NASA ANASA ALTAIRLTAIR Lunar Lander Project Lunar Lander Project
Avionics System Architecture StudyAvionics System Architecture Study
Minimum Functional ArchitectureMinimum Functional Architecture(Subsystems & Components)(Subsystems & Components)
09 April 200809 April 2008
ALTAIR Avionics System Definition
Generic Avionics System Definition:
The integrated group of all Lunar Lander Vehicle flight electrical, electronic, and electro-mechanical components,
flight wiring harnesses connected to those components, and flight software loaded into those components.
Generic Avionics System Definition:
The integrated group of all Lunar Lander Vehicle flight electrical, electronic, and electro-mechanical components,
flight wiring harnesses connected to those components, and flight software loaded into those components.
Major Avionics Subsystems:
• Command & Data Handling (C&DH)
• Communications & Tracking (C&T)
• Electrical Power Avionics
• Guidance Nav & Control (GN&C) Avionics
• Crew I/F, Controls, Displays & A/V
• Flight Software (FSW)
Major Avionics Subsystems:
• Command & Data Handling (C&DH)
• Communications & Tracking (C&T)
• Electrical Power Avionics
• Guidance Nav & Control (GN&C) Avionics
• Crew I/F, Controls, Displays & A/V
• Flight Software (FSW)
Minor Avionics Subsystems:
• Thermal Control & Monitoring Avionics
• Mechanism Control & Monitoring
• Reaction Control System Avionics
• Cryogenic Control & Monitoring Avionics
• Thrust Vector Control & Monitoring Avionics
• Descent Main Engine Control & Monitoring
• Ascent Main Engine Control & Monitoring
• Life Support System Control & Monitoring
Minor Avionics Subsystems:
• Thermal Control & Monitoring Avionics
• Mechanism Control & Monitoring
• Reaction Control System Avionics
• Cryogenic Control & Monitoring Avionics
• Thrust Vector Control & Monitoring Avionics
• Descent Main Engine Control & Monitoring
• Ascent Main Engine Control & Monitoring
• Life Support System Control & Monitoring
Level #
LevelTitle
Level DescriptionThis
Package
1VehicleLevel
• Vehicle Functions and Performance Levels Defined.• Vehicle Treated as “Black-Box”. No Internal Implementation biases.• Interfaces to other Major Exploration System Elements Defined.
2Stages
& ModulesLevel
• Module Functions and Performance Levels Defined.• Modules Treated as “Black-Boxes”. No Internal Implementation biases.• Inter-Module Interfaces Defined.• Stage Separation Interfaces Defined.
3Subsystems
& Components Level
• Components include Electronic Boxes, Antennas, Sensors, etc.• Component Functions and Performance Levels Defined.• Components Treated as “Black-Boxes”. No Internal Implementation biases.• Component Interfaces Defined: Power, C&T, Data, etc.• Power Distribution, Data Networks, and Packaging Approaches Defined.
4-HWHardware
Sub-Assemblies Level
• Hardware Sub-Assemblies include Cards, Backplanes, Chasses, etc.• Sub-Assembly Functions and Performance Levels Defined.• Cards Treated as “Black-Boxes”, but assumed part technologies defined.• Card Interfaces Defined: Box-External and Box-Internal.• Box-Internal Power Distribution, Data Networks, and Packaging Defined.
4-SWSoftware
Level
• Flight Software Architecture Topology Showing Distributed Elements• Flight Software Communication Architecture w/ OSI Reference Model Layers• Flight Software Layered Architecture Models • Potential Implementations of Op Systems, I/O Drivers, Application Tasks, etc
Design Package Partitioning and Scope
Avionics SystemAvionics SystemLevels 1&2 Design DrawingLevels 1&2 Design Drawing
&&Component DescriptionComponent Description
Level 1 – Vehicle Interface Block Diagram
Interface Color-Coding
By Type
ALTAIR Lunar Lander Project Avionics System
Level 1: Vehicle Interface Diagram Pre-Launch1
LEO Loiter3
Lunar Orbit Insertion8
Lunar Orbit Loiter9
Lunar Descent & Landing10
Lunar Surface Operations11
Lunar Ascent12
Lunar CEV Rendezvous & Docking13
Lunar Ascent Stage Disposal14
Trans-Lunar Coast7
Trans-Lunar Injection Maneuver6
Post CEV-Docking Operations5
LEO CEV Rendezvous & Docking
Launch into LEO
Mission Phases
4
2
#Pre-Launch1
LEO Loiter3
Lunar Orbit Insertion8
Lunar Orbit Loiter9
Lunar Descent & Landing10
Lunar Surface Operations11
Lunar Ascent12
Lunar CEV Rendezvous & Docking13
Lunar Ascent Stage Disposal14
Trans-Lunar Coast7
Trans-Lunar Injection Maneuver6
Post CEV-Docking Operations5
LEO CEV Rendezvous & Docking
Launch into LEO
Mission Phases
4
2
#
Design Reference Missions Design Reference Missions ((DRMsDRMs))
Single Lander design configurable as 3 different variants to support the 3 DRMs.
Common Descent Module for all DRMs
Common ‘minimized’ Ascent Module (AM) for Sortie and Outpost DRMs
Utilized for surface missions up to seven days where crew will use ascent stage as living quarters and a base of operations for EVAs.
