HybridUAV

Hybrid Powertrain UAV and Future
Solar System Industrialization and
Infrastructure Development Techniques
MatthewGirard

1 CONTENTS
2 Abstract 4
3 Complex Potential Functions 5
1. Two Dimensional Electrostatics 5
Example 1: Two Infinite Coaxial Cylinders Example 6
4 Electric Machines 7
5 Propeller Theory 12
6 Power Electronics 21
7 Hybrid Powertrain Development 28
1. Series Type Hybrid Electric Aerospace Vehicle Powertrain 31
2. Parallel Type Hybrid Electric Aerospace Vehicle Powertrain 32
3. Powersplit Type Hybrid Aerospace Vehicle Powertrain 33
4. Introduction: 34
5. PMSM Control Schematics 34
6. Code: 37
7. PMSM Control Scope Waveforms: 38
8. PMSM Control Equations 50
8 Relativistic Electrodynamics and Communication 52
9 Space Industrialization and Colonization 82
1. Space Industrialization Phase One 82
9.1.1
9.1.2
The Moon 82
Mars 83
9.2 Space Industrialization Phase Two 84
9.2.1 Venus 84
10 Space Transmission Lines 85
10.1 Space Lensing 85
10.1.1
10.1.2
Space Lensing Phase 1 85
Space Lensing Phase 2 and Phase 3 90
10.2 Space Gel (Mirror and Diffraction based Electro-Optical Space Transmission Lines) 91
11 Navigation and Control 94
12 Novel Semiconductor Layering Technique for Photovoltaic Energy 94
12.1 Introduction 95
13 Quantum Heat Engines and Refrigerators 98

2 ABSTRACT
In the 15th Century, Cosimo Medici liberally used his immense wealth to enrich the people of
Florence and patronage the arts. In this period there was little difference between arts and science, and
through acts such as spending fortunes on engineering marvels, the very first Florentine public library,
and funding artists such as Donatello he was able to endure a lasting legacy of being centrally important
to the advent of the Renaissance Age. The Medici’s even played a part in developing the technologies and
techniques to sail across the Atlantic Ocean. It is my opinion, that humankinds next major step is the
colonization and industrialization of the Solar System and that it is going to require a Medici like
investment, but can be quite profitable after an initial infrastructure is developed.
Figure 1: Cosimo Di Medici (Bronzino's Workshop) Creative Common License
What we look for in this paper is the technologies required to exit and re-enter planetary altitudes
with a full plan towards sustainable techniques of progress and development. The technologies we
develop for aerodynamic flight and navigation include Electric Machines, Power Electronics, Jet Stream
and Lift Theory, Airfoil Control Areas, Propulsion, Turbofans, Rocket Theory, Aerospace Satellite
Techniques, Heat Transfer and 3D multi-navigational coordinated path planning.
In order to fly liberally around the solar system an infrastructure which includes the transmission of
power throughout a coordinated path in outer space must be developed. Similar to the idea of
transmission lines, but we can take advantage of photovoltaic power, electromagnetic theory, relativistic
momentum, optics and electro optics in particular to steadily guide our power. We can similarly rely on
some key characteristics of transmission lines, and properties of light itself to maintain and influence
communication even at vast distances.
After the development of power requirements as guided by a system of solar and planetary resource
harvesting as well as begging the question of distribution and redistribution we investigate the idea of
distributing enough power through said infrastructure to propel vehicles to relativistic speeds. This
includes a plan on relativistic electromagnetic radiation frequencies, communication methods, relativistic
Doppler effect, contraction and dilation of fast moving photodetectors and antennas as seen by a
stationary and moving reference point.

