NPSAT1 Spacecraft Architecture and Technology Demonstration Satellite Brief to SS3011 Space Technolo - PowerPoint PPT Presentation

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NPSAT1 Spacecraft Architecture and Technology Demonstration Satellite Brief to SS3011 Space Technolo

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Sensors: 3-axis magnetometer and solar panel currents. On-board orbit propagator ... New solar panels. Extension on top' Component mounting. VISIM FOV ... – PowerPoint PPT presentation

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Title: NPSAT1 Spacecraft Architecture and Technology Demonstration Satellite Brief to SS3011 Space Technolo


1
NPSAT1 Spacecraft Architecture and Technology
Demonstration Satellite Brief to SS3011 Space
Technology and Applications
  • Presented by
  • Dan Sakoda
  • Space Systems Academic Group
  • 777 Dyer Rd., Bldg. 233
  • Code (SP/Sd), Rm. 125
  • Monterey, CA 93943
  • (831) 656-3198

2
Introduction
  • Space Systems Education at NPS
  • Small Satellite Design Studies Background
  • NPS Facilities
  • NPSAT1
  • Mission Overview
  • Bus Architecture
  • Experiment Platform

3
NPS Space Program
  • Space Systems Operations
  • Space Systems Engineering
  • Space-Related Research
  • Spacecraft Technology
  • Space Environmental Effects on Semiconductors
  • Spacecraft Design

4
NPS Space Curricula
  • Two Curricula Engineering and Operations
  • Broad Scope of Disciplines (interdisciplinary
    education)
  • Masters Thesis Requirement on Space-Related
    Topic
  • Capstone Design Course
  • Six-Week Experience Tour

5
Space Systems Operations
  • Space Systems Operations
  • Master of Science in Systems Technology
  • Eight-quarter program
  • Broad Technical Overview
  • Space sciences / engineering
  • Information technology
  • Operations analysis
  • Acquisition management

6
Space Systems Engineering
  • Master of Science in one of five science or
    engineering disciplines
  • Nine-quarter program
  • Matrix of core technical courses
  • Specialization sequence for concentration in
    selected discipline

Astronautical Engineering Computer
Science Electrical Engineering Mechanical
Engineering Physics
7
NPS Smallsat Program Background
  • Hardware-in-the-loop education
  • Space-flight experiments
  • Space thermo-acoustic refrigerator (STAR)
  • Ferroelectric materials in space
  • Piggyback experiment
  • APEX DATASAT-X

8
NPS Smallsat Program Background
  • Complete spacecraft development
  • Full life-cycle development
  • Design, development, integration test
  • Launch and on-orbit operation
  • PANSAT (Discovery Shuttle, STS-95, 1998)
  • Microsatellite (digital communications)
  • Still operating (beyond 2-year design life)

9
PANSAT Launch Deploy (Oct. 98)
10
NPS Facilities
11
NPS Facilities (contd.)
  • PANSAT ground station
  • EMI shielded enclosure
  • Solar simulator
  • CAD/CAE Tools
  • Tensile-testing
  • Spherical air bearing
  • Battery test
  • Clean room (class 10,000)
  • N2 -purged, component storage
  • Precision machining (CNC mills)
  • Other test instruments (RF, digital, analog)

12
NPSAT1 Mission Overview
  • Objectives
  • Educational tool
  • Demonstrate low-cost, COTS architecture
  • PC-compatible command data handling (CDH)
    subsystem
  • POSIX-compliant operating system (Linux)
  • Demonstrate COTS technology for smallsats
  • FERRO RAM
  • Li-ion polymer batteries

13
NPSAT1 Mission Overview
  • Mission Requirements
  • 2-year mission life (min.)
  • 550 km-800 km, circular
  • 30-80 inclination
  • Secondary payload on a number of launch carriers
  • 3-Axis ACS (10 each axis)
  • NPS command ground station
  • MLV-05 Parameters
  • 560 km 10 km altitude, circular
  • 35.3 inclination
  • ESPA on Delta IV (medium EELV)
  • Lightband separation system

14
NPSAT1 Mission Overview
  • Objectives (contd.)
  • Experiment platform
  • Two NRL experiments
  • Coherent electromagnetic radio tomography (CERTO)
    beacon
  • Langmuir Probe
  • Three NPS experiments
  • Configurable processor experiment (CPE)
  • COTS micro-electromechanical systems (MEMS) rate
    sensor
  • COTS visible imager (digital camera)

15
NPSAT1 Experiments
  • NRL Experiments
  • Coherent Electromagnetic Radio Tomography (CERTO)
  • Two-frequency beacon
  • Ground stations measuring phase and amplitude
    scintillations
  • Total electron content (TEC) in ionosphere in
    plane of observation
  • Applications to radar, communications,
    navigation, surveillance

