Electrical - PowerPoint PPT Presentation

Loading...

PPT – Electrical PowerPoint presentation | free to download - id: 1d8cd1-ZDc1Z



Loading


The Adobe Flash plugin is needed to view this content

Get the plugin now

View by Category
About This Presentation
Title:

Electrical

Description:

Solar Array EICD (431-ICD-000150) Battery EICD (431-ICD-000151) Delta II PPG (MDC 00H0016) ... 1 pps, RS-422, Grounding, Isolation, Shielding, Charging ... – PowerPoint PPT presentation

Number of Views:48
Avg rating:3.0/5.0
Slides: 16
Provided by: nasagoddar
Learn more at: http://snebulos.mit.edu
Category:

less

Write a Comment
User Comments (0)
Transcript and Presenter's Notes

Title: Electrical


1
Electrical
  • Philip Luers
  • NASA/GSFC Code 561
  • August 16-17, 2005

2
Electrical Systems Document Tree
Mission Requirements Document (431-RQMT-000004)
Electrical Systems Specification (431-SPEC-000008)
Delta II PPG (MDC 00H0016)
CDH EICD (431-ICD-000141)
General Thermal Subsystem Specification (431-SPEC-
0000091)
PSE EICD (431-ICD-000142)
CRaTER EICD (431-ICD-000094)
PDE EICD (431-ICD-000143)
Star Tracker EICD (431-ICD-000144)
DLRE EICD (431-ICD-000095)
Power, 1553, SpaceWire, 1 pps, RS-422, Grounding,
Isolation, Shielding, Charging
Inertial Meas. Unit EICD (431-ICD-000145)
LAMP EICD (431-ICD-000096)
Communications EICD (431-ICD-000146)
LEND EICD (431-ICD-000097)
LOLA EICD (431-ICD-000098)
Propulsion EICD (431-ICD-000147)
LROC EICD (431-ICD-000099)
Reaction Wheels EICD (431-ICD-000148)
Heaters, Thermistors
Gimbal Controller EICD (431-ICD-000149)
Solar Array EICD (431-ICD-000150)
Battery EICD (431-ICD-000151)
Mini-RF EICD (431-ICD-000152)
LRO SpaceWire Spec. (431-SPEC-000103)
Electrical Systems Requirements
Document (431-RQMT-000140)
Specific Interfaces Connectors, pinouts
Specific Interfaces Connectors, pinouts
3
Lunar Reconnaissance Orbiter (LRO)Electrical
System Level 2 Flow Down KeyPower Requirements
Level 2 Req. Level 3 Requirements Concept/Compliance
Paragraph Requirement
MRD-32, MRD-101 ESR-1 The Electrical System (ES) shall distribute 28/-7 VDC power to subsystems. Shielded twisted pair for 45 services.
ESS-5 ESR-2 The ES shall provide the capability for redundant power and ground wires (more than required for each service). Easy implementation to protect against broken wires.
ESS-35 ESS-38, ESS-43 ESR-3 The ES shall implement a single point ground system, with appropriate primary power isolation Best practice for spacecraft primary power from NASA-HDBK-4001.
4
Lunar Reconnaissance Orbiter (LRO)Electrical
System Level 2 Flow Down KeyGrounding
Requirements
Level 2 Req. Level 3 Requirements Concept/Compliance
Paragraph Requirement
ESS-45, 47,48 ESR-4,5 The ES shall provide ground straps where necessary to ground all chassis and conductors. Best practice for charging avoidance per NASA-HDBK-4001
ESS-54, 63 ESR-6 Ground all harness shields. Best practice for controlling EMI/EMC.
ESS-55, 56, 57, 59, 60, 61, 156-159, 167-173, 177-186 ESR-7 The ES shall ground all external surfaces. Best practice for charging avoidance per NASA-HDBK-4001
ESS-188 ESS-193 ESR-8 The ES shall be designed to minimize internal charging. Best practice for charging avoidance per NASA-HDBK-4001
MRD-28, ESS-65 ESR-9 The ES shall be designed to minimize radiated emissions and radiated susceptibility to ensure Orbiter self-compatibility. Best practice for controlling EMI/EMC
5
Lunar Reconnaissance Orbiter (LRO)Electrical
System Level 2 Flow Down KeyData Requirements
Level 2 Req. Level 3 Requirements Concept/Compliance
Paragraph Requirement
MRD-36, ESS-102 ESR-10 The ES shall implement a SpaceWire network to support LROC and CDH High speed bus harness and pinouts per ESA SpaceWire specification (ECSS-E-50-12)
MRD-35, ESS-106, ESS-108 ESS-115 ESR-11 The ES shall implement a dual redundant MIL-STD-1553 to support CRaTER, DLRE, LOLA, LEND, CDH, IRW, IMU, ST, PSE, PDE, and Gimbal Controllers. To/from BC and RTs per Electrical Systems Specification (431-SPEC-000008)