3 COMPLEX POTENTIALFUNCTIONS
We begin with a method of transport in which we will define several parameters we need to analyze
our design, and it would ultimately prove valuable to take our concepts into one harmonic complex
domain and map them to their harmonic complex conjugates in order to define boundary conditions for
complex potential functions and use them plentifully in our design taking full advantage of physical
phenomena which is modeled there. To start we will assume you have an understanding of complex
variables, and move quickly from there.
Let’s design a table for the equation
Equation 1: Complex Potential
F(x,y) = Φ(x, y) + j*Ψ(x,y)
Table 1: Complex Potential Functions
Physical Phenomena Φ(x,y) = constant Ψ(x,y) = constant
HeatFlow Isothermals Heat Flow Lines
Electrostatics Equipotential Curves FluxLines
Fluid Flow Equipotentials Streamlines
Gravitational field Equipotentials Lines ofForce
Magnetism Potential Lines ofForce
Diffusion Concentration Lines of Flow
Elasticity StrainFunction StressLines
Current Flow Potential Lines of Flow
3.1 TWO DIMENSIONAL ELECTROSTATICS
A two-dimensional electrostatic field is produced by a system of charged wires, plates, and
cylindrical conductors that are perpendicular to the z plane. We assume the lengths along the z-axis are
effectively infinite from the reference point of the xy-plane. This allows for us to define an electric field
E(x,y) that acts as a force on a unit positive charge placed at the point (x,y). E(x,y) is conservative and is
derivable from the Φ(x,y) complex electrostatic potential as,
Equation 2: Comple Electrostatic Field
E(x,y) = -grad Φ(x,y) = -Φx(x,y) – j*Φy(x,y)
Gauss’s law implies that the line integral of the outward components of E(x,y) taken around any
small rectangle inside our domain D is identically zero. It is shown in my handwritten notes on page (?)
that the value of the line integral is,
-[Φxx(x,y)+Φyy(x,y)]ΔxΔy.
This quantity is zero and thus we can conclusively claim that Φ(x,y) is a harmonic function.
Letting Ψ(x,y) be the harmonic conjugate we define our complex potential (not to be confused with
electrostatic potential) as,
Equation 3: Complex Potential
F(z) = Φ(x,y) + j*Ψ(x,y)

The curves Φ(x,y) = K1 are called equipotential curves, and the curves Ψ(x,y) = K2 are called
the lines of flux. This basically means that a test charge place at any point on an equipotential curve will
feel the same potential, but the charge will travel along the line of flux. Boundary value problems for the
potential function Φ(x,y) are realizations of the Dirichlet problem where the harmonic function is Φ(x,y).
In my handwritten notes on page (?) I develop,
Equation 4: Electric Potential Between Two Parallel Conducting Planes
𝛷(𝑥, 𝑦) = 𝑈1
+
𝑈2 − 𝑈
1 𝑏 −
𝑎
(𝑥 − 𝑎
)
As you can see we find a unique and algebraic way to map and simulate physical systems to decipher in
depth information from. This technique will come up again.
Example 1: Two Infinite Coaxial Cylinders Example
Find the electric potential Φ(x,y) in the region between two infinite coaxial cylinders r
= a and r = b which are kept at the potentials U1 and U2, respectively.
Solution The function w = log z = ln |z| + j arg z maps the annular region between the
circles
r = a and r = b onto the infinite strip ln a < u < ln b in the w plane. The potential
Φ(u,v) in the infinite strip has the boundary values
Φ(ln a, v) = U1 and Φ(ln b, v) = U2, for all v. Using Equation 4 the electric potential
Φ(u,v)is
Equation 5 The Electric Potential in The Region Between Two Infinite Coaxial Cylinders
𝑈2 − 𝑈
1𝛷(𝑢, 𝑣) = 𝑈1 +
ln 𝑏 − ln 𝑎
(𝑢 − ln 𝑎
)
Because u = ln |z|¸we can conclude that the potential Φ(x,y) is,
Equation 6: Equipotentials Φ(x,y) = constant which are Concentril Circles U2 < U1
𝑈2 − 𝑈
1𝛷(𝑥, 𝑦) = 𝑈1 +
ln 𝑏 − ln 𝑎
(ln|𝑧| − ln 𝑎
)
Figure 1 illustrates our electrostatic mapping.

