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Common Avionics- Page 17/25/2012
Common Avionics Approach
SpaceAGE Bus & cFE/CFS:
Software & Hardware Component Based Architecture
Presenters: Jonathan Wilmot & Glenn Rakow
NASA-GSFC
Common Avionics- Page 27/25/2012
Background: Avionics Current Practice
• Each organization that builds space systems has their own approach to implementation, so within organizations there are de facto standards– Necessary to save money– Or make profit
• However among space builders there is little interoperability– Mechanical approach differences– Electrical interfaces differences– Software architecture differences
• Even though the implementation methods used are very similar– Procured Single Board Computer – BAE Rad750, Leon 3– Bus protocols – Mil-Std-1553, SpaceWire– Mechanical approach – Backplane in mechanical chassis– etc.
Common Avionics- Page 37/25/2012
Basic Tenets – Common Avionics
Standards
Hardware SoftwareCommonAvionics
• Standards – Interfaces, protocols, electronic data sheets, examples:– CCSDS AOS, Internet Protocol (IP), xTEDS
• Software architectures, examples:– Frameworks, design patterns, Application
Programmer Interfaces (API),
• Hardware – Interfaces, form factors, protocols, examples:– SpaceWire, Mil 1553b, RMAP, USB PnP, 6U
• Each of these can stand alone and be applied to a wide variety of missions– Missions may use 1553, or CCSDS AOS but
can not interoperate– Current approach for many organizations
• Common Avionics are defined by the intersection– Each organization can define it’s own
intersection, common only to that organization• Example: AFRL Space Plug-and-play Avionics
(SPA)
Common Avionics- Page 47/25/2012
Common Avionics Goal
• Reduce Non Recurring Engineering cost of space avionics through reuse
• Be applicable to majority of space missions both robotics and crew rated vehicles
• Compatibility of avionics between vendors– Necessary for Human Exploration Programs
• Develop different vehicles/systems from same components• Increase pool of compatible products
– Focus limited resources to create synergy in space industry
• Technology independent – focus on interfaces not implementations– Protocols not defined
• Few possibilities - allows space community to converge based upon demand• Provides system engineer flexibility
• Stream-line integration of avionics components (hardware & software) similar to commercial “plug-n-play”
Common Avionics- Page 57/25/2012
Common Avionics Business Model
• Encourage exchange of designs in open market that may be integrated to implement system– Designs may have different levels of compatibility but market forces
should force convergence to small group of options
• Government agencies use tech transfer offices to make designs available to industry that can then be purchased on open market– Current example:
• GSFC developed the SpaceWire Test Set (SWTS) hardware and software.• Via Tech Transfer office, SWTS designs provided to support contractor, who
markets and sells the SWTS product.• Effort involves procuring the Printed Wiring Board (PWB), outsource the PWB
assembly, and test with software.• To date 150 SWTS have been built for multiple agencies and projects
• Currently, GSFC cFE/CFS and SpaceWire IP core (both software products) are widely distributed and used on non-GSFC missions– Help is needed in developing a governance model for
maintaining/updating code
Common Avionics- Page 67/25/2012
Avionics cost savings•Development cost => Build-to-Print
•Hardware cost approaches a reduction of 80-90%
•Based upon LCRD HSE budget
•Reduction of quality assurance and system engineering due to COTS component
•Reduction of risks
•Reduction of documentation
•Reduction of schedule and manpower•Time is money => delay requires funding to carry manpower longer
•Less development
Potential New Budget Model
Cost
Reuse
Build-to-Print
Common Avionics- Page 77/25/2012
Building Block Elements
Definition:• Building block element is a software or hardware functional
standalone unit of implementation with completely defined interfaces, so that they can be integrated together to form increasingly complex systems.
Examples:• Hardware
– Printed Wiring Boards (PWBs) built to a standard mechanical form factor with defined electrical interfaces
– Modules – comprised of a single or multiple PWBs integrated together into a mechanical card frame to form a increasingly complex function
• Software– Software component that has interface to a defined software bus so that
a publish/subscribe messaging service– Hypervisor – supports low level time-space partitioning to protect the
operating system from crashing
Common Avionics- Page 87/25/2012
NASA/GSFC’s Flight Software Architecture:Core Flight Executive and
Core Flight System
Jonathan Wilmot
Software Engineering Division
NASA/Goddard Space Flight Center
Jonathan.J.Wilmot@nasa.gov
301-286-2623
Common Avionics- Page 97/25/2012
cFE/CFS Introduction
coreFlight
Executive(cFE)
CFSApp
CFSApp
CFSApp
CFSApp
CFSAppCFS
Library
CFSApp
CFSLibrary
• Core Flight System (CFS)– A Flight Software Architecture
consisting of the cFE Core, CFS Libraries, and CFS Applications
• core Flight Executive (cFE)– A framework of mission
independent, re-usable, core flight software services and operating environment
• For cFE/CFS, each element is a separate loadable file
Core Flight System (CFS)
Common Avionics- Page 107/25/2012
CFS Flight Software Layers
Real Time OSReal Time OS
OS Abstraction Layer
OS Abstraction Layer
cFE Platform Support Package
cFE Platform Support Package
cFE CorecFE Core
CFS LibraryCFS Library MissionLibraryMissionLibrary
CFS App 1CFS
App 1CFS
App 2CFS
App 2MissionApp 1
MissionApp 1
Mission App 2
Mission App 2
CFS App NCFS
App NMission App N
Mission App N
PROM Boot FSWPROM Boot FSW
Mission and CFSApplication Layer
Mission and CFSLibrary Layer
CFE CoreLayer
AbstractionLibrary Layer
Mission Developed
GSFC Developed
3rd Party
RTOS / BOOTLayerReal Time OSReal Time OS Board Support
PackageBoard Support
Package RTEMS, VxWorks, Linux
http://sourceforge.net/projects/coreflightexec
http://sourceforge.net/projects/osal
Common Avionics- Page 117/25/2012
cFE Core - Overview
• A set of mission independent, re-usable, core flight software services and operating environment– Provides standardized Application Programmer Interfaces (API)– Supports and hosts flight software applications– Applications can be added and removed at run-time (eases system
integration and FSW maintenance)– Supports software development for on-board FSW, desktop FSW
development and simulators– Supports a variety of hardware platforms– Contains platform and mission configuration parameters that are used to
tailor the cFE for a specific platform and mission.