16
NPSAT1 Experiments
  • NRL Experiments (contd.)
  • Langmuir Probe
  • Augments CERTO data
  • In-situ measurements at orbit altitude
  • NPS Configurable Processor Experiment
  • Adaptable processor using FPGA
  • Non-volatile FERRO RAM for configuration memory
  • Add-on card within CDH housing
  • Various applications (triple-modular-redundant
    computer, compression algorithms)

17
NPSAT1 Experiments
  • MEMS rate sensor
  • Use COTS rate sensor
  • 5/sec range
  • Three sensors for 3-axis rates
  • 5 V at
  • Gain flight experience w/ MEMS devices
  • Use during acquisition (low sensitivity at
    orbital rates)
  • Use on a power-available basis

18
NPSAT1 Experiments
  • COTS Visual Imager (VISIM)
  • PC/104 interface card CCD camera
  • PC/104 cpu board
  • Array 652 x 492
  • Raw image Bayer format
  • Custom optics for

PC/104 Camera
19
NPSAT1 Experiments
  • COTS Visual Imager (VISIM) (contd.)
  • Generate data for officer students in space
    curricula
  • Research on-orbit processing of data (compression
    algorithms, etc.)
  • Educational outreach
  • Have k-12 schools task satellite for images
  • Distribute images via Internet (World Wide Web)
  • Spark interest in engineering / science

20
NPSAT1 Design Objectives
  • Low-cost design (
  • Utilizing existing hardware (structure solar
    cells)
  • Power mgmt. duty cycle electronics
  • Subsystems
  • Experiment payloads
  • Single-string design

21
NPSAT1 Configuration
  • Overall dimensions 75.4 cm (29.7 in.) height x
    50 cm (20 in.) diam.
  • CERTO deployable antenna
  • Deployable Langmuir probe
  • Deployable tip mass on GG boom
  • 1.07-inch (height) launch vehicle interface
    (Lightband)

22
NPSAT1 Configuration
23
System Block Diagram
24
NPSAT1 Design Overview CDH
  • CDH
  • X86 processor (Intel386EX)
  • Error-detection-and-correction (EDAC) RAM
  • PC/104 bus interface
  • IDE disk storage
  • Serial test interface via PPP

25
NPSAT1 Design Overview Software
26
NPSAT1 Design Overview ACS
  • ACS
  • 10 pointing accuracy
  • 0.66/sec max. rates
  • Similar control electronics as EPS
  • Actuators magnetorquers
  • Sensors 3-axis magnetometer and solar panel
    currents
  • On-board orbit propagator

27
ACS Block Diagram
28
NPSAT1 Design Overview EPS
  • Rad-hard parts micro-controllers RAM in both
    EPS ACS
  • Electrical Power Subsystem (EPS)
  • 28V bus
  • Silicon solar cells / Li-ion polymer batteries
  • DC/DC conversion at the subsystem
  • Watchdog timer for resetting CDH

29
NPSAT1 Design Overview Communications
  • Communications Subsystem
  • GMSK modulation
  • Full Duplex
  • 100 kbps data rate
  • Uplink at 1.767 GHz
  • Downlink at 2.207 GHz

Modem Development System
30
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31
NPSAT1 Design Overview Structure
  • Mechanical Structure
  • Robust, aluminum frame panels
  • Inherited parts from excess property
  • Necessary modifications
  • Launch vehicle interface
  • New solar panels
  • Extension on top
  • Component mounting
  • VISIM FOV

32
NPSAT1 Design Overview Structure
33
NPSAT1 Design Overview Thermal
  • Thermal
  • Li-ion polymer batteries 0 to 45 C
  • Electronics -25 to 85C (industrial grade)
  • Preliminary analysis cold environment
  • Average spacecraft power 31.5 W
  • Batteries requiring thermal isolation heaters

34
SDRC I-DEAS Thermal Model
  • Orbital Parameters
  • 550 km, circular orbit
  • Beta angle (angle between orbit plane and sun) of
    zero
  • Heat Input
  • Constant heat input of 31.5 W
  • Distributed over three lower equipment plates (8
    W on upper-mid, 10 W on lower-mid, 13.5 W on base
    plate)
  • Transient Analysis
  • Duration 1/2 day
  • Results Output 120 sec

35
I-DEAS Thermal Results
36
(/- X)-Facing Panels
37
(X)-Facing Panel Temperatures
38
(X) Panels Single Orbit
39
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40
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41
Solar Panel Thermal Analysis Results
  • Overall range of temperatures 30C to -22C
  • /- X Panels showing extreme temperatures
  • Max. Temperature
  • Min. Temperature -22C
  • Leading edge (X) panels slightly warmer than
    (-X) trailing edge panels
  • No appreciable difference between positive Y
    panels and negative Y panels
  • Max. Temperature
  • Min. Temperature -19C

42
NPSAT1 Design Overview
  • Experiments
  • Must be able to duty-cycle (power off)
  • Can use telemetry command (TC)
  • On-board memory storage available
  • Can use real-time clock

43
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44
NPSAT1 Web Site
For more information . . . http//www.sp.nps.navy.
mil/npsat1
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