Figure 2: Two Dimensional Electrostatic Mapping from Example 1
4 ELECTRIC MACHINES
Figure 3: Basic Three Phase Synchronous Electric Machine

Figure 4: Drawing from U.S. Patent 381968, illustrating principle of Tesla's alternating current motor. Source:
https://en.wikipedia.org/wiki/AC_motor#Three-phase_AC_synchronous_motors

Figure 5: Permanent Magnet Synchronous Machine Configuration. Source: http://www.microchip.com/design-centers/motor-
control-and-drive/motor-types/pmsm
 With permanent magnets the PMSM can generate torque at zero speed
 Higher torque density versus AC Induction Motors (ACIM), i.e., smaller frame size for same
power
 High efficiency operation
 Requires digitally controlled inverter for operations

Figure 6: Switched Reluctance Machine. Source: http://www.microchip.com/design-centers/motor-control-and-drive/motor-
types/sr
 The stator is similar to a brushless DC motor. However, the rotor consists only of iron laminates
 The iron rotor is attracted to the energized stator pole
 The polarity of the stator pole does not matter
 Torque is produced as a result of the attraction between the electromagnet and the iron rotor
 Switched reluctance motor control is simple to implement but this type of motor is not commonly
available

Figure 7: Various PMSM Configurations.

5 PROPELLER THEORY
Figure 8: Notes on Development of Stream Tubes (Fluid Mechanics for Aerodynamic Thrust)

Figure 9: Development of Bernoulli'sEquation
Figure 10: Analysis of Pressure Flow, Streamtube Elements, and Aerofoil Control Areas

Figure 11: Momentum Equation, Resultant Sidefase Flow Pressures, Drag and Pressure Coefficient
Figure 12: Airflow through Jet Engine and Propulsive Jet Streams

Figure 13: Thrust from Turbofan and Rocket Engine, Propulsion per Jet Stream, Available Power, Propulsive Efficiency,
Temperature, Pressure, Velocity Graph of Turbo Jet (air-intake->compressor->combustion->turbine->exhaust)
Figure 14: Analysis of a Static Turbojet. We see the Thrust Develop Through the Diffuser, Compressor, Combustible Chamber,
Turbine and Exhaust. We define D_ram (ram ~> intake momentum), Discuss Net Thrut and Gross Thrust.

Figure 15: Here we Investigate Several Configurations of Turbofans, By-Pass Ratios, Mixed Exhaust, Dual Flow Benefits
Thermal, Fuel and Propulsive Efficiency While Increasing Costs, and Complexity.

Figure 16: Development of Flight Mechanics, Wing Area Generalized to L2, Wing Vortex Area Generalized from Circle Area to
L2, Hovering vs Flight Chart detailing Deflection Area, Downward Air Momentum Density, Flow Speed, Downward Momentum
Flux, Etc.

Figure 17: Development of Flight Velocity Hyperbolic Optimization, Drag vs Flight Coefficient for Optimum Force and Enerrgy
Consumption.

Figure 18: Analysis of Power and Fuel Consumption Versus Constant Altitude & Versus Constant Speed, Thrust vs Temperature
vs Fan RPM, Thrust vs Ambient Temperature vs Altitude.

Figure 19: Actuator Disc Theory, Control Area of Propellor Stream Tube, Change in Slipstream Momentum, Static Thrust, Jet
Efficiency, and Jet Power.

6 POWER ELECTRONICS
Figure 20: Charger Scheme using DSP/MicroController. Conventional PFC Boost Converter. To Develop Relativistic Speeds
we run into Power Electronics Problems.

Figure 21: Martian Energy Grid. We See Solar Cell Array go through MPPT to DC Link, Energy is Interchanged Betwen
Spacecraft Charger and Grid, Energy is Transferred Between Space Transmission Lines and Martian Pyramid Colony ( LOL )
andGrid.

Figure 22: Investigation and Equations Surrounding Buck Converter

Figure 23: Investigation of Buck Converter and Characteristic Equations

Figure 24: Investigation of Buck-Boost Converter Characteristics as Well as Bidirectional Switch and Single Phase Inverter

Figure 25: Investigation into Gate Drives. Low-Side Gate Drive Circuit for MOSFET, High-Side Gate Drive Circuit for
MOSFET and IGBT Gate Drive.