Executive Services (ES)
Software Bus (SB)
Time Services (TIME)
Event Services (EVS)
TableServices (TBL)
Common Avionics- Page 127/25/2012
Hardware I/Fs
Exemplar GSFC Flight Software Architecture
Inter-task Message Router (SW Bus)
EventServices
EDACMemoryScrubber
Stored Commanding CFDP File
Transfer
Software
Scheduler
Housekeeping
Manager
ExecutiveServices
TimeServices
FileManager
Commands
cFE Components
C&DH Components
Real-time Telemetry
CommunicationInterfaces GN&C Components
LocalStorage
1553 BusSupport
File downlink (CFDP) via SpaceWire
SoftwareBus
InstrumentManagers
CommandIngest
Telemetry Output
1553 Hardware
Memory
Manager
DataStorage
MassStorage
File System
TableServices
AttitudeDetermination
&Control
LimitChecker
SpaceWire
Sensor/actuatorI/O handlers
OrbitModels
SolarArray
High-GainAntenna
Instruments
Note - Some connection omitted for simplicity
Sensors & Actuators
Hardware I/Fs
Device adapters
Common Avionics- Page 137/25/2012
Facets of Common Avionics
• Software– NASA cFE/CFS example of a component software architecture
• Hardware– SpaceAGE bus (intra-box interface definition)
• Modular• Standalone• Scalable
• Interface Control Document definition• Maintain reasonable flexibility with these area
Examples:– Software – allow different operation systems– Hardware – allow different protocols– Electronic Data Sheet (EDS) – work with different software architecture
Common Avionics- Page 157/25/2012
SpaceAGE busIntra-Box Interface Definition
• SpaceAGE bus defines how to integrate Hardware modules together – analogous to cFE/CFS software bus
• Hardware modules analogous to cFE/CFS software components• 2 module types defined – Hub and Node – every box has 1 Hub and one
or more Nodes– Serial interfaces; Protocol agnostic
• Electrical interfaces- Power; Comm; Analog; Clock; Reset; Converter Sync; Module Detect
• Mechanical interface – Card frame– No backplane nor chassis– X&Y dimensions defined – Z (height) not defined (flexible)
• FOMs:– Minimize NRE (cost and schedule)– Broad mission applicability – supports all reliability schemes (cross-strapped, etc.)– Incremental Design
Common Avionics- Page 167/25/2012
NodeModule
Node Module
Node Module
Node Module
Node Module
Node Module
Node Module
HubModule
SpaceAGE Bus Architecture
Legend
SpaceAGE Bus Interface • power• comm.• analog• miscellaneous signals
• typically used for avionics systems
Common Avionics- Page 177/25/2012
HeaterCard
PropCard
PyroCard
ExternalVehicle Control
Bus
HubModule
RIU Example using Integrated Modular Avionics (IMA) Approach
Time Triggered TTP/C (~10 MHz), with Bus Guardian
Legend
Processing, implementation not specified (could be embedded in FPGA)
TTP/CSwitch External I/F to
Higher Controller
Time
Epoch Epoch
TimeSlot
Hypervisor implementing “skinny” version of time-space partitioningSynchronized to Time-triggered data bus
Common Avionics- Page 187/25/2012
ExternalVehicle Control
Bus
HubModule
Distributed IMA (DIMA) Approach
Time Triggered TTP/C (~10 MHz), with Bus GuardianLegend
Processing, implementation not specified (could be embedded in FPGA)
TTP/CSwitch
ExternalVehicle Control
Bus
HubModule
ExternalVehicle Control
Bus
HubModule
NodeNode
Node
Node
Node
Node
CPU1
CPU2
CPU3
Function 1Control
Application
Function 2Control
Application
Function 3Control
Application
OperatingSystem
CPU1
OperatingSystem
CPU2
OperatingSystem
CPU3
CPU1
CPU2
CPU3
sleep sleep
sleepsleep
sleep sleep
sleepsleep
Multiple Timelines Illustrating Distributed Processing Concurrently
Common Avionics- Page 217/25/2012
Altair Avionics Design Approach (Distribution Process)
• Break vehicle up into sectors– AM and AL into quadrants– DM into upper and lower quadrants
• Gather the MEL components (sensors and actuators) into the various sectors per subsystem function– From ProE vehicle layout drawing
• Select module functions to perform requirement• Estimate board and box sizes and locate Distributed Avionics Units
based upon data to minimize harness mass– Rule of thumb – keep sensors and efforts within 10 feet of Remote Interface Unit
(RIU) – point where harness mass dominates box mass– Otherwise consider adding additional RIU in area
• Reliability analysis• Iterate
Common Avionics- Page 227/25/2012
Location on Vehicle (Example: AM Functions per Quadrant)
23
4 1
1 2 3 4
He Tank w/ Iso
RCS Thruster Pod
GO2 Tanks, Pri & Sec
GN2 Tank
SIRU (2)
He Tank
RCS Thruster Pod
Pumps (2) and Accum., PG Loop
Antenna, S-band
Antenna, Emergency
Bus Repeater
He Tank
RCS Thruster Pod
Antenna, S-band
Antenna, Emergency
Pyro Firing Circuit RMUX A
Bus Repeater
He Tank
He Pyro Valves
RCS Thruster Pod
Get Home GO2 Tank
Sublimator H2O Tank
Inertial Meas. Unit
1/2
MMH Tank w/ Iso
NTO Tank w/ Iso
MMH Tank w/ Iso
NTO Tank w/ Iso
3/4
Optics, LIDAR
GN&C System
4/1
Antenna, S-band
Antenna, Emergency
Battery, Primary
Suit Loop Controllers, P&R
Avionics, LIDAR
2/3
Flight Computer
RMUX, CSA
RMUX
Rendezvous Camera
C&T Radio
Star Tracker
Swing Beds, Amine (2)
Major Constituent Analyzer
Fan Controller
Instrumentation Box **
Side Hatch
Monitor
Keyboard
Controllers (2) Trans, Rotational
Long-Range laser Range Finder
Crew Interface Unit (2)
Crew Microphone Speaker
Monitor
Keyboard
Controllers (2) Trans, Rotational
Crew Interface Unit (2)
PDU, Type-1
Accumulator, potable water
Heat Exchanger, LCG Loop
Urine/Waste Collection
Pressurized AM
Unpressurized AM
N2 Controller
