational envelope ...................................................................................... 22

7. Functional requirements ................................................................................................24

7.1. Initialization and power down rules and requirements ............................................ 24

7.1.1. States of the system ........................................................................................ 24

7.1.2. Startup and shutdown conditions..................................................................... 24

7.2. Performance requirements ..................................................................................... 24



7.2.1. Output Voltages .............................................................................................. 24

7.2.2. Output Power .................................................................................................. 25

7.2.3. Electrical efficiency .......................................................................................... 25

7.2.4. Dynamics ........................................................................................................ 25

7.3. Operational requirements ....................................................................................... 25

7.3.1. Autonomous operation .................................................................................... 25

7.3.2. Autonomy ........................................................................................................ 25

7.3.3. Operational conditions ..................................................................................... 25

7.3.4. Operational lifetime ......................................................................................... 25

7.4. Logistic requirements ............................................................................................. 25

7.4.1. Lifting interfaces .............................................................................................. 25

7.4.2. Installation ....................................................................................................... 25

7.4.3. Refueling ......................................................................................................... 25

7.5. Design requirements .............................................................................................. 26

7.5.1. Dimensions ..................................................................................................... 26

7.6. Safety Requirements .............................................................................................. 26

7.7. Maintainability requirements ................................................................................... 26

8. Environmental Requirements ........................................................................................27

9. Conclusions ...................................................................................................................28



1. General

1.1. Purpose of the document

This document is the complete specification of HYCARUS project’s Generic Fuel Cell System.

1.2. Context description

The HYCARUS project will design a generic PEM fuel cell system (GFCS) compatible with two non-essential aircraft applications (NEA), develop, test and demonstrate at technology readiness level 6 (TRL6), a Galley for a single aisle aircraft. A secondary electrical power generation model for a business executive jet will be run.

The Generic Fuel Cell System (GFCS) specification describes the application of the fuel cell system and the hydrogen storage system for tests under flying conditions. Furthermore, investigations will be made to understand how to capture and reuse the by-products.

The HYCARUS project will extend the work particularly for safety codes and standards, and develop these for use in airborne installation and applications.

Hycarus project involves different partners who come with different applications of a fuel cell system onboard an aircraft. This fuel cell system won’t therefore be optimized for any of the base applications. In order to get figures of what the system would be if it was optimized for a particular application, complete numeric models of the system dedicated to each application will be built and run.

1.3. Requirements identification

Words of “shall”, “should”, “must”, “will” and “may” used in this document shall be interpreted as follows:



Documentary

Terms Definition

Shall

The word “shall” in the text means a mandatory requirement of this

document. Discrepancy from such a requirement is not permissible without

formal agreement with the recipient.

Should

The word “should” in the text means a recommendation or advice on

implementing such a requirement of this document. Such recommendations

or advice are expected to be followed unless substantial explanations are

stated and documented for non-implementation.

Must The word “must” in the text is used for legislative or regulatory requirements

(for example Health and Safety) and shall be complied with.

Will The word “will” in the text means a provision or service or an intention in

conjunction with a requirement of this document.

May The word “may” in the text means a permissible practice or action. It does

not express a requirement of this document.

The applicable requirements of this document are identified with a 8 digit number ([xxxx][yyyy]) with [xxxx]=TRS number and [yyyy]=Requirement number.

It shall not be modified through the document issues.

For every requirement the applicable documents and criteria are listed underneath.

If a requirement becomes useless the requirement shall remain followed by DELETED or NOT APPLICABLE.



