Title: Space Based Solar Power Satellite Conceptual Design for Retrodirective Control
1Space Based Solar Power Satellite Conceptual
Design for Retrodirective Control
- Space Engineering Institute
- Spring 2009
2Overview
- Creating a satellite module that will be attached
to a Japanese experimental satellite in a
Low-earth orbit. - Our team objective is to create a satellite
module that can test the retrodirective beam
control method of sending microwave power back to
Earth. - The module must provide its own power, and have
its own thermal management systems.
3Module System Sandwich Design
Space Environment Orbit
Photovoltaic Cells
Structures Materials
Thermal Management
Energy Storage Power Conversion
Antenna Array
Retrodirective Control logic
4Environment Analysis
5Semester Goals and Expectations
- Become familiar with Satellite Tool Kit software
- Model a cubic satellite and evaluate solar energy
collected at each of its six faces to identify
the optimum location for the solar panels - Determine the maximum, minimum, and average solar
energy collected on the optimum location during
one orbit
6Satellite Orientation
- Orange-North
- Green- South
- White- Nadir
- Yellow-Zenith
- Purple-Leading
- Teal- Trailing
7Satellite Orbit Options
- Geostationary
- Altitude 35,786 km
- Inclination 0º
- Low Earth Orbits
- Critically Inclined Sun Synchronous
- Perigee altitude 400 km
- Retrograde inclination 116.565º
- Circular
- Altitude 500 km
- Inclination 45º
- ETS-VII Japanese satellite with similar initial
conditions - Altitude 550 km
- Inclination 35º
8Energy and Power Received
- Power a cos(?)
- ? angle between the sun vector
- and the vector pointing normal to
- the face
- Units W/m2
- EnergyPowerTime
- Units J/m2
- Also dependent on the cosine of ?
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9Approach
- STK provides angular data for each face of the
cubic satellite - Angular data are converted to power W/m2
- Power data are converted to energy data J/m2
10Data from STK
11Data from STK
The Zenith, Nadir, Leading and Trailing faces
have approximately the same exposure to the sun.
The antenna will be located on the Nadir face, so
it reasonably follows that the solar panels be
placed on the Zenith face, directly opposite the
antenna. A circular orbit with an altitude of 500
km and inclination of 45 was chosen, because
with the options available, this orbit allows the
solar panels to receive the most sunlight.
12Thermal Management
13Thermal Management
- Objective
- To perform thermal analysis of the satellite and
ensure a suitable operating environment for the
payload. - Tools
- Thermal Desktop software
- Research Topics
- Low earth orbit environment
- Temperature requirements for internal components
- Cooling/heating methods
14External Environment
- In LEO, the satellite will be heated by
- Direct sunlight
- Earths albedo
- Earths IR emittance
-
- The total heat absorbed by the satellite will not
remain - constant. Fluctuations occur due to
- Entering/exiting Earths shadow
- Varying surface conditions on Earth
15Satellite Interior
- The interior environment of the satellite must be
kept at - a proper temperature range. Most electronic
equipment - onboard must operate in a surrounding temperature
- range of 0 to 50 degrees Celsius.
- Factors to consider for the internal energy
balance - Fluctuating external heat rates
- Heat released by electronic equipment
- -Low level baseline operation
- -High level during periodic transmission
- Thermophysical properties of structural material
16Cooling/Heating Methods
- External
- Radiators Do not require energy. Release heat
without re-entry (thermal diode) - Internal
- Thermoelectric Coolers/Heaters Require energy.
Can absorb/emit heat by reversing polarity - Mechanical cooling Expander, compressor, or heat
exchanger. Takes up space and weight. - Resistive Heating Requires energy but elements
are compact in size. - Heat Pipes Passive
17Thermal Desktop
- Objectives
- Develop a model for the satellite module.
- Use the orbital information from STK to determine
thermal environment of the satellite. - Progress
- In process of creating models.
18Thermal Desktop, Continued
Example of absorbed flux from sun, earths albedo
and IR emittance.
19Materials and Structures
20Structural Requirements
- The satellite must have ability to
- Withstand launch loads
- Provide desired rigidity
- Protect sensitive payload components from extreme
temperatures.
21Material Selection
Currently evaluating two different materials
- Ti6Al4V Titanium alloy VS. Aluminum Alloy(
7075-T651) -
- Although Titanium is 60 heavier than Aluminum,
it is over twice as strong. - Possibility of having titanium based honey comb
exterior joined by a smaller portion of aluminum
interior.