Employs all major elements -- descent module, ascent module, airlock.
LunarLunarSortie Sortie CrewCrew
Utilized for surface missions up to seven days where crew will use ascent stage as living quarters and a base of operations for EVAs.
Employs all major elements -- descent module, ascent module, airlock.
LunarLunarSortie Sortie CrewCrew
Utilized for surface missions up to 210 days where crew will work out of the Outpost.
Configured similar to sortie variant, but without airlock; crew will depressurize ascent module upon landing and head directly for outpost.
Keep-alive power assumed to be provided by outpost.
LunarLunarOutpost Outpost
CrewCrew
Utilized for surface missions up to 210 days where crew will work out of the Outpost.
Configured similar to sortie variant, but without airlock; crew will depressurize ascent module upon landing and head directly for outpost.
Keep-alive power assumed to be provided by outpost.
LunarLunarOutpost Outpost
CrewCrew
Utilized to deliver large elements to the Outpost.
No ascent stage or crew; cargo will sit on upper deck of descent stage.
“Kits” for vehicle components normally resident in ascent stage.
LunarLunarCargoCargo
Utilized to deliver large elements to the Outpost.
No ascent stage or crew; cargo will sit on upper deck of descent stage.
“Kits” for vehicle components normally resident in ascent stage.
LunarLunarCargoCargo
Communications & Tracking Network
(CTN)
Earth Departure Stage(EDS)
OrionCrew Exploration Vehicle
(CEV)
Lunar Surface Systems
(LSS)
Lunar Lander Vehicle
RevisionDate:
02-22-2008
PowerAll DRMs: Phase 1
Hard-LineAll DRMs: Phase 1
PowerDRMs: Phases:
Sortie: 5-9, 13Outpost: 5-9, 13Cargo: na
Hard-LineDRMs: Phases:
Sortie: 5-9, 13Outpost: 5-9, 13Cargo: na
PowerDRMs: Phases:
Sortie: 1-6Outpost: 1-6Cargo: 1-3, 6
Hard-LineDRMs: Phases:
Sortie: 1-6Outpost: 1-6Cargo: 1-3,6
PowerDRMs: Phases:
Sortie:Outpost: 11Cargo: 11?
RF (S)DRMs: Phases:
Sortie: 11Outpost: 11Cargo: 11
RF (S)DRMs: Phases:
Sortie: 4, 9-14Outpost: 4, 9-14Cargo: na
Ares V Launch Tower
RF Interfaces
Power Lines
C3I Hard-Lines
RF (S)DRMs: Phases:
Sortie: 1, 3-5, 9-14Outpost: 1, 3-5, 9-14Cargo: 1, 3, 6, 7, 9-11
Phase 8 Note:LOI Manuever is obscured by the moon
Note:
The Diagram Below Defines 42 Separate Vehicle Interface
Configurations:
3 DRMs x 14 Phases(Data, Control, Monitor, Timing)
Level 2 – Consolidated Module Block Diagram
Outpost Payload DRMs: Phases:
Outpost: 1-11
Cargo PayloadDRMs: Phases:
Cargo: 1-3, 6-11
Power
Air-Lock Module
DRMs: Phases:
Sortie: 1-11
Hard-Line
Hard-Line
Power
StageColor-Coding
By Type
Lunar Lander
Ascent Stage
Lunar Lander
Ascent Stage (Crew Sortie & Outpost DRMs)
PowerDRMs: Phases:
Sortie: 5-9, 13Outpost: 5-9, 13Cargo: N/A
Hard-LineDRMs: Phases:
Sortie: 5-9, 13Outpost: 5-9, 13Cargo: N/A
PowerDRMs: Phases:
Sortie: 1-6Outpost: 1-6Cargo: 1-6
Hard-LineDRMs: Phases:
Sortie: 1-6Outpost: 1-6Cargo: 1-6
RF (S)DRMs: Phases:
Sortie: 4, 9, 10-14Outpost: 4, 9, 10-14Cargo: 8-11
Communications & Tracking Network (CTN)
Earth Departure Stage (EDS)
Lunar SurfaceSystems (LSS)
RF (S)DRMs: Phases:
Sortie: 11Outpost: 11Cargo: 11
Ares V LaunchTower
Lunar Surface Systems (LSS)
Comm & Tracking Network (CTN) Orion Crew Exploration Vehicle (CEV)
RF (S)DRMs: Phases:
Sortie: 3-7, 9-11Outpost: 3-7, 9-11Cargo: 3, 6, 7, 9-11
RF (S)DRMs: Phases:
Sortie: 3-7, 9-14Outpost: 3-7, 9-14Cargo: 3, 6, 7, 9-11
ALTAIR Lunar Lander Project Avionics System
Level 2: Stage & Module Diagram
PowerAll DRMs: Phase 1
Hard-LineAll DRMs: Phase 1
RF (S)DRMs: Phases:
Sortie: 11Outpost: 11Cargo: 11
PowerDRMs: Phases:
Sortie:Outpost: 11Cargo: 11
Common Services Assembly (CSA)
DRMs: Phases:
Sortie: 1-14
Outpost: 1-14
Cargo: 1-3, 6-11
Power
DescentModule
DRMs: Phases:
Sortie: 1-11
Outpost: 1-11
Cargo: 1-3, 6-11
AscentModule
DRMs: Phases:
Sortie: 1-14
Outpost: 1-14
Cargo DRM Connections
Crew DRM Connections
Interface Color-Coding
By Type
RevisionDate:
03-07-2008(Data, Control, Monitor, Timing)
RF Interfaces
Power Lines
C3I Hard-Lines
ConsolidatedDRM Diagram(All 3 DRMs)
Sortie Payload DRMs: Phases:
Sortie: 1-11
C3I Wireless
Level-2 Avionics ArchitectureKey Item
Creation of the Common Services Assembly (CSA): All of the Common Avionics Functions that are required for all 3 Design
Reference Missions (DRMs) were identified and grouped together in a new Level-2 Configuration Item called the “Common Services Assembly” (CSA).