2. Terminology and Abbreviations

2.1. Acronyms

Abbreviation / acronym Description

A/C Aircraft

AC Alternating Current

BOL Beginning Of Life

CEA Commissariat à l’Energie Atomique et aux énergies alternatives

CMS Cooling Management System

CRC Crew Rest Compartment

CRS Corrosion Resistant Steel

CS Certification Specification

CZ Czech Republic

DA Dassault Aviation

DC Direct current

DMIR Designated Manufacturing Inspection Representative

DO Design Organization

EASA European Aviation Safety Agency

ECS Environmental Control System

EPMS Electrical Power Management System

ESD Electro-Static Discharge

EUT GFCS equipment under test

FAA Federal Aviation Administration

FAR Federal Aviation Regulations

FC Fuel Cell

FHA Functional Hazard Assessment

FMEA Failure Mode Effective Analysis

FMS Fuel Management System

FTA Fault Tree Assessment

GAINS Galley Electrical Inserts

GFCS Generic Fuel Cell System



HIRF High Intensity Radiated Fields

HT High Temperature

IFCS Integrated Fuel Cell System

JDP Join Design Phase

LAV Lavatory

LT Low Temperature

LFL Lower Flammability Limit

MCS Monitoring and Control System

MoC Means Of Compliance

N/A Not Applicable

NL Netherlands

ODA Oxygen Depleted Air

OMS Oxidant Management System

P & T Pressure & Temperature

PAX Passenger

PEM Polymer Electrolyte Membrane

PEMFC Proton Exchange Membrane Fuel Cell

PMC Power Management Calculator

PNR Part number

PSSA Preliminary System Safety Assessment

SAE Society of Automotive Engineers

SOC State of Charge

SPS Secondary Power System

SSA System Safety Assessment

STC Supplemental Type Certificate

TBC To Be Confirmed

TBD To Be Defined

TC Type Certificate

TRL Technology Readiness Level (maturity)

TRS Technical Requirement Specification

ZA Zodiac Aerospace

ZECE Zodiac ECE

ZFIS Zodiac Fuel and Inerting Systems



2.2. Glossary

Generic Fuel Cell System efficiency:

The GFCS efficiency is computed as follows:

Where:

: Electrical efficiency

: Electrical power [W]

: Hydrogen flow rate at storage output [kg.s-1]

: Consumed hydrogen flow rate [kg.s-1]

: Lower heating value of hydrogen [J.kg-1]

: Fuel Cell

: Generic Fuel Cell System

: Hydrogen stoichiometry at system level

: Ancillaries

Low Leakage:

Low leakage is defined as an amount of leaking fuel which leads to a fuel concentration in a fuel/air mixture below 25% of the LFL, i.e. 1% volumetric concentration.

Medium Leakage:

Medium leakage is defined as an amount of leaking fuel which leads to a fuel concentration in a fuel/air mixture between 25% and 50% of the LFL, i.e. 1% to 2% volumetric concentration.

High Leakage:

ZGEU Zodiac Galleys Europe

ZDC Zodiac Driessen Czech

ZPGS Zodiac Premium Galleys

ZSSM Zodiac Sensor Systems

ZOS Zodiac Oxygen Systems



High leakage is defined as an amount of leaking fuel which leads to a fuel concentration in a fuel/air mixture above 50% of the LFL, i.e. > 2% volumetric concentration.

Useful Life:

Under given conditions, the useful life of the item is the time interval beginning at the item’s entry into service aboard the A/C and ending when the safety/reliability requirements can no longer be fulfilled.



3. Executive Summary

The deliverable D1.1 "Generic application definition” provides a high level specification of the applications foreseen as follows:

- Overview on aircraft related specification describing usage scenarios, mission load profiles and requirements

- Application of GFCS in galley & lavatory and crew rest compartment - Application of GFCS in secondary power system (SPS) - Generic application specifications and sizing

The specification contains in detail

- expected electrical performances including hybridization, - endurance, robustness and life cycle aspects, - compatibility aspects with existing on board equipment and infrastructure, - Sizing and dimensions, volume and weight, logistics aspects (refueling, etc.)

The project activities are embedded in the HYCARUS work packages as shown in Figure 1.

Therefore, a lot of interfaces to the other HYCARUS work packages exist (refer to [3]).

Figure 1: HYCARUS Work Package Overview

WP1Specifications

and sizing

WP2FC System

Development

WP3Power

Conversion

WP4Battery System Adaptations

WP5Gas supply system

development

WP6System

Integration

WP7System Modeling

and extrapolation

WP10Regulatory certification and dissemination aspects

WP8System

Demonstration

WP9Overall System

Assessment

WP11Management



The HYCARUS development process will be in accordance to SAE 4761 and SAE 4754 in

order to fulfill the requirements of design and safety process. The process thus follows a

“Verification & Validation” Model approach, which is used in aircraft industries;.

