Avionics-Power interfaces standardisation | An exportable ...

ESA UNCLASSIFIED - For Official Use

Avionics-Power interfaces standardisationAn exportable approach?

Ferdinando Tonicello, TEC-E, Electrical Department

16/10/2020

Power and Avionic Work Group*

Presented by

* Participants revealed in slide 13

ESA UNCLASSIFIED - For Official Use Ferdinando Tonicello, TEC-E, Electrical Department | ESA-TEC-HO-020560 | ESTEC | 16/10/2020 | Slide 2

Avionics-Power interfaces standardisation

Outline

• Preamble

• Motivation

• Subjects and objectives

• WG

• Methods

• Work in progress

• Conclusions…………………………………………………………………………………………….slide 22


Avionics-Power interfaces / PREAMBLEAcronyms• ADHA Advanced Data Handling Architecture

parallel studies (RUAG/ADS, TAS-I)

• DOD Depth of Discharge

• OBDH On-board Data Handling (SubSystem)

• EPS Electrical Power SubSystem

• MBSE Model Based System Engineering

• MPPT Maximum Power Point Tracker

• PCDU Power Conditioning and Distribution Unit

• S3R Sequential Shunt Switching Regulator

• SA Solar Array

• SADE Solar Array Drive Electronics

• SADM Solar Array Drive Mechanism

• SAR Solar Array Regulator

• SOC State of Charge

• SOH State of Health

(Key) definitions• Observability of a system

A system is said to be observable if its current state can be estimated using only the information from its outputs.In other words, one can determine the behaviour of the entire system from the system's outputs.

• Functional/logical viewThe perspective of a system that identifies its functionality without specifying the physical allocation of the relevant functions

• Physical viewThe perspective of a system that identifies its functionality including the physical allocation of the relevant functions


Electrical Power subsystem – a real view

Solar Array

SADM

SADE

PCDUSecondary DC/DC converters

Battery


Electrical Power subsystem

Solar Array

SADM

SADE

PCDUSecondary DC/DC converters

Battery

Electrical Power Subsystem (EPS)

Equipment 1

Equipment 2

Equipment n


o Many variants, according to mission (environment, orbits)

• Different solar arrays

• Different batteries

• Different PCDUs with different internal architectures

– Regulated or unregulated bus

– 28V, 50V, 100V regulated; around 28V or 50V unregulated (but not real standard)

• Different or no SADM/SADE…

• Different distribution lines (for essential, non essential equipment, heater lines, etc)

Electrical Power Subsystem variability


o It makes sense to be as general as possible…

Power Subsystem Reference Architecture … (to be continued)

`

Element1(E1)

Power line

Signal line

Pyro line

APS.P.a.1.s APS element, Interface P (power), interface type a,interface instance 1, source side s

TMTC.S.b.2.r TMTC element, Interface S (signal), interface type b,interface instance 2, receiver side r

PCDU.PY.g.3.l PCDU element, Interface PY (pyro), interface type g,interface instance 3, load side l

Legenda

Solar Array(SA)

Solar ArrayDrive

Electronics(SADE)

Power Conditioning and Distribution Unit

(PCDU)

PCD

U.P

.b.1

.l

PCDU.PY.a.1.s

SAD

E.P.

b.1.

s

SAD

E.P.

a.1.

l

SA.P

.a.1

.s

PCD

U.P

.a.1

.b

Battery(BATT)

BATT

.P.a

.1.b

PCD

U.P

.d.1

.s

PCDU.PY.a.2.s

PCD

U.P

.d.2

.s

PCDU.S.a.4.b PCDU.S.b.2.t

BATT.S.b.1.t

SADE.S.a.1.b

PCD

U.P

.c.1

.s

Power Subsystem


Avionics-Power interfaces / MOTIVATION

=> Standardisation effort

• At interface level

• As a first step towards more recurrent products

• With a realistic attitude based on consensus

• Making treasure of previous successful experiences

• With the aim to be MBSE ready!

Solar Array(SA)

Solar ArrayDrive

Electronics(SADE)


(PCDU)

PCD

U.P

.b.1

.l

PCDU.PY.a.1.s

SAD

E.P.

b.1.

s

SAD

E.P.

a.1.

l

SA.P

.a.1

.s

PCD

U.P

.a.1

.b

Battery(BATT)

BATT

.P.a

.1.b

PCD

U.P

.d.1

.s

PCDU.PY.a.2.s

PCD

U.P

.d.2

.s


BATT.S.b.1.t

SADE.S.a.1.b

Remote Terminal Unit(RTU)

RTU.S.a.4.b

RTU

.P.d

.2.l

RTU.S.b.2.rRTU.S.b.1.rRTU.S.a.1.b

PYRO1PCDU.PY.a.1.l

PYRO2PCDU.PY.a.2.l

UNIT1

UNIT1.S.a.2.b

PCD

U.P

.c.1

.s

UN

IT1.