Rationale/Benefits: Centralization/Consolidation of Common Items: The CSAs eliminate any DRM-Unique
implementations of common functions, and any unnecessary duplication of functions/implementations in different modules within a particular DRM, thereby minimizing the avionics system size, mass, power, and cost.
Economies of Scale: The CSAs can be “mass-produced” for use in every mission (9), regardless of the particular DRM, resulting in major cost savings, significant schedule reduction, common verification & test, and operational simplification. Even greater benefits can be achieved if the CSA is also used for other Lunar Surface Systems.
CSA Top-Level Physical Packaging Configuration:
Each DRM Type may have a unique CSA top-level packaging configuration and harness, however, their CSA Hardware Components will be identical.
The CSAs may have to be split into separate physical entities, such as a CSA Electronic Box Bay and a CSA Sensor/Antenna Ring.
Creation of the Common Services Assembly (CSA): All of the Common Avionics Functions that are required for all 3 Design
Reference Missions (DRMs) were identified and grouped together in a new Level-2 Configuration Item called the “Common Services Assembly” (CSA).
Rationale/Benefits: Centralization/Consolidation of Common Items: The CSAs eliminate any DRM-Unique
implementations of common functions, and any unnecessary duplication of functions/implementations in different modules within a particular DRM, thereby minimizing the avionics system size, mass, power, and cost.
Economies of Scale: The CSAs can be “mass-produced” for use in every mission (9), regardless of the particular DRM, resulting in major cost savings, significant schedule reduction, common verification & test, and operational simplification. Even greater benefits can be achieved if the CSA is also used for other Lunar Surface Systems.
CSA Top-Level Physical Packaging Configuration:
Each DRM Type may have a unique CSA top-level packaging configuration and harness, however, their CSA Hardware Components will be identical.
The CSAs may have to be split into separate physical entities, such as a CSA Electronic Box Bay and a CSA Sensor/Antenna Ring.
+X
+Y
+Z
+Y
6.22 m1 1
3
2,4 2,4
3
Sortie Cargo Size Unknown
Airlock
4 4
4
33
4
Orion “K
eep Out” z
one
33
2,4
Position Pros Cons
1• Easily integrated into all 3 DRM’s• Ring Concept
• Engine radiative heating problems• Potential interference with AM adapter during separation
2• Still ring concept, that is integratable into all 3 DRM’s
• Visibility out of top windows• Orion “keep out” zone
3 • Not much interference with other systems• Additional truss structure for mounting• Potential cabling issues
4• Only available uncluttered real estate left
that is close to AM press. vessel• May encroach on sortie cargo space
Ascent Module CSA AvionicsPlatform Placement Options
Level 3Level 3Avionics System Data Processing Avionics System Data Processing and Data Architecture Descriptionand Data Architecture Description
Avionics – Data Processing & Data Architecture Description
• Driven by requirement of minimum mass and power and high reliability of maintaining vehicle control and crew safety
• Composed of two Architectural Elements optimized to perform:
Vehicle Flight Control– Centralized General Purpose Processor – Distributed vehicle control effectors and sensors– Crew Controls and Displays– Interconnected by “low speed” highly deterministic data network Communications and Data Management– RF Communications units– Video imaging and processing units– Data Routers– Interconnected by “high speed” data network and C3I protocols
• Driven by requirement of minimum mass and power and high reliability of maintaining vehicle control and crew safety
• Composed of two Architectural Elements optimized to perform:
Vehicle Flight Control– Centralized General Purpose Processor – Distributed vehicle control effectors and sensors– Crew Controls and Displays– Interconnected by “low speed” highly deterministic data network Communications and Data Management– RF Communications units– Video imaging and processing units– Data Routers– Interconnected by “high speed” data network and C3I protocols
Vehicle Control Element -Central Processing
• Central Processor Performs– Vehicle level closed loop control processing – Vehicle monitoring & configuration mgmt processing– Redundancy management processing– User Display and Controls (C&D) processing (Flt Crew and Ground)– Subsystems processing suited for “general purpose processors”
• Central Processor Precepts and Attributes– “Low/Medium” performance general purpose processor– Focused on high reliability, low power “bullet proof” proven hardware– High performance special purpose processing needs are offloaded to sensors,
effectors, and special processors where necessary– Allows a low speed, highly reliable and low power vehicle control network solution
• Central Processor Performs– Vehicle level closed loop control processing – Vehicle monitoring & configuration mgmt processing– Redundancy management processing– User Display and Controls (C&D) processing (Flt Crew and Ground)– Subsystems processing suited for “general purpose processors”
• Central Processor Precepts and Attributes– “Low/Medium” performance general purpose processor– Focused on high reliability, low power “bullet proof” proven hardware– High performance special purpose processing needs are offloaded to sensors,