Pyro Firing Circuit RMUX B
Flight Computer
Flight Computer
Router, C3I
Video Processing Unit
Disconnect system, AM/DM
Sublimators (2)
Biocide Tank
Propellant Manifold
Electronics, Displays/Controls
Bus Repeater, CSA
Running Light
Running Light
Communication Hub, RCS
Sec. Structure, Instrumentation, RCS
Main Engine
Top HatchBed, Trace
Contaminant Control
Suit Loop Compressors (2)
Suit Loop Heat Exchanger
Life Support System *
Vehicle Assembly Interface (2)
Vehicle Assembly Interface (2)
Cabin Heat Exchanger
Cabin Fan
Internal Light
Propulsion
ECLSS
C&T
Electrical Power
GN&C
C&DH
Active Thermal Control
Mechanisms
Unknown/Undetermined
* Assumed based on location of “Life Support System Mounting”
** Assumed based on location of “Instrumentation Box Mounting”
Common Avionics- Page 237/25/2012
Propulsion Functions per Module/Sector
VDVSTP
ΔPFI
Valve DriverBilevel Valve StatusTemperaturePressureDiff. PressureFlow IndicatorOxygenO2
Q Liquid Quantity
Stepper Motor DriverPosition Indicator
Ctrl Embedded Controller/Electronics
He Tank
LH2Tank
T T
P P
He Tank
T TH(2)* H(2)* H(2)* H(2)*
NTOTank
MMHTank
T(2)*T(2)*H(2) H(2)
Q Q
MMHPyro Vlv
NTOPyro Vlv
NSI NSINSI NSI
DM RCS Propulsion Tanks
P P
HeLH2-Ld
Pyro VlvHeLO2-Ld
Pyro VlvNSI NSINSI NSI
VD(2)VS(2)
HeLH2
Iso VlvsVD(2)VS(2)
VD(2)VS(2)
HeLO2
Iso VlvsVD(2)VS(2)
HeLH2-Dr
Pyro VlvNSI NSI
HeLO2-Dr
Pyro VlvNSI NSI
VD(2)VS
HeLH2
Vent VlvsVD(2)
VSVD(2)
VSHeLO2
Vent VlvsVD(2)
VS
VD(2)VS
HeLO2
VlvHeLH2-Dr
Pyro VlvNSI NSI
DM MPS LH2 He Pressurization DM MPS LO2 He Pressurization
VDVS
HeIso Vlv
VDVS
HeIso Vlv
HeMech
Regulator
HeMech
RegulatorP P
PT
HeRelief Vlv
HeRelief Vlv
DM He Pnuematic Control Regulator
VDVS(2)
PneIsol Vlv
VDVS
LH2TVS Vlvs
VDVS
VS(2)LH2 TnkVent Vlv
P P
TΔP
L Liquid DepletionSMD*
PI*
LQP
VDVS
LH2TVS Vlvs
VDVS
LH2Stir Fans
LH2 Heat Exch
DM LH2 Tank (x4)
VDVS(2)
PneIsol Vlv
VS(2)LO2 TnkVent Vlv
P P
DM LO2 Tank (x4)
PT
PT
LO2Tank
VDVS
LO2TVS Vlvs
VDVS
TΔP
LQP
VDVS
LO2TVS Vlvs
VDVS
LO2Pumps
LO2 Heat Exch
LH2Manifold
LO2Manifold
PT
PT
LH2 Vent Vlvs
LO2Vent Vlvs
VD(3)VS(2)
VD(3)VS(2)
LH2 PneFill Vlv
LO2 PneFill Vlv
VS(2) VS(2)
TP
TP
DM Manifolds and DME Feed
He Tank
VD(2)VS
HeIso Vlv
VD(2)VS
He Tank
He Tank
He Tank
HeIso Vlv
VD(2)VS
HeIso Vlv
HeMech
Regulator
HeMech
Regulator
HeMech
Regulator
VD(2)VS
HeMMH
Iso VlvVD(2)
VS
BurstDisk
HeNTO
Pyro VlvsNSI(7) NSI(7)
BurstDisk
AM He Pressurization
NTOTank
MMHTank
MMHIsol Vlv
NTOIsol Vlv
AM Propulsion Tanks
NTOTank
MMHTank
VD(2)VS
VD(2)VS
VD(2)VS
VD(2)VS
VDVS
MMHIso1 Vlv
VDVS
A1
MMH Iso2 Vlv
A2
A3
A4VD(2)
P*T(4)*
VDVS
NTOIso1 Vlv
VDVS
NTO Iso2 Vlv
AM RCS Thruster Pod A
A5
PneIsol Vlvs
VD(2)VS(2)
VD(2)VS(2)
He Purge Vlvs
VD(2)VS(2)
VD(2)VS(2)
AM Ascent Main Engine
DM Descent Main Engine
Pne LH2Prestart
Vlvs
VDVS(4)
P
Pne LO2Prestart
Vlvs
VDVS(4)
P
HeCooldwn
Vlv
VDVS(2)
P
LO2Cnt Vlv
SMDPI
LO2Pump
RPM
RPM Tachometer
PT
DMEP
HeStart Vlv
VDVS(2)
P
LH2Pump
RPMT
Pne LH2DscRlfBld
VlvVS(2)
LH2Cvt Vlv
SMDPI
P(2)
Pne LH2IntCldBld
VlvVS(2)
P(3)
Pne LH2MnSht
VlvVS(2)
LH2 Pump
Byp Vlv
SMDPI
LH2 ThrCnt
Vlv
SMDPI
T
VD(4)VS(2)
RCS HeIsol Vlvs
HeMMH
MechRegulator
HeNTO Mech
Regulator
HeMMH
Pyro VlvHeNTO
Pyro VlvNSI NSINSI NSI
DM RCS He PressurizationTP
TP
TP
BurstDisk
BurstDisk
P
H H
MMHPyro Vlv
NSI NSI
VD(2)VS
MMHIso1 Vlv
VD(2)VS
A1
VD(2)P
T(4)*
MMH Iso2 Vlv
A2
A3
A4
VD(2)VS
NTOIso1 Vlv
VD(2)VS
NTO Iso2 Vlv
DM RCS Thruster Pod A
MMH Tank
MMHPyro Vlv
NSI NSI
MMHPyro Vlv
NSI NSI
DM MMH Vent
P(2) P(2)
T
P
P
T
T
H H
HH
H(2)
P(4)T(2)
He Fl VlvVDVS
P
P P
QT
QT
QT
QT
HT*
HT*
HT*
HT*
H(2)
P(2) P(2)
VD(2)P*
T(4)*H(2)
VD(2)P*
T(4)*H(2)
VD(2)P*
T(4)*H(2)
VD(2)P*
T(4)*H(2)
T
PP
VDVS
MMHIso1 Vlv
VDVS
B1
MMH Iso2 Vlv
B2
B3
B4VD(2)
P*T(4)*
VDVS
NTOIso1 Vlv
VDVS
NTO Iso2 Vlv
AM RCS Thruster Pod B
B5
HT*
HT*
HT*
HT*
H(2)
P(2) P(2)
VD(2)P*
T(4)*H(2)
VD(2)P*
T(4)*H(2)
VD(2)P*
T(4)*H(2)
VD(2)P*
T(4)*H(2)
T
VDVS
MMHIso1 Vlv
VDVS
C1
MMH Iso2 Vlv
C2
C3
C4VD(2)
P*T(4)*
VDVS
NTOIso1 Vlv
VDVS
NTO Iso2 Vlv
AM RCS Thruster Pod C
C5
HT*
HT*
HT*
HT*
H(2)
P(2) P(2)
VD(2)P*
T(4)*H(2)
VD(2)P*
T(4)*H(2)
VD(2)P*
T(4)*H(2)
VD(2)P*
T(4)*H(2)
T
VDVS
MMHIso1 Vlv
VDVS
D1
MMH Iso2 Vlv
D2
D3
D4VD(2)
P*T(4)*
VDVS
NTOIso1 Vlv
VDVS
NTO Iso2 Vlv
AM RCS Thruster Pod D
D5
HT*
HT*
HT*
HT*
H(2)
P(2) P(2)
VD(2)P*
T(4)*H(2)
VD(2)P*
T(4)*H(2)
VD(2)P*
T(4)*H(2)
VD(2)P*
T(4)*H(2)
T
T(2)P(2)P(2)
AMEP(4)
T(4)PI(4)
T
T* T*
T* T*
T*T*
VD(2)P
T(4)*H(2)
VD(2)P
T(4)*H(2)
VD(2)P
T(4)*H(2)
MMHPyro Vlv
NSI NSI
VD(2)VS
MMHIso1 Vlv
VD(2)VS
C1
VD(2)P
T(4)*
MMH Iso2 Vlv
C2
C3
C4
VD(2)VS
NTOIso1 Vlv
VD(2)VS
NTO Iso2 Vlv
DM RCS Thruster Pod C
P(2) P(2)
T
H H
HH
H(2)
T* T*
T*T*
VD(2)P
T(4)*H(2)
VD(2)P
T(4)*H(2)
VD(2)P
T(4)*H(2)
MMHPyro Vlv
NSI NSI
VD(2)VS
MMHIso1 Vlv
VD(2)VS
B1
VD(2)P
T(4)*
MMH Iso2 Vlv
B2
B3
B4
VD(2)VS
NTOIso1 Vlv
VD(2)VS
NTO Iso2 Vlv
DM RCS Thruster Pod B
P(2) P(2)
T
H H
HH
H(2)
T* T*
T*T*
VD(2)P
T(4)*H(2)
VD(2)P
T(4)*H(2)
VD(2)P
T(4)*H(2)
MMHPyro Vlv
NSI NSI
VD(2)VS
MMHIso1 Vlv
VD(2)VS
D1
VD(2)P
T(4)*
MMH Iso2 Vlv
D2
D3
D4
VD(2)VS
NTOIso1 Vlv
VD(2)VS
NTO Iso2 Vlv
DM RCS Thruster Pod D
P(2) P(2)
T
H H
HH
H(2)
T* T*
T*T*
VD(2)P
T(4)*H(2)
VD(2)P
T(4)*H(2)
VD(2)P
T(4)*H(2)
T(2)*T(2)*T(2)*T(2)*
1 1/2
4
3
2 4/1
3/4
2/3
2U3U
2U
1U
4U
3U
2L
L
2U
UU
1 2
3 4
1/2 1/2
3/4 3/4
1 2 3 43L 1L
2U
3U
3U
2U
2U
1U3U
L
L
L
L
2U
Could not find separate valves/pumps. Assume
this is all part of the “turbo pump” assembly in bottom
center
1
4
Unconnected on schematic - couldn’t find in
CAD model.
