By Matthew Patterson

LowEarthOrbitNanosatelliteIntegratedDistributedAlertSystem

LowEarthOrbitNanosatelliteIntegratedDistributedAlertSystem

Why focus on Nanosats?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

–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

The LEONIDAS TeamThe LEONIDAS Team

•Project Director-Dr. Luke Flynn•Principal Investigator- Lloyd French

•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

What have we accomplished?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

•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

Mission ObjectivesMission 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

– 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

Plug and Play BusPlug and Play Bus

Mission RequirementsMission 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.

• 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.

Power Regulation

and Distribution

Power Regulation

and Distribution

Power Management and Distribution

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: 20x27x11[cm3], 4.1 kg

• 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: 20x27x11[cm3], 4.1 kg

Sun Earth

Space

Space

Batteries

Batteries

Shunts

Shunts

PV

PV

PV

PRU PDU

TT&C

C&DH

ACS

Thermal

Payloads

PV: Ultra Triple Junction Cells GaInP/GaAs/Ge (Gallium Indium diphosphate/Gallium Arsenide/Germanium)

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 = (0˚C – 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 @28.3%x1,367 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 @24.3% = 332.181 W/m2

– Power of Sat = 37.9 W per panel– Peak Power output of solar panels = 91.499 W

• Bare Cells– Weight = 76.608 mg– Dimensions = .5 x .22 (m)– Thickness = ~ 0.140 mm

• Operating Temperature range = (0˚C – 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 @28.3%x1,367 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 @24.3% = 332.181 W/m2

– Power of Sat = 37.9 W per panel– Peak Power output of solar panels = 91.499 W

Rechargeable Lithium-ion Battery 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 = (-20˚C – 75 ˚C)– Charge rate = 2 to 3 hrs @ 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

• Characteristics– Height = .065 m– Width = .060 m– Thickness = .0196 m– Weight = .153 kg– Energy = 26 Wh– Life = 500 cycles– Charge Temp range = (-20˚C – 75 ˚C)– Charge rate = 2 to 3 hrs @ 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

Power Regulation Unit HESC 104 High Efficiency and Smart Charging Vehicle Power Supply

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 = (-40˚C – 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

• Characteristics– Length = .09525 m– Width = .09017 m– Height = .01524 m– Weight = .186 kg– Temp range = (-40˚C – 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

Analysis of RequirementsAnalysis 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 < 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 PRU’s if needed, wires, resistors)

< 4.1 kg

• 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 < 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 PRU’s if needed, wires, resistors)

< 4.1 kg

• Volume: < 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 = (0˚C – 75 ˚C)

• Life– Ideally we can last for 2 yrs. If

everything doesn’t degrade faster than expected and still needing the same power.

• Volume: < 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 = (0˚C – 75 ˚C)

• Life– Ideally we can last for 2 yrs. If

everything doesn’t degrade faster than expected and still needing the same power.

What’s left?What’s left?

• Everything!!!!• Cost• Integrating

– My parts– Sats parts

• Case for solar panels meeting mass budget• Team analysis on subsystems needs• More calculations!!!

• Everything!!!!• Cost• Integrating

– My parts– Sats parts

• Case for solar panels meeting mass budget• Team analysis on subsystems needs• More calculations!!!

Gantt ChartGantt Chart

  Sept Oct Nov Dec Jan Feb Mar

AFOSR Done          

JPL PDR   Done          

JPL CDR              

POWER              

  Sept Oct Nov Dec Jan Feb Mar

Find Item Done          

Cost   Waiting   on    companies    

Integrating              

Research              

Team Chart

My Chart

Thank You!!Thank You!!

Till the next time!!!

Happy Thanksgiving Everyone!!!

Till the next time!!!

Happy Thanksgiving Everyone!!!