effectors, and special processors where necessary– Allows a low speed, highly reliable and low power vehicle control network solution
Vehicle Control Element -Sensor and Effectors
• Sensor and control effectors interface with central processor via two methods depending on complexity/functionality of the unit
“Electronic and processing intense” Units (“Type A”)– Units interface directly with the low speed - Vehicle Control Data Network (VCDN)
– Processing intense sensor and effector units also contain special purpose processors (SW and/or Firmware) for pre-processing and data formatting
– Offloads the central processor and reduces network traffic required
– Units consist of:– IMU - Descent Main Engine (DME) Controller– Star Tracker - S-Band SDR*, Router*, & CIU– Lidar* - D&C Controller*– Landing Radar - PDU– Hazard Detection Sensor* - RPC– Video Processor (VPU)* - Fuel Cell Electronics– EVA Servicing Unit and Battery Charger
*Note: Units also have port to High Rate Data Network (HRDN) for video and C&T data
• Sensor and control effectors interface with central processor via two methods depending on complexity/functionality of the unit
“Electronic and processing intense” Units (“Type A”)– Units interface directly with the low speed - Vehicle Control Data Network (VCDN)
– Processing intense sensor and effector units also contain special purpose processors (SW and/or Firmware) for pre-processing and data formatting
– Offloads the central processor and reduces network traffic required
– Units consist of:– IMU - Descent Main Engine (DME) Controller– Star Tracker - S-Band SDR*, Router*, & CIU– Lidar* - D&C Controller*– Landing Radar - PDU– Hazard Detection Sensor* - RPC– Video Processor (VPU)* - Fuel Cell Electronics– EVA Servicing Unit and Battery Charger
*Note: Units also have port to High Rate Data Network (HRDN) for video and C&T data
Vehicle Control Element -Sensors and Effectors (cont’d)
• “Small, Highly Distributed” Sensors and Effectors (Type “B”)
– “Type B” are of the category of distributed and remote temperature sensors, pressure sensors, position indicators, discrete commands of valve actuation, S&M deploy, and analog drive commands which are of standard type discrete and analogs.
– And, which do not naturally contain sufficient electronic sophistication to interface directly with the vehicle control data network (VCDN)
– “Type B” sensors and effectors interface with central processor via a general purpose data collector/distributor unit dubbed RMUX (remote multiplexer/de-multiplexer)
– Contains a general purpose microcontroller for local processing and control
– Atleast 1 in each module and can have significant commonality
– Provides central process interface for subsystems control and Monitoring:– TCS– Life Support– RCS Prop Storage– Cryo Prop Storage – Pyro Events Control (PEC)– Ascent Main Engine Control– RCS Engine Control– Mechanisms Control– Thrust Vector Control (TVC)
• “Small, Highly Distributed” Sensors and Effectors (Type “B”)
– “Type B” are of the category of distributed and remote temperature sensors, pressure sensors, position indicators, discrete commands of valve actuation, S&M deploy, and analog drive commands which are of standard type discrete and analogs.
– And, which do not naturally contain sufficient electronic sophistication to interface directly with the vehicle control data network (VCDN)
– “Type B” sensors and effectors interface with central processor via a general purpose data collector/distributor unit dubbed RMUX (remote multiplexer/de-multiplexer)
– Contains a general purpose microcontroller for local processing and control
– Atleast 1 in each module and can have significant commonality
– Provides central process interface for subsystems control and Monitoring:– TCS– Life Support– RCS Prop Storage– Cryo Prop Storage – Pyro Events Control (PEC)– Ascent Main Engine Control– RCS Engine Control– Mechanisms Control– Thrust Vector Control (TVC)
Crew and Ground UserCommand & Control (C&C) Interface
• Crew C&C Interface provided by Displays and Controls (D&C) Controller interfacing directly with the Vehicle Control Data Network (VCDN). Hardware consists of:
– D&C Controller – Provides local display formatting, display drive and D&C data routing with Central Processor. High Rate Data Network (HRDN) I/F for video data.
– Flat Screen text and graphic Displays with “Edge Panel Switches”
– Keyboards
– Vehicle Flight Control Hand Controls – With Rotational, Translational, and Throttle Control functionality
– Caution & Warning Indicators and control Panel
• CEV Flight Crew C&C provided by hard-line interface using D&C equivalent commands and display feedbacks to CEV (also used by preflight checkout users)
• CTN ground access users provided C&C interface via RF communications links using D&C equivalent commanding and/or special applications implement command codes.
• Crew C&C Interface provided by Displays and Controls (D&C) Controller interfacing directly with the Vehicle Control Data Network (VCDN). Hardware consists of:
– D&C Controller – Provides local display formatting, display drive and D&C data routing with Central Processor. High Rate Data Network (HRDN) I/F for video data.
