Project Spartnik Objectives

1
(No Transcript)
2
(No Transcript)
3
Project Spartnik Objectives

• To design, construct, test, and operate a
• microsatellite by primarily undergraduate
• students
• To give students practical design
• experience in an interdisciplinary team
• environment
• Use and enhance current microsatellite
• technologies

4
Mission Requirements

• Two-year minimum operational life
• Design a low-cost microsatellite
• No propulsion system
• HAM frequencies
• Passive and/or autonomous systems
• Identification of design drivers

5
Mission Requirements

• Meet the secondary payload constraints for
• multiple launch vehicles
• Design to multiple orbit configurations
• Greater than 40o inclination
• 450 to 900 km altitude
• Support Payloads
• Digital color camera
• Micro-Meteorite Impact Detector (MMID)
• Communications package hardware

6
Spartnik Subsystems

• Structures
• Cleanroom
• Launch Vehicle (LV) and Orbit
• Payload
• Attitude Determination and Control (ADAC)
• Electrical Power
• Thermal
• Telemetry, Tracking and Communications
• (TTC)
• Ground Station
• Mobile Ground Station (MGS)

7
Structures Subsystem
Subsystem Engineers
Norman Fernando Emily Cronin Paul
Gregory Eliazar Ortiz Tristan Pradelle Francisco
Ragsac Mentor Dr. Eric Abrahamson
8
Structures Subsystem
Spartnik Shell and Trays
9
Structures Subsystem
Spartnik Infrastructure
10
Structures Subsystem
L-Stand Adapter
11
Structures Subsystem
Launch Vehicle Adapter
12
Structures Subsystem
Grapple System

• Purpose
• Safe transportation of Spartnik onto launch
  vehicle
• Easy manipulation of Spartnik

13
Structures Subsystem
Grapple System

• Two piece system
• Top Handle
• Bottom Handle
• Two Person Operation
• Placement on
• Spartnik

14
Structures Subsystem
Grapple System

• Bottom Handle (x3)
• Attachment to LVA

15
Structures Subsystem
Grapple System

• Top Handle
• Placement
• Fully Integrated
• Grapple System

16
Structures Subsystem
Antenna System

• Purpose
• Meet Launch Criteria
• Communication Relay
• Solar Pressure Paddles
• Concept
• Spring Loaded Release
• Mechanism
• Reliable

17
Structures Subsystem
Antenna System

• Design
• Modification
• Constraint
• Power
• Model
• Stowed Position
• Extended Position and Placements

18
Structures Subsystem
Manufacturing

• Spartnik Integration Procedure (SIP)
• 3 Stages
• System Tests
• Satellite Test

19
Structures Subsystem
Manufacturing

• Lower Stage
• Hysteresis Rods
• Spacers
• Computer/
• Communications Subsystem
• Computer/
• Communications Tray

20
Structures Subsystem
Manufacturing

• Middle Stage
• Batteries
• Power Box
• Power tray

21
Structures Subsystem
Manufacturing

• Top Stage
• Top Plate
• Nutation Damper
• I/R Sensors
• Micrometeorite
• Detector (MMID)
• Payload Tray
• Camera Box
• Camera
• Periscope
• Shell

22
Structures Subsystem
Manufacturing

• Testing
• Subsystem
• Antenna
• Grapple System
• Satellite
• Thermal
• Dynamic

23
Structures Subsystem
Manufacturing

• All Integration tasks to be documented
• in SIP.
• Integration to be performed using safety
• practices outlined in safety document.

24
Structures Subsystem
Remaining Tasks

• Fabrication/Assembly
• Periscope
• Assembly of the camera in the camera box
• Integrate camera with periscope
• Attachment of the camera box to the top face
• Computer box
• Assembly of the computer components in the
• computer box
• Attachment of the computer box to the bottom
• face
• Final integration of the entire structure
• Integration of the shell with the trays

25
Structures Subsystem
Finite Element Analysis

• Finite Element Methods (FEM)
• - Pro Mechanica
• - NASTRAN
• Structural loads on Spartnik

26
Spartnik Subsystems

• Structures
• Safety
• Cleanroom
• Launch Vehicle (LV) and Orbit
• Payload
• Attitude Determination and Control (ADAC)
• Electrical Power
• Thermal
• Telemetry, Tracking and Communications
• (TTC)
• Ground Station
• Mobile Ground Station (MGS)