Figure 26: Investigation of Fuel Cell and Sun Farming on Mars. This Gives us Propulsive Material, Bi-Directional Energy and
a Starting Point.

7 HYBRID POWERTRAIN DEVELOPMENT
We now develop a hybrid powertrain. So before we begin let’s
reiterate some exchanges of energy that would be beneficial towards the
propulsion of an Aerospace Vehicle. We talked earlier about focused
light, and relativistic momentum. It is well known that light has
momentum, and if you were to turn a flashlight on in space it would
begin to develop a velocity. This is because the photon packets
themselves contain momentum and energy. So for each photon
momentum moving in one direction away from the flashlight we expect
the flashlight similarly to move with an equal momentum opposite to
the direction of the escaping photon. Let’s keep this important natural
science concept in mind as we develop our powertrain allowing for its
inclusion and occlusion depending on emergent technologies.
Figure 27: Photonic Thrusters as envisioned by Young Bae. Source:
https://en.wikipedia.org/wiki/Photonic_laser_thruster
A Series Type Hybrid Aerospace Vehicle is presented figure 4.
In this particular model we are considering a combustible jet engine
with exhaustive jet streams. Here shortly we will consider a more
complex power model based on Electromagnetic Radiative propulsion,
Hydrogen Fuel Cells, Plug-In and known Photovoltaic Techniques.
These control diagrams do not include accessory hook-ups (such as
Antenna’s, Computer Navigation, Control Override, etc.), but we can
make an allowance for that later.
Light Propulsion
Photons, like all particles obey the
relativistic equation:
𝑬 𝟐 = 𝒑 𝟐 ∗ 𝒄 𝟐 + 𝒎 𝟐 ∗ 𝒄 𝟒
A photon has a zero mass, m.
Therefore the momentum of the
photon is given by:
𝑝 = =
𝐸 ℎ
𝑣
𝑐 𝑐Letting v represent the frequency of
the light. Let's suppose we can build
the infrastructure to concentrate
powerful light on a spaceship with a
perfect reflector kept cool through
an internal cooling system. The
number of photons per second is the
total power delivered to the reflector
divided by the energy of a single
photon:
𝑊
𝑛 =
ℎ𝑣
The momentum change per second
is the number of photons multiplied
by the momentum of a single
photon:
𝑠𝑒𝑐 ℎ
𝜈
= ∗ 𝑝 = ∗
=
𝑃 𝑊 𝑊 ℎ𝜈
𝑊 ℎ𝜈 𝑐 𝑐
But the rate of change of momentum
is just the force, so we end up with
an equation for the force created by
your flashlight:
𝑊
𝐹 =
𝑐
The force is proportional to the
flashlight power. Momentum is
conserved because it's the
momentum carried by thephotons
that creates the force.
Now considering Aerospace
propulsion, we recognize 1W of
light creates a force of about 3 ×
10−9 Newtons.

In the Series Configuration the power flows through the entire model allowing for a consistent
power rating across the vehicle. This can be easier to keep track of, program, and ultimately control.
Figure 28: Series Hybrid Aerospace Vehicle Powertrain

Figure 29: Series Hybrid Aerospace Vehicle Powertrain Simulink Model

7.1 SERIES TYPE HYBRID ELECTRIC AEROSPACE VEHICLE POWERTRAIN
In the Series configuration the energy from the torque in a combustible engine is transferred to a
generator, and the exhaust is sent through a compressor and out to a focused jet stream. The generator
outputs energy to an inverter and then a battery for storage. Our battery then begins an (input/output)
relationship with the rest of the powertrain. Both receiving energy and transferring it through another
inverter, receiving electrical energy from a Solar Cell MPPT circuit, receiving/transferring (rx/tx)
electrical energy to the motor/generator, and then receiving/transferring torque derived from the electrical
energy to the transmission, which transfers/receives torque to the turbofan, which delivers a high by-pass
ratio exhaustive jet stream towards the area along the back wings generating lift and thrust.
Figure 30: Simulink Model of a Parallel Aerospace PHEV Powertrain