P.c.

1.l

UNIT2

UNIT2.S.a.3.b

UN

IT2.

P.d.

1.l

UNIT2.S.c.1.b

RTU.S.a.2.b RTU.S.a.3.b RTU.S.c.1.b

Power Subsystem

SAR3SAR2

Solar Array Regulator 1

(SAR1)

APS3

APS.

P.c.

3.s

Control&Telemetry/telecommand Module*(CTM)

APS2

SAR

.P.f.

1.s

AuxiliaryPower

Supply 1(APS1)

APS.

P.c.

1.s

APS.

P.b.

1.l

APS.

P.a.

1.s

CTM

.P.a

.1.l

CTM.S.b.1.b CTM.S.b.2.b CTM.S.b.3.b

SAR

.P.f.

1.s

SAR

.P.f.

1.s

APS.

P.c.

2.s

CTM.S.a.1.b

CTM

.P.a

.1.l

CTM.S.a.2.b

Input switch/OvercurrentProtection 1

(OCP1) OC

P1.P

.e.1

.s

OC

P1.P

.d1.

l

OCP1.S.a.1.b

CTM.S.a.3.b

CTM

.P.a

.1.l

SAR

1.P.

c.1.

lSA

R1.

P.e.

1.l


(OCP1) OC

P2.P

.e.2

.s

OC

P2.P

.d.2

.l

OCP2.S.a.2.b


(OCP1) OC

P3.P

.e.3

.s

OC

P3.P

.d.3

.l

OCP3.S.a.3.b

LatchingCurrentLimiter 2(LCL2)LC

L2.P

.f.2.

l

LCL2.S.b.2.b

LCL2

.P.g

.2.s


L3.P

.f.3.

l

LCL3.S.b.3.b

LCL3

.P.g

.3.s

To load 1

To load 2

To load 3

FromSolarArray

NOTES

1. For simplicity the PCDU example contain just the Solar Array regulation part and not the battery management one2. * Provided with internal redundancy


L1.P

.f.1.

l

LCL1.S.b.1.b

LCL1

.P.g

.1.s


Avionics-Power interface / SUBJECTS AND OBJECTIVES


o Gives account of Power Subsystem large variability

o Realistic

• Covering those interfaces that are actually already largely used in applications

• No projection of too idealistic / too theoretical ideas

o Opportunistic

• Covering those (mature) interfaces for which standardization seems possible

• Considering that effective standardization is consensus based

Power Interfaces Standardisation – The approach used so far…


Power Interfaces Standardisation – key topics

`

Element1(E1)

Power line

Signal line

Pyro line

APS.P.a.1.s APS element, Interface P (power), interface type a,interface instance 1, source side s

TMTC.S.b.2.r TMTC element, Interface S (signal), interface type b,interface instance 2, receiver side r

PCDU.PY.g.3.l PCDU element, Interface PY (pyro), interface type g,interface instance 3, load side l

Legenda

Solar Array(SA)

Solar ArrayDrive

Electronics(SADE)


(PCDU)

PCD

U.P

.b.1

.l

PCDU.PY.a.1.s

SAD

E.P.

b.1.

s

SAD

E.P.

a.1.

l

SA.P

.a.1

.s

PCD

U.P

.a.1

.b

Battery(BATT)

BATT

.P.a

.1.b

PCD

U.P

.d.1

.s

PCDU.PY.a.2.s

PCD

U.P

.d.2

.s


BATT.S.b.1.t

SADE.S.a.1.b

PCD

U.P

.c.1

.s

Power Subsystem

Power distribution interfaces (source &

load) based on Latching

Current LimitersECSS-E-

ST&HB-20-20, 2016

Actuators power interfaces

(source and load)ECSS-E-ST&HB-20-

21, 2019

Failure Detection, Isolation and

Recovery

+ Secondary

power distributionTM/TC interfaces


o Identification and agreement on electrical power subsystem reference architectures

o Cooperation with any standardisation activity concerning back plane definition for avionic equipment (ADHA, other)

Power interfaces and SAVOIR, Prerequisites


Avionics-Power interfaces / (SAVOIR)WORKING GROUPToR agreed mid March 2020

Participation

ADS, N. Neugnot, J,. Seronie-Vivien

CNES, C. Elisabelair

DLR, N. Aksteiner

ESA, S. Landstroem, O. Mourra, F. Tonicello

OHB, J. Caudepon

RUAG, H. Myllymaki

SENER, C. Tato

TAS, G. Bouhours, J.L. Bolsee

7 Web-meetings performed so far


Avionics-Power interface / METHODSReference architecture definition!