27
Safety Subsystem
Subsystem Engineers
Paul Gregory Norman Fernando Becky
Houliston Peter Mazanec Mentor Mike
Jeung-Wesoloski
28
Safety Subsystem
Safety Objectives

• Ensure Spartniks integrity during
• liftoff and deployment
• Main purpose is to produce Safety
• Document

29
Safety Subsystem
Safety Objectives

• Purpose of Safety Document
• Present to prospective launch vehicle
• companies
• Review and Analyze possible hazards
• Document any possible hazards to LV and
• other payloads
• Nutation damper Batteries
• Release Mechanism Structural

30
Spartnik Subsystems

• Structures
• Cleanroom
• Launch Vehicle (LV) and Orbit
• Payload
• Attitude Determination and Control (ADAC)
• Electrical Power
• Thermal
• Telemetry, Tracking and Communications
• (TTC)
• Ground Station
• Mobile Ground Station (MGS)

31
Cleanroom Subsystem
Subsystem Engineers
Emily Cronin Paul Gregory Rocio Duran Ruben
Garza
32
Cleanroom Subsystem
Cleanroom Objectives

• Main purpose is for satellite testing
• and integration
• Maintain a cleanliness level
• required for optics/sensors
• Ensure that Spartnik will not
• contaminate primary payload and
• launch vehicle

33
Cleanroom Subsystem
Spartnik Cleanroom

• Cleanroom Specs
• 3 laminar-flow hoods mounted on
• C-frames
• Enclosed area of 110 Square feet
• Cleanliness level Class 100 under hoods
  Class 1000 general area

34
Cleanroom Subsystem
Spartnik Cleanroom
35
Spartnik Subsystems

• Structures
• Cleanroom
• Launch Vehicle (LV) and Orbit
• Payload
• Attitude Determination and Control (ADAC)
• Electrical Power
• Thermal
• Telemetry, Tracking and Communications
• (TTC)
• Ground Station
• Mobile Ground Station (MGS)

36
LV Orbit Subsystem
Subsystem Engineers
Clayton Taylor William Blanch Emily Cronin Greg
Rodgers
37
LV Orbit Subsystem
Desired Orbital Parameters

• Design Parameters
• Minimum lifetime of two years
• Altitude range of 450 - 900 (km)
• Maximize duration of passes
• Inclination greater than 40o

38
LV Orbit Subsystem
Orbital Modeling Software

• Satellite Tracking Program (STP)
• Modeling parameters
• Altitudes 450 - 800 km
• Inclinations 60, 90 degrees
• Eccentricities 0 - 0.0365
• Perturbation forces
• Earth oblateness

39
LV Orbit Subsystem
Candidate Launch Vehicles

• Small
• Athena
• Pegasus
• Minotaur
• Medium
• Kosmos
• Intermediate
• Sea Launch
• Large
• Proton
• Ariane V
• Delta IV

40
LV Orbit Subsystem
LV Selection Process

• Mission objectives
• Secondary payload
• Environmental tests
• Monetary requirements

41
LV Orbit Subsystem
Safety Analysis

• Lockheed Martin California State
• University Cooperative
• Microsatellite Safety Certification
• Certification Template
• Microsatellite Spartnik safety certified

42
LV Orbit Subsystem
Candidate Launch Sites
Kourou French Guiana
43
LV Orbit Subsystem
Candidate Launch Sites
Wallops Flight Facility
Western Test Range Vandenberg AFB
Eastern Test Range Cape Canaveral
44
LV Orbit Subsystem
Work In Progress

• Acquisition of launch vehicle
• Ariane5
• Minotaur
• Delta
• Sea Launch
• Athena
• Proton
• Pegasus

45
LV Orbit Subsystem
Work In Progress

• Arianespace
• Ariane V
• ILS
• Athena
• Proton
• Orbital Sciences Corporation
• Pegasus
• Boeing
• Sea Launch
• Delta
• Air Force
• Minetaur

46
Spartnik Subsystems

• Structures
• Cleanroom
• Launch Vehicle (LV) and Orbit
• Payload
• Attitude Determination and Control (ADAC)
• Electrical Power
• Thermal
• Telemetry, Tracking and Communications
• (TTC)
• Ground Station
• Mobile Ground Station (MGS)

47
Payload Subsystem
Subsystem Engineers
Norman Fernando Emily Cronin Tristan
Pradelle Francisco Ragsac
48
Payload Subsystem
Onboard Payloads