22Weight Comparison
23Honeycomb Layer
- Planned use of Honeycomb design
- Hexagonal Structure
- Uses the least amount of material to create a
lattice of cells within a given volume - Maintains strength
24Preliminary Sandwich Structure
Layered design that takes advantage of each
materials different thermal properties.
25Energy System
26Goal Requirements
- Collect Solar Energy and store it to power the RF
amplifiers - Collect power from 1m2 solar panel.
- Store energy in a medium that can withstand high
drain current. - Energy storage mediums must have a wide operating
temperature range.
27DC to RF Converter Options
- Tube magnetron _at_ 5.8 GHz
- Can output 650W with 65 efficiency
- Heavier than solid state options
- (1.1kg vs .6g)
- Produces more heat than solid state converters
- Requires a high voltage power supply
- to excite the electrons.
- GaN HEMT solid state converters _at_ 5.8 GHz
- Fujitsu converter can output 320W theoretically
- Cree converter can output 35W, commercially
- available now.
- Lightweight (.6 g) and extremely small size
- relative to the magnetron.
28Energy Storage Li-ion
- For storing energy from the photovoltaic cells
Li-ion and Li-S batteries are being considered. - Li-ion batteries have an energy density of 110
Wh/kg. - Saft MPS space series batteries that are already
thermally insulated and autonomously heated. - Have a wide operating temperature range ( -5o F
to 140o F for charging and -40o F to 140o F in
operation) - Built in over current and charging circuits into
the module. - 17 Ah capacity per battery _at_ 28V.
29Energy Storage - Continued
- Lithium sulphur batteries are being considered
for their higher energy density (350 Wh/kg vs the
110Wh/kg for Li-Ion) - Experimental, expensive technology.
- No history of satellite use.
- Ultracapacitors
- High energy density capacitor used for powering
the Solid state microwave converters when
transmitting a signal. - Ultracapacitors can handle 20A continuous
current. - Will be used in conjunction with the Li-ion
batteries to power the GaN HEMT amplifiers at
their maximum capacity
30Current Concept
- Maximum Power Point Tracker monitors the voltage
and current of the Solar Panel and tracks the
peak point on the power curve. - Battery Management System tracks the charge rate,
voltage and current.
31Antenna and Retrodirective Control
32Retrodirective Beam Control
- The implementation of retrodirective beam control
is critical to accurate beam pointing, as well as
the overall safety of the system. - The key objective is to have the power beam of
the solar power satellites transmitter pointed
only in the direction of a received pilot beam,
which provides a phase reference - Retrodirective beam control ensures that
microwave power transmission is both safe and
insusceptible to accidental misalignment.
33Proposed Retrodirectivity Method
- The 2.9 GHz incoming pilot signal is received at
a Frequency of ?1 and Phase f1 - To conjugate, the received signal is next mixed
with a reference source of Frequency 2?1 and
Phase fref - The conjugated signal is then mixed itself to
produce a signal with Frequency 2?1 and Phase
-2f1 - After conjugated and doubled, the signal is
transmitted from a different transmitting
subarray - The complete phased array transmits a 5.8GHz beam
in the direction of the incoming pilot signal
34Proposed Phased Array Antenna Concept
- Linear Microstrip Patch Phased Array Antenna
- The Microstrip Patch Antenna will operate at a
Frequency of 5.8 GHz, and will have an Input
Impedance of 50? - The Antennas design features a 4x4 Phased Array
consisting of 15 Transmitting Elements and 1
nested Receiving Element each spaced 0.5? apart - The 4 subarrays are expected to be at different
phases prior to power transmission
5.8 GHz 4x4 Linear Microstrip Patch Phased Array
with nested 2.9 GHz Receiving Element
35Antenna and Transmitter Interface
- Solid-State
- Facilitates electronic beam steering
- Power amplifier and phase shifter are placed
behind each transmitting element - Microwave filters are required to countervail
amplifier-spawned noise
- Magnetron
- RF power is split to feed fed to each antenna
subarray - Negligible power loss may occur during energy
feed - Loss expected from phase shifter
36Advantages of Proposals
- Microstrip Patch Antenna
- Advantages
- Low cost to manufacture
- Light weight and low profile
- Supports both Linear and Circular Polarization
-
-
- Retrodirectivity Method
- Advantages
- Conjugates pilot signal directly at RF
- Reduction in the number of electronics per
antenna subarray - Less power consumption