Figure 2 shows the process flow of work packages and validation process of the HYCARUS

project.

Figure 2: HYCARUS V-Model in the process flow of work packages

Figure 3 shows the interaction of design process and safety process of the HYCARUS

project.

Figure 3: HYCARUS V-Model and interactions in the design process

The safety activities contribute to the overall project goal. The main contribution of the safety

assessment is to prepare a future certification process and ensure safe operation in flight.

The preparation of the certification process also requires input from other work packages.

After completion of the deliverables required by the certification plan (HYCARUS WP10) the

system can be considered to be safe for flight. Further details are described in the “Safety

Report” (Deliverable D1.2).



4. System / Equipment Description

4.1. Aircraft characteristics

The system will be installed onboard a Falcon aircraft, dedicated to special aeronautics equipment flight tests.

The GFCS will also be tested in a Galley on ground, assuming an A320 integration of this fuel cell powered Galley.

Therefore, both contexts have to be taken into account for system integration topics. As Galley integration is the most constraining one, integration works will be focused first on this application and adapted for flight tests in a second phase

4.2. Description and function on aircraft

4.2.1. General

HYCARUS project aims to demonstrate consortium’s know-how about fuel cell systems, and the maturity of this technology in aeronautics applications.

CEA, as a French leading research center on fuel cells and fuel cell systems, will bring its expertise to the consortium.

Air Liquide Advanced Technology (ALAT), as a major stakeholder in hydrogen distribution has the complete skill panel to design the logistic, the storage and the high pressure supply chain in the aircraft.

Dassault Aviation (DA) as an OEM in the international aircraft market has the complete skill panel to specify and integrate a generic fuel cell system into a commercial aircraft.

Zodiac Aerospace (ZA), as a major stakeholder in oxygen distribution and galleys & lav applications in aircraft, has the complete skill panel to design an innovative generic galley & lavatory solution, the fuel cell system providing a way to make it completely independent from the aircraft electrical network.

Furthermore, as the electricity production in the fuel cell implies heat, water and oxygen depleted air production, high overall system efficiency can be expected, through these by-products valorization.

Many questions arise from a safety point of view, speaking about putting high pressure hydrogen storage onboard an aircraft. As all major aircraft business actors consider the introduction of the technology for future generations of A/C and from different points of view, rules and standards are still being discussed and could lead to major constraints for hydrogen storage integration.

Nevertheless, assumption is made here that such integration will be possible, either in the cabin or in cargo zone. As this location has an impact on system design, it will have to be clearly stated in early developments of the project. The fuel cell and its ancillaries will be located in the test Falcon cabin for flight tests, and in the G4 galley for ground tests.



4.2.2. Function

The function of the GFCS is to convert hydrogen and oxygen to supply electrical power to its cabin loads.

4.2.3. Life situations

The GFCS will encounter following life situations:

Conditioning

Storage

Transport

Integration on on flight test aircraft

Integration on Galley aircraft

Use

o Start-up

o Aircraft on ground

o Aircraft in flight

o Shut-down

o Hydrogen refilling

Maintenance

Recycling

4.2.4. Definition of Generic Fuel Cell System

4.2.4.1. Mission Profiles

4.2.4.1.1. Computation of Generic Application mission profiles: Approach

During WP1 of the project, 3 different mission profiles have been considered, corresponding to 3 different applications: Crew Rest Compartment (CRC), Galley G4 (G4), and Secondary Power System (SPS).

The design of the Generic Fuel Cell System has to be as representative as possible of these three applications. To achieve this objective, the process has been the following:

Identification of key parameters to ensure representativeness. These parameters are:

- Peak power for each application

- Mean power

- Dynamics (time increment Δt)

- Power distribution on mission duration

Taking into account of major integration constraints onboard the tests A/C



In both cases, and regarding system sizing, the most constraining figures have been retained.