ESS-122 ESS-126 ESR-12 The ES shall implement 5V discrete commands with appropriate shielding. Terminated per Electrical Systems Specification (431-SPEC-000008)
ESS-127 ESR-13 The ES shall implement 28V discrete commands with appropriate shielding. Per Electrical Systems Specification (431-SPEC-000008)
ESS-130 ESR-14 The ES shall implement 1 pulse-per-second to support CDH, CRaTER, DLRE, LOLA and LEND RS-422 with termination per Electrical Systems Specification (431-SPEC-000008)
6
Lunar Reconnaissance Orbiter (LRO)Electrical
System Level 2 Flow Down KeyThermal Requirements
Level 2 Req. Level 3 Requirements Concept/Compliance
Paragraph Requirement
MRD-080 ESR-14 The ES shall size wire based on heaters for a minimum bus voltage of 24 VDC Prevents over sizing of heaters at maximum bus voltage
MRD-078 ESR-15 The ES shall support all heater circuits (instrument survival, instrument operational, spacecraft survival heaters (primary redundant), spacecraft operational heaters, propulsion heaters (primary redundant), gimbal heaters (primary redundant), and deployable heaters. The ES shall support thermistors to verify temperatures. Maintain and monitor temperatures per Thermal System Specification (431-SPEC-000091)
7
Lunar Reconnaissance Orbiter (LRO)Electrical
System Level 2 Flow Down KeyMisc. Interface
Requirements
Level 2 Req. Level 3 Requirements Concept/Compliance
Paragraph Requirement
MRD-87, ESS-138 ESR-18 The ES shall provide multiple inhibits on all thrusters and isolation valves. Catastrophic hazard inhibits
MRD-87, ESS-139 ESR-19 The ES shall provide harness to support all pyrotechnic requirements, isolating actuation devices from external energy sources by greater than 20 dB. The ES shall protect electroexplosive devices from electrostatic hazards. Protection against unintentional firing of pyrotechnics
ESS-140-ESS-144, ESS-146-ESS-150 ESR-20 The ES shall provide harness and connectors to support component integration, anomaly investigation, environmental testing, and launch site operations. Spacecraft test panel
ESR-145 ESR-21 The ES shall provide 3 independent launch vehicle separation switches. Sensing separation from launch vehicle, also used as a catastrophic hazard inhibit
ESS-194 ESS-234 ESR-22 The ES shall use qualified spaceflight connectors, materials, design and manufacturing processes. Best practices for materials, design and fabrication of spaceflight harnesses per Design and Development Guidelines for Spaceflight Electrical Harnesses (565-PG-8700.2.1)
8
Lunar Reconnaissance Orbiter (LRO)Electrical
System Level 2 Flow Down KeyInstrument
Requirements
Level 2 Req. Level 3 Requirements Concept/Compliance
Paragraph Requirement
TRA 4.3, MRD-35, MRD-115 ESR-23 The ES shall support 1 switched 1 A service, MIL-STD-1553 and 1 pulse-per-second (pps) for CRaTER Per CRaTER to Spacecraft Electrical Interface Control Document (EICD) (431-ICD-000094)
TRA 4.3, MRD-35, MRD-115 ESR-24 The ES shall support 3 switched 2 A services (DLRE main, DLRE survival heaters, DLRE operational heaters), MIL-STD-1553 and 1pps for DLRE Per DLRE to Spacecraft EICD (431-ICD-000095)
TRA 4.3, MRD-117 ESR-25 The ES shall support 2 switched 2 A service, support heritage LAMP telemetry and command interface for LAMP Per LAMP to Spacecraft EICD (431-ICD-000096)
TRA 4.3, MRD-35, MRD-115 ESR-26 The ES shall support 1 switched 1 A service, MIL-STD-1553 and 1pps for LEND Per LEND to Spacecraft EICD (431-ICD-000097)
TRA 4.3, MRD-35, MRD-115 ESR-27 The ES shall support 1 switched 2 A service, MIL-STD-1553, 20 MHz, and 1pps for LOLA Per LOLA to Spacecraft EICD (431-ICD-000098)
TRA 4.3, MRD-36 ESR-28 The ES shall support 1 switched 2 A service, 1 switched 5 A service, and SpaceWire for LROC Per LROC to Spacecraft EICD (431-ICD-000099)