One Isol. Valve on each tank
Assume Iso Valves are included in thruster pods.
Couldn’t find valves on CAD. He doesn’t run to
AME.
Common Avionics- Page 247/25/2012
Distributed Avionics Unit Configuration
Common Controller Slice (HUB)
Subsystem Specific Slicee.g. Propulsion
Subsystem Specific Slicee.g. Thermal
EMI Filter
Logic
Cross Bar Switch(Serial Backplane)
Rx Tx
Vehicle Control Bus(Protocol Program Specific)
Micro-processor
MemoryMemory
ManagementUnit
SwitchingIsolated
& POL; LDO
+28V
VDD
Current LimiterCircuit Breaker
Current LimiterCircuit Breaker
Current LimiterCircuit Breaker
Current LimiterCircuit Breaker... ...Switching
Isolated&
POL; LDO
TargetInterface
Power DriverCircuit(s)
AnalogSensingCircuits
(Optional)
VDD
...
SwitchingIsolated
&POL; LDO
TargetInterface
Power DriverCircuit(s)
AnalogSensingCircuits
(Optional)
VDD
...
PrimaryVoltage
Vehicle Control BusPass-Thru
PowerEffectorsEffectors Sensors Sensors
Rx TxRx Tx Rx TxRx Tx
Pass-ThruPower
Cabled Interfaces (just Power & Comm. Shown)
Common Avionics- Page 257/25/2012
Example RIU - AM Monitor 1
E-A
-C
H18
D4H
32D
AT-
A-
CH
16V
6H32
DA
Pow
er S
upp
ly
&C
ontr
olle
r
End
Cap
ECLSS
ATCS
C&DH
C&T
Power
GN&C
Mech
Prop
Structure
ATCS
End
Cap
Functional Description:
C&TRF Switches
ECLSSVent valvesLGC systemPotable waterSuit loopSwing bed controlCabin air supplyCabin air returnCabin Waste venting
ATCSPumpsAccumulatorPropylene Glycol Loop
PowerSwitching
Location:AM Pressurized
Size:10” x 7.5” x 6.5” (L x W x H) L x W = mounting surface (includes 0.75” flange)W x H = connector face
P-A
-CH
16H
P-A
-CH
16H
E-A
-C
H18
D4H
32D
A
Con RPC 1 FET 2 FET3
FET Analog Inputs Digital InputsPowerWiring
C&DH Wiring 22 AWG
Name Type
Relay
RPCSw
ServH RD VD SMD NSI VS T P dP L Fl O2 Q Pl
Network
Serial
RPM
Power
ServicesAWG ??
Power
ServicesAWG 16 TP
Power
ServicesAWG 20 TP
AWG 22 TSP
AWG 26 TSP
AWG 26 TST
Harness Mass (80 wires @
10ft)
Mass(Kg)
Power(W)
TOTAL 26 8 18 1 25 4 10 2 1 3 2 1 1 4 6 27 49 4 5.6 kg 7.81 21.00Controller & PS HUB-6U 1 4 1 1 4 1.07 4.80AM C&T Monitor 1 C-6U-CH18D4H32DA 8 13 1 8 13 1.07 0.98AM ECLSS Monitor 1 E-6U-CH18D4H32DA 14 1 10 4 8 2 1 2 2 1 1 15 30 1.07 2.23AM ATCS Monitor 1 T-6U-CH16V6H32DA 4 2 2 1 1 4 5 1.07 2.78AM Monitor 1, SSC 1 S-6U-CH16 13 1 1.07 5.11AM Monitor 1, SSC 2 S-6U-CH16 13 1 1.07 5.11Internal Harness 0.85 End Caps (2 ea) 0.54
Common Avionics- Page 267/25/2012
Example RIU - AM Prop Monitor
ECLSS
ATCS
C&DH
C&T
Power
GN&C
Mech
Prop
Structure
ATCS
P-A
-C
H11
T32
DA
Pow
er S
upp
ly
&C
ontr
olle
r
End
Cap
End
Cap
P-A
-C
H11
T32
DA
Functional Description:PropHe Tanks StatusHe Tanks Iso ValvesMMH Tanks StatusMMH Tanks Iso ValvesNTO Tanks StatusNTO Tanks Iso Valves
PowerSwitching
Location:AM Unpressurized
Size:10” x 5.5” x 6.5” (L x W x H) L x W = mounting surface (includes 0.75” flange)W x H = connector face
P-A
-CH
16H
Con RPC 1 FET 2 FET3
FET Analog Inputs Digital InputsPowerWiring C&DH Wiring 22 AWG
Name Type
Relay
RPCSw
ServH RD VD SMD NSI VS T P dP L Fl O2 Q Pl
Network
Serial
RPM
Power
ServicesAWG ??
Power
ServicesAWG 16 TP
Power
ServicesAWG 20 TP
AWG 22 TSP
AWG 26 TSP
AWG 26 TST
Harness Mass (49 wires @
10ft)
Mass(Kg)
Power(W)
TOTAL 13 19 10 6 9 4 1 4 19 30 3.4 5.47 11.93Controller & PS HUB-6U 1 1 1 1.07 4.80AM Prop Mon AME P-6U-CH11T32DA 10 5 3 5 2 1 10 15 1.07 1.01AM Prop Mon AME P-6U-CH11T32DA 9 5 3 4 2 1 9 14 1.07 1.01AM Prop Monitor, SSC 1 S-6U-CH16 13 1 1.07 5.11Internal Harness 0.65 End Caps (2 ea) 0.54
Common Avionics- Page 277/25/2012
Avionics Totals
Con RPC 1 FET 2 FET3
FET Analog Inputs Digital InputsPowerWiring C&DH Wiring 22AWG
Module Box
Relay
RPCSw
ServH
RF SW
VD SMD NSI VS T P dP L Fl O2 Q PlNetwork
Serial
RPM
Power
ServicesAWG ??