7.2 PARALLEL TYPE HYBRID ELECTRIC AEROSPACE VEHICLE POWERTRAIN
Figure 31: Parallel Type Aerospace HEV Powertrain

7.3 POWERSPLIT TYPE HYBRID AEROSPACE VEHICLE POWERTRAIN
Figure 32: Powersplit Type Hybrid Aerospace Vehicle Powertrain

7.4 INTRODUCTION:
Running the given parameter Matlab file the control system PMSM_InVC_v07_data.m and
Simulink file PMSM_InVC_v07_data.m as a starting point. The constants, wiring and PI transformations
were then developed in Simulink. Two separate conversions were run to compare results. One using the
built in Simulink function dq <-> abc transformations and the other using the power invariant direct
quadrature formula described by a 90 degree rotated transformation into the A plane as a frame of
reference.
The scopes were then tuned to deliver quality images and the specimen was run for 1 s. The
Schematics followed by code, and subsequently followed by Results and equations are now presented.
7.5 PMSM CONTROLSCHEMATICS:
Figure 33: Full DQ Control System for PMSM with PWM Inverter

Figure 34 dq to abc transformation subsystem
Figure 35: abc to dq transformation subsystem

Figure 36: PWM Inverter
Figure 37: Changes Made to Compare Results with Simulink ABC to DQ Built-in Function

Figure 38: Changes Made to Compare Results with Simulink DQ to ABC Built-in Function
7.6 CODE:
Figure 39: Matlab Code Designed By Author For ABC to DQ Vector Control System

Figure 40 Matlab Code Designed By Author For ABC to DQ Vector Control System
The code was easy to develop and just ran functions of wt and d & q or a & b & c.
7.7 PMSM CONTROL SCOPEWAVEFORMS:
Figure 41: Waveform For Outgoing abc Phase Currents

Figure 42 Close up of ABC Phase Waveform Currents Investigating Half Second Mark

Figure 43 Idq Current Waveforms Generated

Figure 44: Close up of Idq Current Waveforms

Figure 45: Idq Current Waveforms Generated Using Built in Simulink Functions

Figure 46: Close up of Idq Current Waveforms Generated Using Built in Simulink Functions

Figure 47: Vdq Current Waveforms

Figure 48: Vabc VoltageWaveforms

Figure 49: Close up of Vabc Voltage Waveforms

Figure 50: PWM Voltage Output Pulses from PWMInverter

Figure 51: Close up of Voltage PWM pulses close to 0.5 seconds

Figure 53: Repeating Sequence
7.8 PMSM CONTROLEQUATIONS
The Matlab code above clearly covers the equations I used in producing output. However it is worth
investigating various results.
Figure 54: I used a derived version of this rotational form. However the multiplicative factors were Sqrt[2/3] and u0 was not
used. Source:
https://www.mathworks.com/help/physmod/sps/powersys/ref/abctodq0dq0toabc.html;jsessionid=0e39ec92956b98a8b84660d50b
ac

Figure 55: I used a derived version of this inverse rotational form. However the multiplicative factors was Sqrt[2/3] and
Sqrt[1/2]. ~
https://www.mathworks.com/help/physmod/sps/powersys/ref/abctodq0dq0toabc.html;jsessionid=0e39ec92956b98a8b84660d50b
ac
Figure 56: Sequencing and Generating Pulses From Voltage Control Lines. Soure: Ned Mohan Advanced Electric Drives
Figure 57: Equation used to Define Vd for PWM Inverter

Figure 58: An Abstraction of the Vector Control System. Soure: Ned Mohan Advanced Electric Drives
8 RELATIVISTIC ELECTRODYNAMICS AND COMMUNICATION
Keep in Touch is the best idea here. Once we arrived after having developed the infrastructure
along the way there we can always communicate by sending signals halfway of the way between each
other and bear in mind the speed of light.

Figure 59: Lorentz Transform Refresher, Relationships between Inertial Reference Points, Development of Gamma Constant.
Figure 60: Development of Time Contraction, Light Velocity Vector and Space Time Relationship.