• Micro-Meteorite Impact Detector
• (MMID)
• Kodak Color Digital Camera

49
Payload Subsystem
Camera Box Design

• Material
• 6061 T-6 aluminum
• 1/4 top
• 1/8 sides and bottom
• Dimensions
• 8.6 x 8.6 x 2.65
• Camera mounting
• Horizontally under Z face
• Space rated foam

50
Payload Subsystem
Payload Placement
MMID
Side View
Top View (Z face)
51
Payload Subsystem
Periscope

• Two Piece Unit
• Mirror Holder
• Mirror Housing

52
Payload Subsystem
Mirror, Lens and Periscope Placement

• Periscope Housing
• Lenses Mirror
• IR UV Filters
• (in progress)

53
Payload Subsystem
Camera Protection

• Conformal Coating
• Foam Enclosure
• Silicon Enclosure

54
Payload Subsystem
Conformal Coating

• Prevent Outgassing
• Radiation Protection
• Paralene C

55
Payload Subsystem
Foam Enclosure

• Survive Launch Criteria
• Roachell Foam

56
Payload Subsystem
Silicon Enclosure

• Various Assets
• Requirements for Silicon

57
Payload Subsystem
MMID

• Piezoelectric strip sensor
• 6.75 in. x 0.86 in. x .008 in.
• Records impact occurrence and
• magnitude as voltage pulses

58
Payload Subsystem
Payload Block Diagram
Spartniks Antennas
Camera
SJSU Ground Station
CPU
MMID
59
Payload Subsystem
Camera Field of View

• Pointing Accuracy

• Pointing Accuracy

60
Payload Subsystem
Color Digital Camera

• KODAK DC40
• Can take 4 - 6 pictures per orbit
• 4 MB Flash RAM

61
Payload Subsystem
Camera Positioning

• Sweeping Technique
• Z-Face Positioning

62
Payload Subsystem
Camera Modifications

• Flash removed
• LCD display removed
• Capacitors replaced
• Conformal coating with Paralene C
• to prevent outgassing
• Plastic lens replaced by periscope
• with space rated optic lens

63
Payload Subsystem
In Progress

• Test camera for motion blur
• Integration
• Camera vacuum test
• Verify hardware
• Verify camera operation procedures
• Camera modifications
• Conformal coating
• Periscope tests

64
Spartnik Subsystems

• Structures
• Cleanroom
• Launch Vehicle (LV) and Orbit
• Payload
• Attitude Determination and Control
• (ADAC)
• Electrical Power
• Thermal
• Telemetry, Tracking and Communications (TTC)
• Ground Station
• Mobile Ground Station (MGS)

65
Subsystem Engineers
William Blanch Tristan Pradelle Emily
Cronin Greg Rodgers
66
Flight Hardware
67
Controlled Tumble
68
Spacecraft Nutation
69
Earth Horizon Sensors
70
Simulations Performed

• Original control system design
• Investigated variation of
• Spin rate
• Number of magnets
• Moments of inertia
• Simulation run at 500 and 1,000 km
• Note All runs were circular, polar orbits

71
Simulation Results

• Results
• Excessive nutation
• Inability to lock onto Earths magnetic field
  at
• higher altitudes
• Final control system design
• Increase number of magnets to 8
• Decrease spin rate
• Lower moments of inertia

72
Simulation Results
73
Attitude Determination Algorithm

• Purpose
• Gathering data on actual spin and tumble rate
• Solar panel current data
• Magnetic field data
• IR sensor

74
Accomplishments

• Construct - Test - Assemble ADAC flight
• Hardware
• Magnets- Inserted
• Solar pressure paddle design complete
• Dynamic model of Spartniks attitude
• ADAC simulations
• Longer run times-completed
• Quantify performance of new control system-
• completed

75
Projects Pending

• Integrate ADAC flight hardware into
• Spartnik
• Analysis of IR detector
• Hysteresis rod research
• New analysis of EOMs
• New nutation damper design

76
Spartnik Subsystems

• Structures
• Cleanroom
• Launch Vehicle (LV) and Orbit
• Payload
• Attitude Determination and Control
• (ADAC)
• Electrical Power
• Thermal
• Telemetry, Tracking and Communications (TTC)
• Ground Station
• Mobile Ground Station (MGS)

77
Electrical Power Subsystem
Subsystem Engineers
Robbie Singh Norman Fernando Rocio
Duran Mentors Dave Nawrocki and Mike
McCormick
78
Electrical Power Subsystem
Overview

• Main Components
• Solar Panels
• Power Controller
• Batteries
• Satellite Wiring