The Figure 4 and Figure 5, hereafter, illustrate the definition of the power profiles curves:

a) Power versus mission time

i. Curve describing net power required to address payload demand as a

function of flight time

Figure 4 : HYCARUS Definition of a Power Profile Curve

ii. Identification of gross power required from the fuel cell system

iii. Identification of net power required from the fuel cell system

b) Time Increment “Δt”

i. Identification of time increment required for computation of energy

use throughout entire mission => sizing of energy source

ii. Identification of time increment required to properly describe the

dynamics of the power demand => constraints for hybridization

Figure 5 : Time Increment “Δt”

4.2.4.1.2. Base mission profiles

The three “base” mission profiles are described hereafter:

4.2.4.1.2.1. Mission profile for Galley G4 application

To define the mission profile for the Galley application, a G4 galley has been considered, equipped with following inserts:

3 Water boilers



2 Ovens

1 Chiller

The resulting power profile leads to 17kWh overall energy consumption and about 17kW system maximum power.

4.2.4.1.2.2. Crew Rest Compartment (CRC) Power System

requirements

The Crew Rest Compartment (CRC) is used in the cabin of an Airbus aircraft A320 and is limited in dimensions and power consumption. Mission load profile of the CRC shows a very stable and reproducible power and heat demand.

Its consumed power varies between 0 and 3 kWel with a certain periodicity.

4.2.4.1.2.3. Mission profile for SPS Falcon application

The Secondary Power System (SPS) is used in the cabin of a Falcon aircraft. The power varies between 4,5 and 8 kWel with a certain periodicity at peak power of 8 kWel.

4.2.4.1.3. Constraints related to the flight tests A/C

The choice of the Falcon as the A/C for the flight tests has induced several constraints for the system:

The size of the A/C makes it impossible to perform the flight tests with a Galley installed onboard. The GFCS will therefore be installed in dedicated pallets inside the A/C for the flight tests, and in the Galley for ground tests.

The electrical load used for the flight tests will be a dynamic resistive load.

Due to the characteristics of the Falcon’s ECS, the heat released to the cabin shall always be kept under 5kW. As the dynamic load releases 2kW heat itself, the maximum amount of heat releases allowed to the GFCS in the cabin is 3kW.

The duration of one mission in the flight tests will not exceed 4 hours.

4.2.4.1.4. Definition of Generic application mission profiles

The analysis of the three mission profiles and the above constraints leads to the following remarks:

CRC mission profile is covered by the other mission profiles. Therefore it has been decided to take only G4 and SPS mission profiles into account.

Mean power of G4 and SPS profiles are respectively 5.7kW and 5kW. The Generic application mission profiles should therefore have a mean power around 5kW.

The maximum power of G4 and SPS mission profiles are respectively 17kW and 8kW.



In order to keep the system representative of both applications, and taking into account heat limitations constraints for the flight tests, it has been decided the following:

Sizing of the system on the G4 maximum power. The system will therefore be oversized regarding SPS application, and estimation of the size of an optimized fuel cell system for SPS will be obtained through modelling activities.

Use of an optimized G4 mission profile for ground tests, with GFCS integrated into the Galley.

Use of a “generic” mission profile for flight tests, computed from both SPS and G4 mission profiles, with limited maximum power (9kW), and a mean power around 5kW.

4.2.5. Integration

4.2.5.1. Galley Application

The integration of GFCS into cabin interiors like galley is specified by Zodiac Galley Europe ZGEU. The requirements and constraints are given by the Airbus specification of these compartments. Figure 6 shows expectations of the cabin interior integration.



Figure 6: GFCS integrated in Galley G4

The GFCS is handled as an insert to supply electrical power to the Galley. This application enables ZGEU to prepare the EASA certification process of the Galley with the GFCS. The specification uses the Galley G4 mission profile and the restrictions of volume and weight for the GFCS integration.

4.2.5.2. Secondary power application: Specifications

The integration of GFCS into a cabin secondary power application is specified by Hycarus partners and Dassault. The requirements and constraints are given by the Dassault Falcon Flight test centre. Figure 7 shows expectations of the cabin interior integration.



Figure 7: GFCS Integrated in Falcon

The GFCS is handled as a power rack to supply electrical power to a payload. This application enables Dassault to proceed with the safe for flight process of the SPS for flight test.