Power
ServicesAW
G 16 TP
Power
ServicesAW
G 20 TP
AWG 22 TSP
AWG 26 TSP
AWG 26 TST
# wires 10ft)
Harness
MassMass(Kg)
Power(W)
Grand Total 15 150 249 121 18 289 15 58 225 271 170 10 10 6 3 14 17 26 4 150 96 501 752 4 204.02 342.74AM Total 5 65 121 59 16 120 1 20 86 130 70 2 2 5 2 4 5 12 4 65 42 216 318 4 535 37.4 88.87 151.82 AM Monitor 1 Total 26 8 18 1 25 4 10 2 1 3 2 1 1 4 6 27 49 4 80 5.6 7.71 21.00 AM Monitor 2 Total 26 3 8 27 35 20 15 1 2 4 1 7 38 78 116 8 8.88 22.02 AM Prop Monitor Total 13 19 10 6 9 4 1 4 19 30 49 3.4 5.37 11.93 AM RCS Driver 1 Total 14 14 4 25 9 1 3 28 39 67 4.7 4.20 10.72 AM RCS Driver 2 Total 14 14 4 25 9 1 3 28 39 67 4.7 4.20 10.72 AM RCS Driver 3 Total 14 14 4 25 9 1 3 28 39 67 4.7 4.20 10.72 AM RCS Driver 4 Total 14 14 4 25 9 1 3 28 39 67 4.7 4.20 10.72 AM Pyro Driver (P) Total 10 1 3 10 1 11 0.8 4.20 6.15 AM Pyro Driver (R) Total 10 1 3 10 1 11 0.8 4.20 6.15 AM MBSU Total 5 11 1 11 1 1 22.38 6.05 AM PDU 1 Total 30 28 1 30 3 1 10.26 18.13 AM PDU 2 Total 24 28 1 24 3 1 9.05 17.51DM Total 10 76 121 62 2 162 14 38 132 138 97 8 8 1 10 12 12 76 50 278 418 693 48.4 106.66 172.73 DM Monitor 1 Total 13 36 12 34 12 18 1 12 1 7 48 78 126 8.8 8.88 20.27
DM Prop Mon MPS 1 Total 14 4 32 44 17 23 4 4 4 1 6 36 97 133 9.3 7.71 20.65
DM Prop Mon MPS 2 Total 14 4 26 35 14 18 4 4 4 1 6 30 80 110 7.7 7.71 20.65
DM RCS Driver 1 Total 13 12 2 16 2 5 21 8 1 5 32 35 67 4.7 6.54 16.26
DM RCS Mon Driver 2 Total 13 18 20 6 32 14 2 1 5 38 55 93 6.5 6.54 17.97
DM RCS Driver 3 Total 13 12 16 4 21 8 1 4 28 34 62 4.3 5.37 15.28 DM RCS Driver 4 Total 13 12 16 4 21 8 1 4 28 34 62 4.3 5.37 15.28 DM Pyro Driver (P) Total 19 1 4 19 1 20 1.4 5.37 6.83 DM Pyro Driver (R) Total 19 1 4 19 1 20 1.4 5.37 6.83 DM MBSU Total 10 17 1 17 1 1 29.60 6.67 DM PDU 1 Total 30 14 1 30 2 1 9.09 13.03
DM PDU 2 Total 29 14 1 29 2 1 9.09 13.03AL Total 9 7 7 7 3 3 1 2 9 4 7 16 22 1.5 8.49 18.19 AL ECLSS Monitor Total 7 7 3 3 1 1 2 7 15 22 1.5 3.03 7.03 AL PDU Total 9 7 1 9 2 1 5.45 11.15
Common Avionics- Page 287/25/2012
Portion of Altair C&DH MELDistributed Control Unit (DCU); DM Reaction Control System (RCS) Monitor/Driver # 4
100 HUB-6U101 P-6U-CH8T6H32DA; Propulsion driver, heater, telemetry card102 P-6U-CH8T6H32DA; Propulsion driver, heater, telemetry card103 S-6U-CH16; Power switched service card104 DCU internal cable harness105 Enclosure end plates
Distributed Control Unit (DCU); DM Pyrotechnics Drive, Prime106 HUB-6U107 I-6U-CH7N108 I-6U-CH7N109 I-6U-CH7N110 DCU internal cable harness111 Enclosure end plates
Distributed Control Unit (DCU); DM Pyrotechnics Drive, Redundant112 HUB-6U113 I-6U-CH7N114 I-6U-CH7N115 I-6U-CH7N116 DCU internal cable harness117 Enclosure end plates
Distributed Control Unit (DCU); AL, ECLSS Monitor118 HUB-6U119 E-6U-CH18D4H32DA; ECLSS driver, heater, status card120 DCU internal cable harness121 Enclosure end plates
Flight Computer; AM, # 1122 HUB-6U123 CDH-6U-SBC124 DCU internal cable harness125 Enclosure end plates
Common Avionics- Page 307/25/2012
Building Blocks Used on LCRD
• Three building block elements initially developed– Reprogrammable Digital board– Analog board– Memory board
• Schematics developed initially under constellation funding• Layout and reviews done under LCRD funding• Boards can be interconnected within modules to form different
functional modules– HUB – Digital board and Analog board– Data Processing Storage Unit (DPSU) – Digital board and Memory board– Channel Coding Output Buffer (CCOB) – 2 Digital boards
• Approach allowed different combinations of boards and modules to be traded to match performance requirements– Allowed board development to continue as system changed
Common Avionics- Page 317/25/2012
LCRD Application of Building Blocks
• Data Processing and Storage Unit (DPSU)– Stores high rate data for Payload
operational modes– Supports store and forward function– Provides T&C interfaces to CEs
through SpaceWire• Channel Coding and Output
Buffer (CCOB) (2)– Multi-rate gigabit non-blocking,
crossbar switch to internal/external functional elements (DPSU, CCOB and Integrated Modems)
– Performs Forward Error Correction (FEC) decode/encode based on Integrated Modem operational mode
– Provides translation of frame format and data link buffering to switch
– Performs channel data interleave/de-interleave function
DPSU
CCOB 1CCOB
2
Integrated Modem 1
Integrated Modem 2
HSE
CE1 CE2SpW1
SpW2SpW2
SpW1
Common Avionics- Page 337/25/2012
Actel FPGARTAX4000SCCGA1272
Exp
an
sio
n C
on
nec
tor
AE
xpa
nsi
on
Co
nn
ecto
r B
RelayFET
RelayFET
Card’s Front2Tbits of user space
SerDes
Sa
brite
c
Spa
ceA
GE
Bus
Card’s Back
PH
YP
HY
Sa
mte
c
Sp
Wx2
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
MW
DM
-51
P
Debug C
onn.
Buffers
Sa
mtec
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
64G
bF
lash
5V
/15
W D
C/D
C
1.5VPOL
3.3VPOL
2.5VULDO
SerDes
Sa
mtec M
WD
M-9S
MW
DM
-9S
Sa
brite
c
Spa
ceA
GE
Bus
33u
F
75
V
Layout of Memory Module
Common Avionics- Page 367/25/2012
CommModule
SSRModule
External Analog
TlmModule
C&DH – Single String(LRO Mapping using LCRD elements)
SpaceWire
Legend
Embedded processor in FPGA
ExternalVehicle Control
Bus
HubModule
Mil-Std 1553b
Mil-Std 1553b
Low rate SpaceWire using Manchester encoding over intra-box interfaceGigabit SpaceWire 2 (SpaceFiber protocol) over intra-box interface
Instrument B I/F
Instrument A I/F
Instrument C I/F
UART I/F
Comm Module: 2 Digital boardsSSR Module: 1 Digital board & 1 Memory boardHub Module: 1 Digital board & 1 Analog boardExternal Analog Tlm Module: New design
Common Avionics- Page 377/25/2012
CommModule
SSRModule
External Analog
Tlm
C&DH – Redundant Processor(LRO Mapping using LCRD elements)
SpaceWire
Legend
Embedded Self Checking Pairs (SCP); One BC other Monitor on 1553
ExternalVehicle Control
Bus
HubModule
ExternalVehicle Control
Bus
HubModule
Mil-Std 1553b
Mil-Std 1553b; one Hub module BC, other Hub Module Monitor, switchable through backdoor control over SpaceWire
Low rate SpaceWire using Manchester encoding over intra-box interfaceGigabit SpaceWire 2 (SpaceFiber protocol) over intra-box interface
Instrument B I/F
Instrument A I/F
Instrument C I/F
UART I/F
Comm Module: 2 Digital boardsSSR Module: 1 Digital board & 1 Memory boardHub Module: 1 Digital board & 1 Analog boardExternal Analog Tlm Module: New design
Common Avionics- Page 407/25/2012
NodeModule
Node Module
Node Module
Node Module
Node Module
Node Module
Node Module
*EMIFilter
Power In
HubModule
Power - Single Voltage Distribution
Non-Digital Power and Return, Redundant Pair (LCRD implementation used primary power)
Power Switch
Legend
* Power conversion could also be done here (LCRD does not)
Common Avionics- Page 417/25/2012
NodeModule
Node Module
Node Module
Node Module
Node Module
Node Module
Node Module
*X-Bar SwitchExternal
Vehicle Control Bus
HubModule
Communications - Serial Full Duplex
2 uni-directional differential pairs, i.e., need to encode data & clock on same pair
Legend
Non-Blocking, protocol agnostic – multiple different protocols may be bridged via switch(LCRD uses SpaceWire 2 – new multi-Gigabit version of SpaceWire)
*
Common Avionics- Page 427/25/2012
NodeModule
Node Module
NodeModule
Node Module
Node Module
Node Module
Node Module
ExternalVehicle Control
Bus
HubModule
Processing
2 uni-directional differential pairs, used for communicating with Nodes
Legend
Processing, implementation not specified (could be embedded in FPGA)
Common Avionics- Page 437/25/2012
NodeModule
Node Module
Node Module
Node Module
Node Module
Node Module
Node Module
HUB InternalAnalog Tlm
HubModule
Analog Telemetry Gathering
1 Analog signal and ground pair
Legend
ADC OutIn
AnaMux
I0
I1
Sel
Out
Common Avionics- Page 447/25/2012
NodeModule
Node Module
Node Module
Node Module
Node Module
Node Module
Node Module
ClockGen
HubModule
Clock Distribution
Differential pair, Node defined, may be different between nodes.Multiple uses - could be 1 Hz pulse, etc.