• Two step approach, functional/logical layer first, physical layer after that

• Most importance given to the precise correspondence of verbal definitions and assumptions with the relevant reference block diagrams


Avionics-Power interface / METHODS / in practice…

1. Broad system/subsystem functional/logical definition => EPS2. Relevant (verbal) functions

functional/logical description (as exhaustive as possible)

Example

Power conditioningis the function of the powersubsystem dedicated to theconversion of power comingfrom power generation, andfrom or to energy storage to thepower bus. The powerconditioning function isregulated by the power controlfunction.





Example


3. Block diagram (“twin”) functional/logical function description

Example

Power conditioning

Power line Signal line

The arrows indicate the flow of power or of the signal

From/to Energy Storage

From Power Generation

From/to Power Control

From/to Power

Monitor

To Power

Bus





Example



Example

Power conditioning






From/to Power

Monitor

To Power

Bus

4. Overall Block diagram (“twin”) functional/logical function description

Example

Power generation

Power conditioning

Power control

Power distribution


Power monitor


Energy storage Power Bus





Example



Example

Power conditioning






From/to Power

Monitor

To Power

Bus

4. Overall Block diagram (“twin”) functional/logical function description

Example

Power generation

Power conditioning

Power control

Power distribution


Power monitor



5. “Get inside the box”, functional/logical function description

Example

Power distribution

Deployment Actuator

Electronics

Platform and payload

equipment distribution

Thermal heater distribution

Power distribution


PCDU


Power generation

Power conditioning

Power control

Power distribution


Power monitor



From functional/logical to physical block diagram / ”allocation”


Avionics-Power interface / METHODS / in practice…From functional/logical to physical block diagram / ”allocation”

Power distribution

Power monitor

Power generation

Power conditioning

Power control




PCDU

Some monitor sub-function is done outsidethe PCDU (e.g. in the OBDH)


PCDU

Power distribution

Power monitor

Power generation

Power conditioning

Power control




Avionics-Power interface / METHODS / in practice…From functional/logical to physical block diagram / ”allocation”

Some monitor sub-function is done outsidethe PCDU (e.g. in the OBDH)

Some distributionsub-function is done outside the PCDU (example: in the PPU)


Avionics-Power interface / METHODS / in practice…Instantiation of physical functions, where interfaces are impacted

SA conditioning

SAR

S3R

SA conditioning

SAR

Converter

MPPT

Power conditioning




From/to Power

Monitor

To Power

Bus

SA conditioning

Battery charge and discharge


Avionics-Power interface / WORK IN PROGRESS

• Reaching agreement on

• Functional/logical EPS description, including both nominal and contingency aspects

• The level of depth to go to(see “Get inside the box” , slide 15)

• Possible instantiation options on EPSphysical view

• Starting to identify the observability andcommandability needs of all Primes/LSI and translate this need into standard interfaces where possible and convenient


Avionics-Power interface / WORK IN PROGRESS / exampleDiscussion on

EPS observable items, as an input for the agreed telemetry set (and the relevant interfaces, according to possible instantiation of the physical layer)

Observable items

Information available for Flight/Ground/AIT purposes

Processing Accuracy

Battery DOD Flight second ±3% of DODBattery SOC Flight second ±5% of SOCBattery SOH Ground month ±3% of SOHBattery internal impedance (DC, AC) Ground hour ±10% of full scaleBattery temperature Ground minute ±2°CSA instantaneaous output power Ground second ±3% of full scaleSA available power (of possible) Ground second ±3% of full scale… … … …… … … …


Avionics-Power interface / CONCLUSIONS

Too early to have some definitive conclusions, but…

1. We identified a workable way to have a MBSE ready approach to reference architecture! (see “ METHOD” slides)

2. Whatever the level of interface definition we will achieve, it will be agreed by European Large System Integrators, European Agencies and by some of the most important power equipment manufacturers and users

3. This (interesting) work continues…

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