– Flat Screen text and graphic Displays with “Edge Panel Switches”
– Keyboards
– Vehicle Flight Control Hand Controls – With Rotational, Translational, and Throttle Control functionality
– Caution & Warning Indicators and control Panel
• CEV Flight Crew C&C provided by hard-line interface using D&C equivalent commands and display feedbacks to CEV (also used by preflight checkout users)
• CTN ground access users provided C&C interface via RF communications links using D&C equivalent commanding and/or special applications implement command codes.
Communication and Data Management Element
• Communication and Data Management Element Provides function of:– RF Communications between Lander, CTN, CEV and Surface Sys– Data formatting and encoding– High Speed Data Routing– Video imaging and processing
• Hardware Consists of:– RF Communications units– Video Cameras (landing and Rndz/docking)– Interfaces with LIDAR and Hazard Detection Sensor for any video type image
data provided– Video processing units (VPU)– D&C “Flat screen” display interfaces for Video– Interconnected by “high rate” data network and C3I protocols
– C3I Data Routers– Interfaces to all external CxP Systems
– Provides communication security to Vehicle Control Data Network (VCDN) and Altair
– Interface to crew portable networked equipment
– Partitions critical function protocols
• Communication and Data Management Element Provides function of:– RF Communications between Lander, CTN, CEV and Surface Sys– Data formatting and encoding– High Speed Data Routing– Video imaging and processing
• Hardware Consists of:– RF Communications units– Video Cameras (landing and Rndz/docking)– Interfaces with LIDAR and Hazard Detection Sensor for any video type image
data provided– Video processing units (VPU)– D&C “Flat screen” display interfaces for Video– Interconnected by “high rate” data network and C3I protocols
– C3I Data Routers– Interfaces to all external CxP Systems
– Provides communication security to Vehicle Control Data Network (VCDN) and Altair
– Interface to crew portable networked equipment
– Partitions critical function protocols
Avionics SystemAvionics SystemLevel-3 Design DrawingLevel-3 Design Drawing
&&Data Network DescriptionData Network Description
Level 3 - Minimum Functional Block Diagram
Avionics Interface
Color-Coding
By Type
ALTAIR Lunar Lander Project Avionics System
Level 3: Subsys & Components Diagram
Lunar Surface Systems (LSS)
RF (S)
RevisionDate:
02-13-2008
Comm & Tracking Network (CTN)
Earth Departure Stage (EDS)
Lunar SurfaceSystems (LSS)
RF (S)RF (S)C3I Hard-LinePower Power
Comm & Track Network (CTN)
Orion Crew Exploration Vehicle (CEV)
RF (S) RF (S) C3I Hard-linePower
Common Services Assembly (CSA)
Cargo Payload
Ascent Module
Air-Lock Module
Hard-Line
Power
C&DH
Remote Mux Unit
· Thermal I/F· RCS (VDE)· AME· Life Support· Mech I/F· THC/RHC I/F
Crew I/F Power
Power Distribution
Unit
Batteries
C&T
Speaker / Mic
Crew I/F Unit
GN&C
LIDAR
C&DHFlight
Computer
Power
Remote Power
Controller
(RPC)
C&T
Antenna Electronics
SDR
GN&C
Inertial Measurement
Unit
(IMU)
S-Band Antenna
Remote Mux Unit· TCS· PEC· Mech Star Tracker
Docking Cam
C&DH
RemoteMux Unit
· Thermal I/F· Life Support
C&T
Speaker / Microphone
EVA RF Checkout Antenna
Crew I/F Displays & Controls
Suit / Backpack Servicing & Checkout
Power
Remote Power
Controller
(RPC)EVA Battery
Charger
Lunar Lander Ascent Stage (Crew DRMs)
Configuration Item
Color-Coding
By Type
Subsystems
VPU
Displays
D&C Elec
Hand Controls
EVA AntC&W
C3IWireless
Power(TBD)
Components
Ares V Launch Tower
(Data, Control, Monitor, Timing)
RF Interfaces
Power Lines
C3I Hard-Lines
Descent Module
C&DH GN&C
Landing Radar
Power
Fuel Cell Electronics
Power Distribution
Unit
C&TLanding Camera
Hazzard Detection Sensor
S / EVA Comm
Antennas & Elec
DME
Descent Main
Engine Controller
OutpostPayload
SortiePayload
Remote Mux Unit
· Thermal I/F Elec· PEC & Mech I/F Elec· RCS I/F & Drive Elec· Cryo I/F Elec· Thrust Vector Control
Hard-LinePower
Crew DRM Connections
Cargo DRM Connections
C3I Router
Data Network Diagram
C&T
Power C&DH
ALTAIR Lunar Lander Project Avionics System
Level 3: Data Network Diagram
RevisionDate:
04-08-2008
Remote Mux Unit
· Thermal I/F· RCS (VDE)· AME· Life Support· Mech I/F· THC/RHC I/F
Batteries
Remote Power
Controller
(RPC)
GN&C
Remote Mux Unit· TCS· PEC· Mech
RemoteMux Unit
· Thermal I/F· Life Support
Remote Power
Controller
(RPC)
Fuel Cells / Electronics
Power Dist Unit
Remote Mux Unit
· Thermal I/F Elec· PEC & Mech I/F Elec· RCS I/F & Drive Elec· Cryo I/F Elec· Thrust Vector Control
LSS
RF (S)
CTN
Crew I/F
Crew I/F Units
(6)
Speaker/Mic
EVA RF Checkout Antenna Suit / Backpack
Servicing & Checkout
EVA Battery Charger
Displays
Hand Controls
EVA Ant
C&W
C3IWireless
S / EVA Comm
Antennas & Elec
DME
Descent Main
Engine Controller
Payload
Flight Computer
Ant Elect
S-Band Ant
6
Software Defined Radio(SDR)
VPU
RF (S)
2
Display &
Control Elec(2)
CEV
C3IWireless
Vehicle Control Data Network (<10 Mbps)
VCDN
High-Rate Data Network (>100 Mbps) HRDN
Vehicle Control Data Network (<10 Mbps) VCDN
Ø Highly-Reliable Low/Medium Rate Data Network for all Critical Communication, Control, and Monitoring
Ø Deterministic Time-Synchronized Protocol
Ø ~300 kbps Throughput Requirement:· Housekeeping Data · Bi-Directional Digital Audio· 20% Packet Overhead
High-Rate Data Network (>100 Mbps) HRDN
Ø High-Rate Data Network for Supplemental Data Communication such as Video Signals, etc.