9
Lunar Reconnaissance Orbiter (LRO)Electrical
System Level 2 Flow Down KeySpacecraft
Requirements
Level 2 Req. Level 3 Requirements Concept/Compliance
Paragraph Requirement
TRA 4.1, TRA 4.3, MRD-35, MRD-36, 115, 119, 120, 122-124, 078, 117 ESR-29 The ES shall support 2 unswitched 2 A services, 1 switched 2 A service. Provide MIL-STD-1553, SpaceWire, 1 pps, 20 MHz, RF, thermistors, and LAMP heritage interfaces for CDH Per CDH to Spacecraft EICD (431-ICD-000141)
TRA 4.1, TRA 4.3, MRD-98, MRD-101- MRD-107 ESR-30 The ES shall support 9 unswitched services, 36 switched services, MIL-STD-1553, interface to battery and solar panels for Power System Electronics (PSE) Per PSE to Spacecraft EICD (431-ICD-000142)
TRA 4.3, MRD-85, 87 ESR-31 The ES shall support 1 switched 15 A service, MIL-STD-1553, propulsion valve actuator, and deployment interfaces for Propulsion Deployment Electronics (PDE) Per PDE to Spacecraft EICD (431-ICD-000143)
TRA 4.3, MRD-85 ESR-32 The ES shall support 2 switched 1 A services (2 Trackers), and MIL-STD-1553 for 2 Star Trackers Per Star Tracker to Spacecraft EICD (431-ICD-000144)
TRA 4.3, MRD-85 ESR-33 The ES shall support 1 switched 2 A services, and MIL-STD-1553 for Intertial Measurement Unit (IMU) Per IMU to Spacecraft EICD (431-ICD-000145)
TRA 4.1, TRA 4.3, MRD-119, 120, 122-124 ESR-34 The ES shall support 1 unswitched 2 A service (S-band RX), 1 switched 2 A service (S-band TX), 1 switched 10 A service (Ka-band TX), and RF interfaces (S-band RX, S-band TX, Ka-band TX) for Comm System Per Communications to Spacecraft EICD (431-ICD-000146)
10
Lunar Reconnaissance Orbiter (LRO)Electrical
System Level 2 Flow Down KeySpacecraft
Requirements
Level 2 Req. Level 3 Requirements Concept/Compliance
Paragraph Requirement
TRA 4.3, MRD-85 ESR-35 The ES shall support propulsion catalyst bed heater, pyrotechnic valve, isolation valve, thrusters, pressure and pressure transducers interfaces for Propulsion System Per Propulsion to Spacecraft EICD (431-ICD-000147)
TRA 4.1, MRD-85 ESR-36 The ES shall support 4 unswitched 2 A services (4 Integrated Reaction Wheels (IRWs)), MIL-STD-1553 for 4 Integrated Reaction Wheels Per IRW to Spacecraft EICD (431-ICD-000148)
TRA 4.3, MRD-15, MRD-16 ESR-37 The ES shall support 1 switched 2 A service, MIL-STD-1553 for Gimbal Control Electronics Per Gimbal Controller Electronics to Spacecraft EICD (431-ICD-000149)
MRD-98, MRD-101- MRD-107 ESR-38 The ES shall support solar array power and thermal sensors Per Solar Array to Spacecraft EICD (431-ICD-000150)
MRD-102 ESR-39 The ES shall support battery power Per Battery to Spacecraft EICD (431-ICD-000151)
11
Lunar Reconnaissance Orbiter (LRO)Electrical
System Level 2 Flow Down KeyTechnical
Demonstration Requirements
Level 2 Req. Level 3 Requirements Concept/Compliance
Paragraph Requirement
RLEP-LRO-P160, TRA 4.3, MRD-36 ESR-40 The ES shall support 1 switched 5 A service, 1 switched 2 A service, and SpaceWire for Mini-RF Per Mini-RF to Spacecraft EICD (431-ICD-000152)
12
Block Diagram (Data)
13
Block Diagram (Power)
14
Verification
  • By Analysis
  • Derating for current carrying capability
  • Transmission line (RF) of high-speed signals (ex
    SpaceWire)
  • By Test
  • Fit check on spacecraft mock-up
  • Continuity and High Potential (Insulation/Resistan
    ce) for workmanship
  • Network test (RF, SpaceWire, 1553)
  • Bakeout
  • S/C Level Integration
  • Safe-to-mate - as part of subsystem integration
  • Functional - as part of subsystem integration
  • Orbiter Level
  • EMI/EMC, Thermal Vacuum, Vibration

15
Summary
  • Electrical Systems requirements are understood
  • Electrical ICDs are in process
  • some into CM, some in internal review
  • Electrical Systems requirements are easily met
  • Standard harness materials and processes
  • We are ready to proceed with design
About PowerShow.com