79
Electrical Power Subsystem
Solar Panels

• Solar Panel Characteristics
• GaAs Cells Total 40 strings Each string
  consists of 12 cells TOTAL CELLS 480
• Optimum power output 8 Watts ( 9 V _at_ 0.8 A )
• Blocking diodes
• Electromagnetic interference
• Donated by ASEC

80
Electrical Power Subsystem
Power Controller
Switching to Initiate Payload Power
Solar Power Switching
Battery Charge Switching
K4
K1
M1
M2
M3
K2
K3
K6
K5
Solar Array
Solar Array
K7
PAYLOADS
Battery 1
Battery 2
Discharge Switching
LaunchVehicle
81
Electrical Power Subsystem
Battery Packs

• 6 NiCd cells in series
• 4 A-Hr
• Nom. Voltage 7.2 VDC
• SAFT
• Internal thermocouples
• Aluminum housing
• Xylan coating (AIC)
• DB 9 connector
• Acquisition in progress

82
Electrical Power Subsystem

• Micro-switches
• Off shelf product
• Purchase in progress
• Momentary action
• Wiring
• Wiring diagram in progress

83
Electrical Power Subsystem
Powering the Satellite
 
84
Spartnik Subsystems

• Structures
• Cleanroom
• Launch Vehicle (LV) and Orbit
• Payload
• Attitude Determination and Control (ADAC)
• Electrical Power
• Thermal
• Telemetry, Tracking and Communications (TTC)
• Ground Station
• Mobile Ground Station (MGS)

85
Thermal Subsystem
Subsystem Engineers
Becky Houliston Teddy Long Phil Canlas Mentor
Bob Clark
86
Thermal Subsystem
Overview

• Passive Thermal Control
• Internal radiation
• Spacers provide conduction path
• Radiation to space
• Thermal monitoring
• Integrated circuit temperature transducers
• Provide data to camera and battery
• manufacturers
• Thermal analysis
• SINDA
• SINDA 3D

87
Thermal Subsystem
Temperature Limits
88
Thermal Subsystem
External Heat Loads

• Earth-Orbit Heat Loads
• Direct sunlight
• Reflected sunlight
• Earth-generated

89
Thermal Subsystem
SINDA Analysis

• Commercial thermal analysis program
• Network-style (resistor-capacitor)
• Simulates conduction, radiation
• Finite Difference Method
• Resistors representing conductors,
• radiation
• 304 node model representing Spartnik

90
Thermal Subsystem
SINDA Analysis
91
Thermal Subsystem
SINDA 3D
92
Thermal Subsystem
FOSR Layout
Circular FOSR patches
Cutouts for payloads
Cut-outs for solar panels
Exposed Aluminum painted black
93
Thermal Subsystem
Temp Sensor Placement

• Verify prediction of thermal design
• 30 Analog Devices (AD) thermocouples
• in satellite
• One centered in each shell panel
• Each major component
• Adequately characterize temperature
• Gathers operational temperature
• information

94
Thermal Subsystem
Temp Sensor Placement
95
Spartnik Subsystems

• Structures
• Cleanroom
• Launch Vehicle (LV) and Orbit
• Payload
• Attitude Determination and Control (ADAC)
• Electrical Power
• Thermal
• Telemetry, Tracking and
• Communications (TTC)
• Ground Station
• Mobile Ground Station (MGS)

96
Telemetry Tracking and Command Subsystem
Subsystem Engineers
Teddy Long John Robinson Keiko Endo John
Van Arsdall Phil Canlas Peter Mazanec Greg
Rodgers Wenrui Mui Akarsha Kumar Paul
Gregory Mentors Jeff Nokes and Steve
Peterson
97
Telemetry Tracking and Command Subsystem
Overview

• Computer Hardware
• Computer Software
• Ground Station

98
Telemetry Tracking and Command Subsystem
Computer Hardware Requirements

• Implement real time control for
• Performing self-testing, housekeeping,
• subsystem management, communications
• Meet power budget of 1 Watt
• 80C188EC Associated Hardware runs on
  milliwatts, SRAM CPU Sleep Mode
• Minimize circuit board size
• custom design allowing for no wasted space

99
Telemetry Tracking and Command Subsystem
Requirements (cont.)

• Full Command Capability
• Complete control of all on-board systems
• Reprogram in Flight
• Upload new code to run the satellite and
  update operational registers
• Future Expandability
• Design for minimal hardware/software changes
• for and future mission requirements
• All Programming in ANSI C, from Scratch
• Allows for efficient coding, greater
  functionality,
• quicker results and in-house bug control