4.2.5.1. Generic Fuel Cell System integration

Following both application descriptions above, the GFCS will be integrated in the 2 configurations described.

4.2.6. Perimeter

The perimeter of the system is presented in Figure 8 hereafter.

The GFCS includes following subsystems:

The fuel cell

The fuel (gaseous hydrogen) management system, that supplies hydrogen to the fuel cell according to the power demand

The oxidant (air) management system, that supplies air to the fuel cell according to the power demand

The thermal management system, which role is to evacuate the heat from the system

The exhaust management system, to deal with non-valorized by-products

The electrical power management system, which role is to distribute electricity from the fuel cell to its ancillaries and the consumers.

The monitoring and control system, which role is to ensure subsystems synchronization, actuators control and active security functions.



Figure 8: GFCS perimeter

4.2.7. Partners scope

In addition to the subsystem breakdown the scope related to each partner in the system has been depicted on Figure 9:

ALAT is responsible for the design and realization of the High Pressure (HP) hydrogen system, including vessel, pressure regulator, and electronic shut off valve.

CEA is responsible for the design and realization of the Fuel Cell (FC) and the hybridization battery.

ZA is responsible for system synthesis, and the other components of the system.



Figure 9: Partners scope



5. Documents

5.1. Applicable documents

Reference Description

EUROCAE ED14-F/RTCA DO160G Environmental Conditions And Test Procedures For

Airborne Equipment

MIL-STD-704F Aircraft Electric Power Characteristics

ISO14687_2 Hydrogen Fuel – Product specification

SAE – ED219 / AIR6464 Aircraft Fuel Cell Safety Guidelines

5.2. Reference documents

Number Reference Description

[1] HYC-ZCC-D1.2-Safety Analysis Report Hycarus confidential safety report

[2] SAE Air 6464 Aircraft fuel cell safety guidelines

[3] DoW 13 3 13 Description of Work

[4] RTCA_DO-160/ED-14 Environmental Conditions And Test

Procedures For Airborne Equipment

[5] SAE ARP 4754A Guidelines for development of civil

aircraft and systems

[6] SAE ARP 4761 Guidelines and methods for safety

assessments



6. Description

6.1. Aircraft related specification

Aircraft related specifications are devoted to the definition of all operational specifications and safety requirements applicable for the airborne use of a fuel cell power generation. The aircraft related specification has been worked out as “usage scenarios”. The details are as follows:

6.1.1. Flight envelope

6.1.1.1. Cabin pressure

The cabin pressure varies from 750hPa to 1100hPa.

6.1.1.2. Cabin temperature

In normal operation, cabin temperature is maintained between 5°C and 45°C.

6.1.2. Operational envelope

6.1.2.1. Operational ambient conditions

Operating ambient pressure between 750hPa and 1100hPa.

Operating ambient temperature between 5°C and 45°C.

6.1.2.2. Usage Scenarios

6.1.2.2.1. Mission definition

I. Purpose: provide power to specific, “non-essential” cabin

loads

II. Duration: Entire flight time (4 hours maximum)

III. Occurrence: Each flight

IV. Restrictions: Capability to operate on ground at selected

airfileds

6.1.2.2.2. Operational characteristics

V. Start-up: On-ground during aircraft/flight preparation +

checks

VI. Stop: Upon aircraft shut-down

VII. In-flight capability of re-start

VIII. Autonomous operation: no required assistance / staff intervention

IX. Storage phase

6.1.2.2.3. Description and functions on Aircraft

X. Independent power generation system based on PEM fuel cell technology

XI. Non-intrusive system with regards to aircraft operation

XII. May be taken on-board existing platform



6.1.2.2.4. Functional perimeter

I. Includes

i. Energy source = hydrogen storage system + associated delivery

system to fuel cell; oxygen (air) delivery system to fuel cell

ii. Power source = PEM fuel cell and associated BOP components for

autonomous operation (incl. thermal management system + by product

management system + start-up system)

iii. Power conversion = ensures autonomous delivery of proper electrical

power from fuel cell system to payload (incl. thermal management

system)

II. Excludes

i. Payload system (used as consumers in cabin)