Legend
Common Avionics- Page 457/25/2012
NodeModule
Node Module
Node Module
Node Module
Node Module
Node Module
Node Module
ResetGen
HubModule
Reset Distribution
Legend
Signal and Return (Return shared with “Sense” signal),Node defined electrical and protocol
Common Avionics- Page 467/25/2012
NodeModule
Node Module
Node Module
Node Module
Node Module
Node Module
Node Module
SenseDetect
HubModule
Node Presence “Sense”
Legend
Signal and Return (Return shared with “Sense” signal),Allows hot-plugability of Node
Common Avionics- Page 477/25/2012
NodeModule
Node Module
Node Module
Node Module
Node Module
Node Module
Node Module
ConverterSync
HubModule
Nodes “Converter Sync” Signal
Legend
Signal and Return same as Power Return,Used to reduce EMI by synchronizing switching converters on each Node
Common Avionics- Page 547/25/2012
Suggested HUB Architecture (Digital Section)
16MBSRAM
w/EDAC
+2.5V
+1.5V
+1.0V
Serial_Comm
Back sideNodeInterfaces(7 ports)
Reprogrammable NV Memory w/EDAC:
A) Xilinx Configuration,B) Xilinx CPU ROM,C) Scratchpad RAM
2 banks x 8MB
3.3V Converter Synchronization
SystemClock
POR
2 PortsSpWire
JTA
G 1
JTAG 2
Node Clock
Analog TLM and TLM Control
GSEConnector
Deb
ug S
etup
+3.3
DigitalGND
(Through Analog Card)
Xilinx Virtex-5FPGA
Node Power Control
Node Plug-in Sense
ExternalLVDS
HUB InternalVoltageTelemetry
FPGA Supervisor:Actel AX2000 or AX4000 with built-in IP cores for:
CPU, SpW, NVRAM programmer, etc.
2 HUBS
32b Local Bus
Functions:a) Full Duplex I/Fb) Clock Exchangec) Mutual Reset
Memory Bus
S/C Communications
2x16MBSRAM
w/EDAC
(Through Analog Card)
Node Reset Control
Peer Hub Communications
+1.8V
256MBSDRAMw/EDACBank 3
ExternalLVDS
Flexible DebugCommunications:
UART,10M Ethernet(Can be also used as S/C General PurposeCommunication ports)
2 Ports
LVDSClock
Configuration 8b Slave Bus
w/ CRC Check
(Through Analog Card)
Peer HUB and ID Sense
256MBSDRAMw/EDACBank 2
+1.2Van
+1.0Van
Bank 1: mainBank 2: auxiliary
(8bits+addr)
256MBSDRAMw/EDACBank 1
256MBSDRAMw/EDACBank 4
ExpansionPort A
32b
ExpansionPort B
32b
Inte
rfac
eP
orts
A&
B
+3.3 +3.3
MOSFET Switches
LocalDigital
DomainDC/DC
Converters< 20W
+5.0V
On-boardIsolated
28V PowerConverter
+28V
+28Vret
Selectable:MIL-STD-1553B, or
Dual RS-485 I/F
SerDes
Serial_Comm
SerDes
Front sideS/CInterfaces(4 ports)
1553
/RS
-485
Por
ts
Redundant X-over
Common Avionics- Page 567/25/2012
SpaceAGE Bus Signal AssignmentsGroup
Sub Group
Function PinNode Bus Connector
Flow Direction
Hub Bus Connector
Flow Direction
Redundant Hub Notes
1 TX+ ← RX+
2 RX+ → TX+
3 TX− ← RX−
4 RX− → TX−
1 Clock_in+ ← Clock_out+
2 Analog_out+ → Analog_in+
3 Clock_in− ← Clock_out−
4 Analog_out- → Analog_in-
1 Node Power ← Node Power
2 Node Power ← Node Power
3 Power Return → Power Return
4 Power Return → Power Return
1 Reset_in ← Reset_out
2 HUB GND ← HUB GND
3 Sense_out → Sense_in
4 Converter sync ← Converter sync
1 X_TX+ X_TX+
2 X_Clock_out+ X_Clock_out+
3 X_TX− X_TX−
4 X_Clock_out- X_Clock_out-
1 X_RX+ X_RX+
2 X_Clock_in+ X_Clock_in+
3 X_RX− X_RX−
4 X_Clock_in- X_Clock_in-
1 X_Reset_out+ X_Reset_out+
2 Peer_Hub out Peer_Hub out
3 X_Reset_out− X_Reset_out−
4 Config_out Config_out
1 X_Reset_in+ X_Reset_in+
2 Case GND Case GND
3 X_Reset_in− X_Reset_in−
4 Case GND Case GND
Reset, Node Sense and
DC/DC Sync
Hub
to
Hub
Cros
sove
r Bu
s
(4
inse
rts
for
an e
xtra
Hub
)
Digital
Reset and
Config
Hub
to
Nod
e Bu
s (2
8 in
sert
s ou
t of
32
for
7 N
odes
)
Digital
Serial Communication
Clock and Analog IF
Power and
Analog
Power Supply
Peer_Hub tells each Hub that its Peer Hub is in
Master Hub (A) - no jumper, Slave (B) - external jumper
X_Reset allows each Hub to reset its peer Hub either by
command, or by lack of communications for the
TBD time period
Cross Communication
Cross Clock
Cross Reset
Mster-Slave Configuration and Peer Hub
Plug-in
Full Duplex link. Diagonal pins 1-3 and 2-4 provide 100Ω impedance
Full Duplex cross link. Diagonal pins 1-3 and 2-4 provide 100Ω impedance
Allows both Hubs to share common clock
Up to 3A@18V of derated Node current;
DC/DC Sync is 200-800KHZ free running 5V clock;
Hub generated Power Fail
Optoisolated "Reset" from Hub and DC converter Sync; "Sense" tells Hub if Node is
plugged in and secured
Clock function is defined by Node end user
Node may have extra active analog telemetry, or 1
linear AD590 thermsitor;
Common Avionics- Page 577/25/2012
Example RIU - AL ECLSS Monitor
ECLSS
ATCS
C&DH
C&T
Power
GN&C
Mech
Prop
Structure
ATCS
Pow
er S
upp
ly
&C
ontr
olle
r
End
Cap
End
Cap
Functional Description:ECLSSHigh pressure O2 controlPLSS
Size:10" x 3.5” x 6.5" (L x W x H) L x W = mounting surface (includes 0.75” flange)W x H = connector face
E-A
-C
H18
D4H
32D
A
Con RPC 1 FET 2 FET3
FET Analog Inputs Digital InputsPowerWiring C&DH Wiring 22 AWG
Name Type
Relay
RPCSw
ServH RD VD SMD NSI VS T P dP L Fl O2 Q Pl
Network
Serial
RPM
Power
ServicesAWG
??