Ø Event-Driven Protocol
Ø ~300 Mbps Throughput Capability:· Supplemental Control & Monitoring· 2 Bi-Directional Uncompressed Digital Video with
640 x 480 pixel resolution & 30 frames/sec
RF Communications Network
Notes:
Ø The data network diagram above shows logical connections only. No Network Topology is implied (such as point-to-point, ring, etc.)
Ø Estimated Data Network Connections:o Primary Data Network: ~30o Auxiliary Data Network: ~ 12
Configuration Item
Color-Coding
By Type
Subsystems
Components
Analog RF point-to-point connections
Bridged to flight networks via C3I router
C3I Hard-Line Network
Direct Hard-Line interface to connected spacecraft
Features adaptable spacecraft bus for interface
Could be same bus as HRDN
C3IRouter
EDS
C3I Hard-Lines
CEV
Power Dist Unit
Inertial Measurement
Unit
(IMU)
Star Tracker
Landing Radar
Landing Camera
LIDARHazzard
Detection Sensor
Docking Cam
Avionics SystemAvionics SystemSubsystem SpecificSubsystem Specific
Design DriversDesign Drivers
Electrical Power Subsystem & Components
Accommodate All External Power Sources: Ares-V Launch Tower via Umbilical Cable and EDS Earth Departure Stage Crew Exploration Vehicle Lunar Outpost
Accommodate LLV Power Sys - Internal Power Generation B/L Approach: Fuel Cells & Assoc Electronics located in Descent Module
Accommodate LLV Power Sys - Internal Power Storage B/L Approach: Batteries located in Ascent Module
Power Switching & Distribution Simple Power Distribution Bus between Modules (sometimes bi-directional)
Each Module contains a Power Unit (RPC or PDU) with a Primary Power Bus Input, Power Distribution Outputs to all required components within that module, and a Vehicle Control Data Network (VCDN) I/F that controls the power switching/distribution within that module.
Support an EDS or insitu Flight Crew initiated startup with an “always-active” power source for "cold start" of Altair - Nominal mission and contingencies.
Power Component Modularity & Commonality RPC and PSDU components in different modules can have significant commonality Avionic Component Power Supply Cards may be able to use common designs.
Accommodate All External Power Sources: Ares-V Launch Tower via Umbilical Cable and EDS Earth Departure Stage Crew Exploration Vehicle Lunar Outpost
Accommodate LLV Power Sys - Internal Power Generation B/L Approach: Fuel Cells & Assoc Electronics located in Descent Module
Accommodate LLV Power Sys - Internal Power Storage B/L Approach: Batteries located in Ascent Module
Power Switching & Distribution Simple Power Distribution Bus between Modules (sometimes bi-directional)
Each Module contains a Power Unit (RPC or PDU) with a Primary Power Bus Input, Power Distribution Outputs to all required components within that module, and a Vehicle Control Data Network (VCDN) I/F that controls the power switching/distribution within that module.
Support an EDS or insitu Flight Crew initiated startup with an “always-active” power source for "cold start" of Altair - Nominal mission and contingencies.
Power Component Modularity & Commonality RPC and PSDU components in different modules can have significant commonality Avionic Component Power Supply Cards may be able to use common designs.