100
Telemetry Tracking and Command Subsystem
CPU Technology

• Uses Intel 80C188EC
• Same CMOS technology as 80386
• Smaller board layout
• Cost saving
• Power consumption saving
• Meets power budget of 1 Watt
• Custom design provides expandability for
• future satellites

101
Telemetry Tracking and Command Subsystem
Software Mission Requirements

• System initialization
• Boot-up
• Device initialization
• Mission management
• Interrupt driven operating system
• Battery operations (passive charging)
• Data collection

102
Telemetry Tracking and Command Subsystem
Mission Requirements (cont.)

• Housekeeping
• Payloads (temperature, voltage IR)
• Solar cell current
• Contingency operations
• System emergencies
• Intentional excursions

103
Telemetry Tracking and Command Subsystem
Ground Station

• Autonomous Satellite Communication
• Multitasking Automated Track and Control
• MS Windows NT
• Receive Stored Realtime Telemetry
• Command Realtime
• Database Telemetry/Payload Data Manipulation
• Public Software Application (Portable Platform)
• Public Internet Access for Data

SJSU Ground Station Operator
SJSU College of Engineering
104
Telemetry Tracking and Command Subsystem
Communication

• Utilizes Amateur Radio Frequencies
• 70cm uplink (9600 Bps), 2m downlink (1.2 to
  57.6
• KBps)
• Multitask/Multithread Kernel (similar to
• UNIX)
• Custom OS written in C utilizing soft/hard
  interrupts
• 8 Simultaneous Users (estimated)
• 2 System Administrator accounts
• 6 Public User accounts
• Ground station autonomous

105
Telemetry Tracking and Command Subsystem
Public Access

• Beacon with Constant Telemetry Downlink
• HAM Radio User Chat Room
• File Transfer via PACSAT (similar to FTP)
• Command Camera Real-time
• Download picture immediately
• Download Stored Telemetry, Pictures
• (Files) and MMID Data

106
Telemetry Tracking and Command Subsystem
Computer Firsts

• All Hardware and Software Designs will
• be available free for public use
• A completely custom computer running a
• full multitasked/multithreaded OS with a
• hardware design keeping power
• consumption under 1 Watt.
• AX.25 raw code will be free for public use
• PACSAT raw code will be free for public use

107
Spartnik Subsystems

• Structures
• Cleanroom
• Launch Vehicle (LV) and Orbit
• Payload
• Attitude Determination and Control (ADAC)
• Electrical Power
• Thermal
• Telemetry, Tracking and
• Communications (TTC)
• Ground Station
• Mobile Ground Station (MGS)

108
Mobile Ground Station
Subsystem Engineers
William Blanch Clayton Taylor Paul Gregory
109
Mobile Ground Station
110
Mobile Ground Station
111
Mobile Ground Station
Sample Designs
112
(No Transcript)
113
Project Status

• Software development
• Camera box
• Internal wiring model
• Attitude determination model
• SINDA thermal analysis
• Battery testing
• Orbital analysis
• Launch Vehicle acquisition
• Flight model integration

114
Spartnik Outreach

• Sharing the Knowledge
• K-12
• Los Paseos Elementary School
• Santa Teresa High School
• Independence High School
• Menlo-Atherton High School
• Junior Colleges
• Mission College
• West Valley College
• Bakersfield College
• Universities
• University of Washington
• UC Santa Cruz
• Santa Clara University
• Stanford University

115
Industry Mentors

• Pat Machmiller
• Dave Nawrocki
• Jack Lovegren
• Eric Abrahamson
• Sean Medina
• Kevin Friend
• Kevin Bilger
• Steve Petersen
• Ron Fischler
• John Mattingly

• Mike McCormick
• Jim Currier
• Carl Strombaum
• Steve Tyley
• Len Kwiatkowski
• Jeff Nokes

116
Industry Contributors

• Lockheed Martin
• Corporation
• UTC-CSD
• Eagle-Picher
• Satellite Power
• Corporation
• Optical Coating
• Laboratories Inc.
• Kodak
• Teledyne
• Flow Star Corp.
• Hewlett Packard
• NuSil

• Stanford Satellite
• Development Lab
• Shur-Lok
• USGS
• Logitech
• Teklam
• Dexter Magnets
• Richmond Aircraft
• LL Grace
• Communications
• Lord Corp.
• Packaging Systems Inc.

117
Spartnik
www.engr.sjsu.edu/spartnik
118
(No Transcript)