6.1.2.2.5. Interactions with other systems

i. Heat tank: heat receipt during fuel cell system

operation

ii. Cabin air for fuel cell electrochemical reactions

iii. Hydrogen ventilation mitigation of hydrogen

leakage/confinement

iv. Hydrogen discharge mitigation of fire/explosion risk



7. Functional requirements

7.1. Initialization and power down rules and requirements

7.1.1. States of the system

In “use” life situation, the generic fuel cell system may be in several states. These states are shown in the following table:

N° Code Description

1 Power off In power off state, all controllers and ancillaries are powered off. The fuel cell is not supplied with gases, its voltage is less than 50VDC, and no energy is actively exchanged.

2 Start-up Start-up phase begins when start button is pushed ON and ends when the GFCS in idle state.

3 Idle The GFCS is in idle state when it is ready to supply its electrical consumers but is still electrically isolated from them, i.e.:

The fuel cell is supplied with reactants

The fuel cell supplies all its ancillaries with electrical power

4 Warm-up phase

The warm-up phase starts when the fuel cell begins supplying electrical power, and ends when it has reached a sufficient threshold temperature to avoid any water management issue (flooding). The power delivery will thus be limited during this phase. Threshold temperature will have to be defined in further phases of the project.

5 Operating The GFCS is considered to be operating when it is able to continuously deliver electrical power to its consumers.

6 Shut-down The shutdown phase starts when the GFCS main controller receives a shutdown order and is considered to be completed when the GFCS enters power off state.

Table 1 : States of the GFCS in “Use life situation”

7.1.2. Startup and shutdown conditions

The startup of the system shall be conditioned by a/c (pilot) authorization.

The a/c shall be able to shut the system down in case of emergency.

7.2. Performance requirements

7.2.1. Output Voltages

The system shall be able to supply:

- 115VAC to supply Galley inserts

- 28VDC o supply Galley ancillaries and flight test load.



7.2.2. Output Power

The system shall be able to supply a maximum power of:

- 17kW in Galley configuration

- 9kW in flight test configuration.

7.2.3. Electrical efficiency

The system shall deliver its maximum power with a minimum efficiency of 40%.

7.2.4. Dynamics

The GFCS shall be able to reach maximum power from null power within 3s.

7.3. Operational requirements

7.3.1. Autonomous operation

The GFCS shall be able to operate without any human intervention

7.3.2. Autonomy

The GFCS shall be able to operate 4h in the test a/c without refilling.

The GFCS shall be able to operate 3h in Galley configuration without refilling.

7.3.3. Operational conditions

The GFCS shall comply with the operational envelope of §‎6.1.2

7.3.4. Operational lifetime

The GFCS shall be designed for a useful life of at least 3,500FH.

7.4. Logistic requirements

7.4.1. Lifting interfaces

The GFCS sub-assemblies shall integrate lifting interfaces for parts of more than 20kg.

7.4.2. Installation

Installation/removal time of each system’s equipment in the SPS shall not exceed 30 minutes.

7.4.3. Refueling

The GFCS refueling time shall not exceed 15 min.



7.5. Design requirements

7.5.1. Dimensions

The mass of the GFCS, excluding hydrogen storage, shall not exceed 200kg.

The volume of the GFCS, excluding hydrogen storage, shall not exceed 220L.

7.6. Safety Requirements

The safety analysis is described in the “Safety Analysis Report” (D1.2 deliverable).

The safety studies process follows ARP 4761.

7.7. Maintainability requirements

The GFCS shall allow light maintenance operations onboard.



8. Environmental Requirements

Unless specially agreed and specified, the applicable environmental requirements are based on EUROCAE ED14-F/RTCA DO160G.



9. Conclusions

The HYCARUS project aims to design a generic airborne hydrogen fuel cell system

compatible of two non-essential applications, model an essential one, develop, test and

demonstrate a galley while partially reusing produced heat, water and ODA for other

applications. The specification and the safety report will be used for all following WP in order

to provide the design and development of the GFCS. The “System Specification (D1.1)” and

the “Safety Report (D1.2)” will be the basis for the entire project.