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By Matthew Patterson

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... develop and complete an entire mission for typical large satellites is enormous. ... We will send a microsatellite into a LEO, sun-synchronous, polar orbit ... – PowerPoint PPT presentation

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Title: By Matthew Patterson


1
By Matthew Patterson
2
LowEarthOrbitNanosatelliteIntegratedDistribut
edAlertSystem
3
Why focus on Nanosats?
  • The cost and time to design, develop and complete
    an entire mission for typical large satellites is
    enormous.
  • Microsatellites and Nanosatellites allow quicker
    mission overturn.
  • Risk for missions are reduced
  • Provide a means to test new scientific
    technologies
  • Because we have the ability to complete an entire
    mission from concept design to launch

4
The LEONIDAS Team
  • Project Director-Dr. Luke Flynn
  • Principal Investigator- Lloyd French

Aukai Kent Payloads Dennis Dugay -
Communications Matt Patterson - Power Zachary
Lee-Ho - Systems Engineer
Jennie Castillo Orbits Kaipo Kent
Thermal Lynette Shiroma - Attitude Control Minh
Evans Command Data Handling Mike
Menendez - Structure and
Mechanical Devices
5
What have we accomplished?
  • Learned the basic concepts in mission design
    and development
  • Developed a mission concept report for the
    LEONIDAS BUS
  • Prepared proposal for Air Force Office of
    Scientific Research University Nanosatellite
    Competition
  • Presented our mission design to Jet Propulsion
    Laboratory and Ames

6
Mission Objectives
  • We will send a microsatellite into a LEO,
    sun-synchronous, polar orbit
  • The microsatellite will serve as a platform for
    demonstrating scientific technologies
  • Data attained through the operations of the
    scientific technology payloads will be
    transmitted to the ground station
  • The development, manufacturing and launching of
    the satellite will serve as an educational tool
    for aiding the development of students at the
    University of Hawaii at Manoa

7
Plug and Play Bus
8
Mission Requirements
  • Satellite must accurately point and orient itself
    to take a picture of Hawaii
  • Satellite shall be robust and reliable
  • This will be accomplished through
  • Minimizing the use of mechanical devices
  • The use of COTS components and interfaces
  • Operation of payloads or communication with
    ground station will be accomplished within the 14
    minute viewing window of each orbit.
  • Cost of components must not exceed 500k
  • Cost estimation does not reflect the cost for
    structure and sublimation thrusters
  • All scientific demonstrations will be performed
    within the projected mission lifetime of six
    months
  • The shall be sufficient amount of battery power
    to operate the satellite for a duration of 12
    hours, in the event the photovoltaics should
    fail.

9
Power Regulation and Distribution
10
Power Management and
Distribution
  • Objective
  • To provide, store, distribute, and control the
    satellites power at Beginning of Life (BOL) and
    End of Life (EOL).
  • Key Requirements
  • To provide a continuous source of power to loads
    and subsystems through out the mission life (6
    months 1 year).
  • Support and distribute different voltages (3, 5,
    -12, 28V) to variety of loads.
  • Provide enough power to support peak electrical
    load and provide enough power at total loss of
    solar cells for 12 hrs.
  • Protect against failures in the System.
  • Fit volume and weight budget 20x27x11cm3, 4.1
    kg

11
Space
Shunts
PV
Batteries
TTC
Thermal
Sun
Earth
PV
PRU
PDU
ACS
Payloads
CDH
Batteries
PV
Shunts
Space
12
PV Ultra Triple Junction Cells
GaInP/GaAs/Ge
(Gallium Indium diphosphate/Gallium
Arsenide/Germanium)
  • Bare Cells
  • Weight 76.608 mg
  • Dimensions .5 x .22 (m)
  • Thickness 0.140 mm
  • Operating Temperature range (0C 75 C)
  • For every degree off, degrades by .5
  • UTJ (Ultra Triple Junction) Solar Cell
  • BOL average efficiency 28.3
  • EOL average efficiency 24.3
  • Degrades .8 per year
  • BOL
  • Power _at_28.3x1,367 W/m2(average solar
    illumination intensity) 386.86 W/m2
  • Power of Sat 386 W/m2 x .114 m2 44 W per
    panel
  • Peak Power output of solar panels (ideal 3
    panels) 106.225 W
  • EOL (5 year lifetime)
  • Power _at_24.3 332.181 W/m2

13
Rechargeable Lithium-ion
Battery
  • Characteristics
  • Height .065 m
  • Width .060 m
  • Thickness .0196 m
  • Weight .153 kg
  • Energy 26 Wh
  • Life 500 cycles
  • Charge Temp range (-20C 75 C)
  • Charge rate 2 to 3 hrs _at_ 6.8 A
  • of batteries ?
  • In order to meet last for 12 hrs at total failure
    of Solar Cells
  • of batteries needed to operate 16

14
Power Regulation Unit HESC
104 High Efficiency and Smart
Charging Vehicle Power Supply
  • Characteristics
  • Length .09525 m
  • Width .09017 m
  • Height .01524 m
  • Weight .186 kg
  • Temp range (-40C 85 C)
  • Charge Current 0 to 4 A
  • Charge Voltage 9.5 to 19.5 V
  • Input Voltage 6 to 40 V
  • Provides for 3, 5, -12 V

15
Analysis of Requirements
  • Given
  • WBol, avg 106.225 W
  • WEol, avg 91.499 W
  • Need
  • Wpeak, bus 76 W x 30 99 W
  • Wellipse, bus 40 W x 30 52 W
  • Weight lt 4.1 kg
  • .186 kg (PRU)
  • 76.608 mg (Bare Cells)
  • .153 kg x 10 (batteries)
  • 1.716 kg
  • casing for solar cells, extra batteries,
    more PRUs if needed, wires, resistors)
  • lt 4.1 kg
  • Volume lt 20x27x11 cm
  • PRU 9.5 x 9.0 x 1.5 cm
  • Battery 6.5 x 6.0 x 1.96 cm
  • Plenty of room because the batteries may be in
    their own side compartment.
  • Temperature, to satisfy all (0C 75 C)
  • Life
  • Ideally we can last for 2 yrs. If everything
    doesnt degrade faster than expected and still
    needing the same power.

16
Whats left?
  • Everything!!!!
  • Cost
  • Integrating
  • My parts
  • Sats parts
  • Case for solar panels meeting mass budget
  • Team analysis on subsystems needs
  • More calculations!!!

17
Gantt Chart
Team Chart
My Chart
18
Thank You!!
  • Till the next time!!!
  • Happy Thanksgiving Everyone!!!
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