Power
ServicesAWG 16 TP
Power
ServicesAWG 20 TP
AWG 22 TSP
AWG 26 TSP
AWG 26 TST
Harness Mass (22 wires @
10ft)
Mass(Kg)
Power(W)
TOTALS 7 7 3 3 1 1 2 7 15 1.5 kg 3.13 7.03Controller & PS HUB-6U 1 1 1 1.07 4.80ECLSS E-6U-CH18D4H32DA 7 7 3 3 1 1 7 14 1.07 2.23Internal Harness 0.45 End Caps (2 ea) 0.54
Common Avionics- Page 587/25/2012
23
4 1
U
L
1U 2U 3U 4U4/1U 1/2U 2/3U 3/4U
1L 2L 3L 4L4/1L 1/2L 2/3L 3/4L
LO2 Tank
Radiator
LH2 Tank
Porch Light
LO2 Tank
Radiator
Antenna, Whip, EVA
LH2 Tank
NTO Tank
MMH Drain Tank
LO2 Tank
Radiator
LH2 Tank
MMH Tank
LO2 Tank
Radiator
LH2 Tank
Power Distribution Unit
Fuel Cell Ancillaries
He Tank (LO2 Press.)
Terrain Hazard Detection
Electronics, Radar, Sec.
Remote Multiplexer Unit
Bus Repeaters (2)
He Tank (LH2 Press.)
Inter-loop Heat Exchanger
Fuel Cell Hydrogen Tank
Fuel Cell Stacks (2)
Pump & Accumulator
H2O Tank, Thermal
Electronics, Radar, Pri.
Radar Antenna
Survival Heater
TurboPump Assembly
Main Engine
C&T Radio
RCS Valves
Regulator Pkg, Pneumatic Ctrl.
DME Controller
Landing Gear Mechanisms*
Landing Gear Mechanisms*
Landing Gear Mechanisms*
Landing Gear Mechanisms*
*Assumed location – Pyros not found on CAD model.
Propulsion
ECLSS
C&T
Electrical Power
GN&C
C&DH
Active Thermal Control
Mechanisms
Unknown/Undetermined
DM Functions per Quadrant
Common Avionics- Page 597/25/2012
1
23
4
1 2 3 41/2
Main Airlock Hatch
High-Pressure O2 System
3/44/1
High-Pressure O2 Accumulator
2/3
Airlock Hatch/Tunnel
Unpressurized Airlock
PDU
Crew Interface Micro./Speaker
Suit Service Unit Repeater
RMUX
EVA Battery Charger
Life Support System, Pri. (4)
Controls Module, EVA (4)
Whip Antenna, EVA Checkout
Pressurized AM
RMUX *
*Assumption based on location of an RMUX coldplate
Propulsion
ECLSS
C&T
Electrical Power
GN&C
C&DH
Active Thermal Control
Mechanisms
Unknown/Undetermined
AL Functions per Quadrant
Common Avionics- Page 607/25/2012
DM Propulsion FunctionsBay 1U
Bay 1L
Bay 2U
Bay 2L
LH2Tank
LQP
LO2Tank
LQP
Bay 3L
VDVS LH2
Valves
VDVS
VDVS(2)
VDVS LO2
Valves
VDVS
VDVS(2)
TΔP
TΔP
2/3
Bay 4L
Bay 2U/3U RCS
VD(4)VS(2) He
Pressurization
T(3)P(4)
H(2)T(2)*
NTOTank
MMHTank
T(2)*T(2)*H(2) H(2)
Q Q
MMH Tank
P
P
T(2)
He Tank
T TH(2)* H(2)*
P P
He Valves
VD(2)VS(2)
VD(2)VS(2)
T(2)*T(2)*
LH2Tank
LQP
LO2Tank
LQP
VDVS LH2
Valves
VDVS
VDVS(2)
VDVS LO2
Valves
VDVS
VDVS(2)
TΔP
TΔP
4/1
LH2Tank
LQP
LO2Tank
LQP
VDVS LH2
Valves
VDVS
VDVS(2)
VDVS LO2
Valves
VDVS
VDVS(2)
TΔP
TΔP
1/2
LH2Tank
LQP
LO2Tank
LQP
VDVS LH2
Valves
VDVS
VDVS(2)
VDVS LO2
Valves
VDVS
VDVS(2)
TΔP
TΔP
3/4
VS(2)
P P
PT
VDVS LH2
Valves
VDVS
VDVS
VDVS
VS(2) LO2 Valves
P P
PT
VS(2)
P P
PT
VDVS
LH2Valves
VDVS
VDVS
VDVS
VS(2)LO2
Valves
P P
PT
1/2
4/1
VD(2)VS HeLO2
Vlvs
VD(2)VS
VD(2)VS
He Tank
T T
P P
H(2)* H(2)*
He Valves
VD(2)VS(2)
VD(2)VS(2)
T(2)*T(2)*
LH2Valves
LO2 Valves
HeLO2
Vlvs
LH2Valves
LO2 Valves
VS(2)P P
PT
VDVS
VDVS
VDVS
VDVS
VS(2)
P PPT
VD(2)VS
VD(2)VS
VD(2)VS
VS(2)P P
PT
VDVS
VDVS
VDVS
VDVS
VS(2)
P PPT
LH2 Valves
LO2 Valves
HeLO2
Vlvs
LH2 Valves
LO2 Valves
He Drain Valves
VS(9)
P(3)
P(4)T(4)
VD(8)VS(7)
VD(4)
P(3)
VD(8)VS(7)
LO2 Tank
LO2 Valves
He Tank
LH2 Tank
LH2 Valves
He Valves
LO2 Tank
LO2 Valves
LH2 Valves
LH2 Tank
LQPT
ΔP
VDVS
VDVS
VDVS(2)
LQPT
ΔP
VDVSVD
VS(2)
VDVS
VD(2)VS(2)
VD(2)VS(2)
T T
P P
H(2)* H(2)*T(2)*T(2)*
LQPT
ΔP
VDVS
VDVS
VDVS(2)
LQPT
ΔP
VDVSVD
VS(2)
VDVS
LO2 Tank
LO2 Valves
He Tank
He Valves
LH2 Tank
LH2 Valves
L(2)
LH2 Tank
LH2 Valves
LO2 Tank
LO2 Valves
H(2)T(3)
Q(2)ΔP(2)
H(2)T(3)
He Pressuriz
ation
MMH Tank
MMH Pyro Vlv
NTO Tank
NTO Pyro Vlv
MMH Valves
H(2)P(4)T(5)
VD(4)VS(2)
T(2)H(2)
Q
Q
T(2)H(2)
MMH Drain Tank
P
PT(2)
He Pressuriza
tion
MMH Tank
MMH Pyro Vlv
NTO Tank
NTO Pyro Vlv
MMH Valves
VS(2)H(6)T(11)
VD(4)
P(6)
MMH Drain Tank
VS(16)
P(2)
P(6)T(6)
VD(4)VS(4)
P(2)
VD(4)VS(4)
L(2)Q(2)ΔP(2)
LO2 Tank
LO2 Valves
He Tank
LH2 Tank
LH2 Valves
He Valves
LO2 Tank
LO2 ValvesLH2 Valves
LH2 Tank
LQPT
ΔP
VDVS
VDVS
VDVS(2)
LQPT
ΔP