Communication & Tracking (C&T) Subsystem & Components
Software Defined Radio (SDR) and supporting antennas and electronics Configurable for S-Band, 802.xx, EVA Interfaces to both data networks (VCDN & HSDN) Encoding/decoding (LDPC,etc..) One radio needed for each concurrent link
Video Processing Unit (VPU) ALHAT,LIDAR, & GN&C (Landing\Docking) Video data processing Accepts raw or encoded streams Limited to 2 video streams in each mission phase Processes and distributes camera commands
CIU & Speaker Mic Provides voice communications for astronauts Located in Ascent Module and Air Lock
EVA Checkout Antenna Located in Air Lock for Sortie and Ascent Module for Crew Checkout for EVA
Software Defined Radio (SDR) and supporting antennas and electronics Configurable for S-Band, 802.xx, EVA Interfaces to both data networks (VCDN & HSDN) Encoding/decoding (LDPC,etc..) One radio needed for each concurrent link
Video Processing Unit (VPU) ALHAT,LIDAR, & GN&C (Landing\Docking) Video data processing Accepts raw or encoded streams Limited to 2 video streams in each mission phase Processes and distributes camera commands
CIU & Speaker Mic Provides voice communications for astronauts Located in Ascent Module and Air Lock
EVA Checkout Antenna Located in Air Lock for Sortie and Ascent Module for Crew Checkout for EVA
Guidance, Navigation, & Control (GN&C) Subsystem & Components
All GN&C sensors assumed to be Type A “SMART” boxes with direct interface to the Vehicle Control Data Network (VCDN).
Star Tracker – Inertial attitudes
Inertial Measurement Unit (IMU) – Rates and Acceleration
LIDAR• Provides range & relative orientation to support docking• Sensor is critical for auto docking
Landing Radar – Altitude and altitude rate, multiple beams
Hazard Detection Sensor
Currently not known exactly what functionality will be included Using as a placeholder to provide “HOOKS” for inclusion into design Interfaces directly to the Vehicle Control Data Network (VCDN) for processed data, and to the
High Rate Data Network (HRDN) for video processing Study includes looking at sharing of Altair resources such as cameras and IMU’s Where possible sharing of Altair resources such as cameras and IMU’s is recommended
All GN&C sensors assumed to be Type A “SMART” boxes with direct interface to the Vehicle Control Data Network (VCDN).
Star Tracker – Inertial attitudes
Inertial Measurement Unit (IMU) – Rates and Acceleration
LIDAR• Provides range & relative orientation to support docking• Sensor is critical for auto docking
Landing Radar – Altitude and altitude rate, multiple beams
Hazard Detection Sensor
Currently not known exactly what functionality will be included Using as a placeholder to provide “HOOKS” for inclusion into design Interfaces directly to the Vehicle Control Data Network (VCDN) for processed data, and to the
High Rate Data Network (HRDN) for video processing Study includes looking at sharing of Altair resources such as cameras and IMU’s Where possible sharing of Altair resources such as cameras and IMU’s is recommended
Propulsion Subsystem & Components
Descent Main Engine Controller (DME)
Controller performs critical function of safe pre-start, start, throttling, monitoring and shutdown of Descent Engine.
Requires critical time sequencing and monitoring performed at 50 HZ
• Based on meeting with Kendall Brown while at LaRC
High rates and precision sequencing requirement led to concluding a DME local Controller would be necessary.
Interfaces directly with Flight Computer over Vehicle Control Data Network (VCDN).
Closed-loop control of engine to be performed locally within DME Controller based on high level commands from Central Processor.
Descent Main Engine Controller (DME)
Controller performs critical function of safe pre-start, start, throttling, monitoring and shutdown of Descent Engine.
Requires critical time sequencing and monitoring performed at 50 HZ
• Based on meeting with Kendall Brown while at LaRC
High rates and precision sequencing requirement led to concluding a DME local Controller would be necessary.
Interfaces directly with Flight Computer over Vehicle Control Data Network (VCDN).
Closed-loop control of engine to be performed locally within DME Controller based on high level commands from Central Processor.
BackupBackup