VDVSVD
VS(2)
VDVS
VD(2)VS(2)
VD(2)VS(2)
T T
P P
H(2)* H(2)*T(2)*T(2)*
LQPT
ΔP
VDVS
VDVS
VDVS(2)
LQPT
ΔP
VDVSVD
VS(2)
VDVS
LO2 Tank
LO2 Valves
He Tank
He Valves
LH2 Tank
LH2 Valves
VD(2)VS(8)L(2)
LH2 Tank
LH2 Valves
LO2 Tank
LO2 Valves
H(2)T(3)
Q(2)P(5)T(5)
ΔP(2)
H(2)T(3)
VD(2)VS(8)L(2)Q(2)P(4)T(4)
ΔP(2)
VD(2)VS
MMHIso1 Vlv
VD(2)VS
A1
VD(2)P
T(4)*
MMH Iso2 Vlv
A2
A3
A4
VD(2)VS
NTOIso1 Vlv
VD(2)VS
NTO Iso2 Vlv
DM RCS Thruster Pod A
P(2) P(2)
T
H H
HH
H(2)
T* T*
T*T*
VD(2)P
T(4)*H(2)
VD(2)P
T(4)*H(2)
VD(2)P
T(4)*H(2)
VD(2)VS
MMHIso1 Vlv
VD(2)VS
C1
VD(2)P
T(4)*
MMH Iso2 Vlv
C2
VD(2)VS
NTOIso1 Vlv
VD(2)VS
NTO Iso2 Vlv
DM RCS Thruster Pod C
P(2) P(2)
T
H H
HH
H(2)
T* T*
T*T*
VD(2)P
T(4)*H(2)
VD(2)P
T(4)*H(2)
VD(2)P
T(4)*H(2)
VD(2)VS
MMHIso1 Vlv
VD(2)VS
B1
VD(2)P
T(4)*
MMH Iso2 Vlv
B2
B3
B4
VD(2)VS
NTOIso1 Vlv
VD(2)VS
NTO Iso2 Vlv
DM RCS Thruster Pod B
P(2) P(2)
T
H H
HH
H(2)
T* T*
T*T*
VD(2)P
T(4)*H(2)
VD(2)P
T(4)*H(2)
VD(2)P
T(4)*H(2)
VD(2)VS
MMHIso1 Vlv
VD(2)VS
D1
VD(2)P
T(4)*
MMH Iso2 Vlv
D2
VD(2)VS
NTOIso1 Vlv
VD(2)VS
NTO Iso2 Vlv
DM RCS Thruster Pod D
P(2) P(2)
T
H H
HH
H(2)
T* T*
T*T*
VD(2)P
T(4)*H(2)
VD(2)P
T(4)*H(2)
VD(2)P
T(4)*H(2)
2U
1U
4U
3U
Thruster Valves
Thrusters
VS(4)P(4)H(4)T(5)*
Thruster Valves
Thrusters
VD(8)
P(4)H(8)
T(16)*
VD(8)
VS(4)P(8)
H(12)T(21)
VD(16)
Thruster Valves
Thrusters
VS(4)P(4)H(4)T(5)*
Thruster Valves
Thrusters
VD(8)
P(4)H(8)
T(16)*
VD(8)
VS(4)P(8)
H(12)T(21)
VD(16)
Thruster Valves
Thrusters
VS(4)P(4)H(4)T(5)*
Thruster Valves
Thrusters
VD(8)
P(4)H(8)
T(16)*
VD(8)
VS(4)P(8)
H(12)T(21)
VD(16)
Thruster Valves
Thrusters
VS(4)P(4)H(4)T(5)*
Thruster Valves
Thrusters
VD(8)
P(4)H(8)
T(16)*
VD(8)
VS(4)P(8)
H(12)T(21)
VD(16)
DM Descent Main Engine
Pne LH2Prestart
Vlvs
VDVS(4)
P
Pne LO2Prestart
Vlvs
VDVS(4)
P
HeCooldwn
Vlv
VDVS(2)
P
LO2Cnt Vlv
SMDPI
LO2Pump
RPM
PT
DMEP
HeStart Vlv
VDVS(2)
P
LH2Pump
RPMT
Pne LH2DscRlfBld
VlvVS(2)
LH2Cvt Vlv
SMDPI
P(2)
Pne LH2IntCldBld
VlvVS(2)
P(3)
Pne LH2MnSht
VlvVS(2)
LH2 Pump
Byp Vlv
SMDPI
LH2 ThrCnt
Vlv
SMDPI
T
L
Could not find separate valves/pumps. Assume
this is all part of the “turbo pump” assembly in bottom
center
He Pressuriza
tion
MMH Tank
MMH Pyro Vlv
NTO Tank
NTO Pyro Vlv
MMH Valves
VS(18)PI(4)T(3)
P(11)
MMH Drain Tank
SMD(4)
VD(4)
RPM(2)
LH2 Vent Vlvs
LO2Vent Vlvs
VD(3)VS(2)
VD(3)VS(2)
Vent Valves
VD(6)VS(4)
VD(8)
Vent Valves
LH2 PneFill Vlv
LO2 PneFill Vlv
VS(2) VS(2)
TP
TP
Pne Fill Valves
VS(4)T(2)P(2)
Bay 3U
VS(2)
P P
PT
VDVS LH2
Valves
VDVS
VDVS
VDVS
VS(2)LO2
Valves
P P
PT 2/3
VDVS Pneumatic
Regulator
VDVS
P P
PT
VD(2)VS HeLH2
Valves
VD(2)VS
LH2Valves
LO2 Valves
Pneumatic Regulator
HeLH2
Valves
VS(2)P P
PT
VDVS
VDVS
VDVS
VDVS
VS(2)
P PPT
VDVS
VDVS
PT
P P
VD(2)VS
VD(2)VS
LH2 Valves
LO2 Valves
Pneumatic Regulator
HeLH2
Valves
P(4)
VD(9)VS(8)
P(4)
VD(9)VS(8)
Bay 4U
VS(2)
P P
PT
VDVS LH2
Valves
VDVS
VDVS
VDVS
VS(2) LO2 Valves
P P
PT
3/4
LH2Valves
LO2 Valves
VS(2)P P
PT
VDVS
VDVS
VDVS
VDVS
VS(2)
P PPT
LH2 Valves
LO2 Valves
P(2)
VD(4)VS(4)
P(2)
VD(4)VS(4)
Bay 1
Bay 2
Bay 3
Bay 4
RCS
Common Avionics- Page 617/25/2012
DM Propulsion Bay 3 Upper/Lower
LH2Tank
LQP
LO2Tank
LQP
Bay 3L
VDVS LH2
Valves
VDVS
VDVS(2)
VDVS LO2
Valves
VDVS
VDVS(2)
TΔP
TΔP
2/3
He Tank
T TH(2)* H(2)*
P P
He Valves
VD(2)VS(2)
VD(2)VS(2)
T(2)*T(2)*
LO2 Tank
LO2 Valves
He Tank
He Valves
LH2 Valves
LH2 Tank
LQPT
ΔP
VDVS
VDVS
VDVS(2)
LQPT
ΔP
VDVSVD
VS(2)
VDVS
VD(2)VS(2)
VD(2)VS(2)
T T
P P
H(2)* H(2)*T(2)*T(2)*
LO2 Tank
LO2 Valves
He Tank
He Valves
VD(2)VS(8)L(2)
LH2 Tank
LH2 Valves
H(2)T(3)
Q(2)P(5)T(5)
ΔP(2)
H(2)T(3)
Bay 3U
VS(2)
P P
PT
VDVS LH2
Valves
VDVS
VDVS
VDVS
VS(2)LO2
Valves
P P
PT 2/3
VDVS Pneumatic
Regulator
VDVS
P P
PT
VD(2)VS HeLH2
Valves
VD(2)VS
LH2Valves
LO2 Valves
Pneumatic Regulator
HeLH2
Valves
VS(2)P P
PT
VDVS
VDVS
VDVS
VDVS
VS(2)
P PPT
VDVS
VDVS
PT
P P
VD(2)VS
VD(2)VS
LH2 Valves
LO2 Valves
Pneumatic Regulator
HeLH2
Valves
P(4)
VD(9)VS(8)
P(4)
VD(9)VS(8)
Bay 3
Recommended