Level 2 – Crew Sortie Block Diagram
Interface Color-Coding
By Type
RevisionDate:
03-07-2008
SortiePayloadModule
DRMs: Phases:
Cargo: 1-3, 6-11
Power
Air-Lock Module
DRMs: Phases:
Sortie: 1-11
Hard-Line
Power
StageColor-Coding
By Type
Lunar Lander
Ascent Stage
PowerDRMs: Phases:
Sortie: 5-9, 13Outpost: 5-9, 13Cargo: N/A
Hard-LineDRMs: Phases:
Sortie: 5-9, 13Outpost: 5-9, 13Cargo: N/A
PowerDRMs: Phases:
Sortie: 1-6Outpost: 1-6Cargo: 1-6
Hard-LineDRMs: Phases:
Sortie: 1-6Outpost: 1-6Cargo: 1-6
RF (S)DRMs: Phases:
Sortie: 4, 9, 10-14Outpost: 4, 9, 10-14Cargo: 8-11
Communications & Tracking Network (CTN)
Earth Departure Stage (EDS)
Lunar SurfaceSystems (LSS)
RF (S)DRMs: Phases:
Sortie: 11Outpost: 11Cargo: 11
Ares V LaunchTower
Lunar Surface Systems (LSS)
Comm & Tracking Network (CTN) Orion Crew Exploration Vehicle (CEV)
RF (S)DRMs: Phases:
Sortie: 3-7, 9-11Outpost: 3-7, 9-11Cargo: 3, 6, 7, 9-11
RF (S)DRMs: Phases:
Sortie: 3-7, 9-14Outpost: 3-7, 9-14Cargo: 3, 6, 7, 9-11
(Data, Control, Monitor, Timing)
ALTAIR Lunar Lander Project Avionics System
Level 2: Stage & Module Diagram
PowerAll DRMs: Phase 1
Hard-LineAll DRMs: Phase 1
RF (S)DRMs: Phases:
Sortie: 11Outpost: 11Cargo: 11
RF Interfaces
Power Lines
C3I Hard-Lines
Common Services Assembly (CSA)
DRMs: Phases:
Sortie: 1-14
Outpost: 1-14
Cargo: 1-3, 6-11
DescentModule
DRMs: Phases:
Sortie: 1-11
Outpost: 1-11
Cargo: 1-3, 6-11
Crew SortieDRM
Hard-Line
Ascent Stage (Crew Sortie & Outpost DRMs)
Power
AscentModule
DRMs: Phases:
Sortie: 1-14
Outpost: 1-14
C3IWireless
Lunar Lander (Crew Sortie DRM)
Level 2 – Crew Outpost Block Diagram
StageColor-Coding
By Type
Lunar Lander
Ascent Stage
PowerDRMs: Phases:
Sortie: 1-6Outpost: 1-6Cargo: 1-6
Hard-LineDRMs: Phases:
Sortie: 1-6Outpost: 1-6Cargo: 1-6
RF (S)DRMs: Phases:
Sortie: 4, 9, 10-14Outpost: 4, 9, 10-14Cargo: 8-11
Communications & Tracking Network (CTN)
Earth Departure Stage (EDS)
Lunar SurfaceSystems (LSS)
RF (S)DRMs: Phases:
Sortie: 11Outpost: 11Cargo: 11
Ares V LaunchTower
Lunar Surface Systems (LSS)
Comm & Tracking Network (CTN) Orion Crew Exploration Vehicle (CEV)
RF (S)DRMs: Phases:
Sortie: 3-7, 9-11Outpost: 3-7, 9-11Cargo: 3, 6, 7, 9-11
RF (S)DRMs: Phases:
Sortie: 3-7, 9-14Outpost: 3-7, 9-14Cargo: 3, 6, 7, 9-11
ALTAIR Lunar Lander Project Avionics System
Level 2: Stage & Module Diagram
PowerAll DRMs: Phase 1
Hard-LineAll DRMs: Phase 1
RF (S)DRMs: Phases:
Sortie: 11Outpost: 11Cargo: 11
PowerDRMs: Phases:
Sortie:Outpost: 11Cargo: 11
Common Services Assembly (CSA)
DRMs: Phases:
Sortie: 1-14
Outpost: 1-14
Cargo: 1-3, 6-11
DescentModule
DRMs: Phases:
Sortie: 1-11
Outpost: 1-11
Cargo: 1-3, 6-11
Interface Color-Coding
By Type
RevisionDate:
03-07-2008(Data, Control, Monitor, Timing)
RF Interfaces
Power Lines
C3I Hard-Lines
Crew OutpostDRM
OutpostPayloadModule
Power
C3IWireless
DRMs: Phases:
Outpost: 1-11
PowerDRMs: Phases:
Sortie: 5-9, 13Outpost: 5-9, 13Cargo: N/A
Hard-LineDRMs: Phases:
Sortie: 5-9, 13Outpost: 5-9, 13Cargo: N/A
Hard-Line
Ascent Stage (Crew Sortie & Outpost DRMs)
Power
AscentModule
DRMs: Phases:
Sortie: 1-14
Outpost: 1-14
Lunar Lander (Crew Outpost DRM)
Power Hard-Line
StageColor-Coding
By Type
Lunar Lander
Lunar Lander (Cargo DRM)
PowerDRMs: Phases:
Sortie: 1-6Outpost: 1-6Cargo: 1-6
Hard-LineDRMs: Phases:
Sortie: 1-6Outpost: 1-6Cargo: 1-6
Communications & Tracking Network (CTN)
Earth Departure Stage (EDS)
Lunar SurfaceSystems (LSS)
RF (S)DRMs: Phases:
Sortie: 11Outpost: 11Cargo: 11
Ares V LaunchTower
Lunar Surface Systems (LSS)
Comm & Tracking Network (CTN)
RF (S)DRMs: Phases:
Sortie: 3-7, 9-11Outpost: 3-7, 9-11Cargo: 3, 6, 7, 9-11
RF (S)DRMs: Phases:
Sortie: 3-7, 9-14Outpost: 3-7, 9-14Cargo: 3, 6, 7, 9-11
ALTAIR Lunar Lander Project Avionics System
Level 2: Stage & Module Diagram
PowerAll DRMs: Phase 1
Hard-LineAll DRMs: Phase 1
RF (S)DRMs: Phases:
Sortie: 11Outpost: 11Cargo: 11
PowerDRMs: Phases:
Sortie:Outpost: 11Cargo: 11
Common Services Assembly (CSA)
DRMs: Phases:
Sortie: 1-14
Outpost: 1-14
Cargo: 1-3, 6-11
DescentModule
DRMs: Phases:
Sortie: 1-11
Outpost: 1-11
Cargo: 1-3, 6-11
Interface Color-Coding
By Type
RevisionDate:
03-07-2008(Data, Control, Monitor, Timing)
RF Interfaces
Power Lines
C3I Hard-Lines
CargoDRM
CargoPayloadModule
Power
C3IWirelessDRMs: Phases:
Cargo: 1-3, 6-11
Level 2 – Cargo Block Diagram