Figure 61: Relativistic Velocity Transformations. Six Equations are used to Represent Stationary Observer and Inertial
Observer
Figure 62: Example Use of Relativistic Velocity Transformations

Figure 63: Applying Relativistic Dynamics to Moving Charge Velocities and Observed Line Charge
Figure 64: Line Charge and The Lorentz Transformation

Figure 65: Development of Minkowski Force and Comparison with Magnetic Field

Figure 66: Development of Relativistic Electrodynamics Utilizing Field of Charge in Motion

9 SPACE INDUSTRIALIZATION AND COLONIZATION
Space Industrialization or more simply put: How to make a return for working towards ushering in
the greatest advancement of humankind, and ensuring a lasting legacy and history for our species. In
order to understand the potential energy abundance and cheap resources available to a well-managed
space infrastructure we first examine our nearest stellar neighbors.
9.1 SPACE INDUSTRIALIZATION PHASE ONE
Phase one starts off with our two closest most hospitable neighbors. A stable steady manufacturing
infrastructure between Earth, Mars and the Moon will not only hasten the development of energy and
resources needed for phase two and three, but proves to be a profitable and attainable first step.
9.1.1 The Moon
The Moon is the closest large space body to the planet Earth, and therefore is worth special initial
consideration. The moon sits a mere 238,900 miles (384,400 km) away, and has a radius of 1,079 miles
(1,737 km). This gives a surface area of 14.6 million square miles (38 million square kilometers), or
about 3 and ½ Canada’s. Figure 5 shows the main chemical components of the moon showing a gracious
amount of iron, silica and aluminum which are 3 crucial industrial elements.
Figure 67: Chemical Composition of the Lunar Surface Regolith (crustal rock derivation). Source:
https://en.wikipedia.org/wiki/Moon
Additionally a study from the Jet Propulsion Laboratory at the California Institute of Technology
suggests that the water (which can be developed for sustainable rocket propulsion, farming, drinking, and
daily washing), the Helium-3 (rare element sought for future developments in the energy sector like
nuclear fusion), and plentiful rare earth metals (REMS). Materials such as Helium-3 can be used to
develop more energy in the grid, and (REMS) can be used to fuel the development of future technologies.
We finally note the Moon has an escape velocity of 2.38 km/s, a surface gravity of 0.1654g, and
an atmospheric surface pressure of 10-10 to 10-7 Pa composed of He, Ar, Ne, Na, K, H, and Rn.

9.1.2 Mars
Is another equally important beginning to a solar system technological Renaissance. It is the closest
full planet at an average of 140 million miles away (225 million km), and at its closest 35 million miles
away (56 million km). It has a mean radius of 3,389 km, and surface area of 144,800 km2 about 30% of
earths. This gives a lower surface gravity of 0.376 g, and an escape velocity of 5.027 km/s. The surface
pressure is 0.00628 atm (0.636 kPa) on average, and its atmosphere is composed of mostly carbon dioxide
with argon, nitrogen, oxygen and carbon monoxide.
Besides having two small moons which may have energy and technological resources. There is
strong evidence to believe that Mars hosts a variety of ores. Development of volcanic resources on earth
are also beneficial on Mars with its terrains abundant supply of their features. On Mars, magma can be
used for heating purposes, and during the cooling process heavier elements such as copper, chromium,
iron and nickel concentrate on the bottom. Incompatible elemental deposits also form in abundance and
include niobium (superconductors, specialty steels), lanthanum, neodymium, and europium (useful for
electro-optics and energy efficient LED bulbs). Gaseous deposits from very hot magma chambers can
mix with water and sulfur in aqueous solutions producing rich mineral veins. These often include gold,
silver, lead, mercury, zinc, and tungsten.
Figure 68: Lava Flow, as seen by THEMIS. The shape of the edges indicate a magma flow. Source:
https://en.wikipedia.org/wiki/Ore_resources_on_Mars

Figure 69: Lower Volcano is Ceraunius Tholus and upper volcano is Uranius Tholus as seen by Mars Global Surveyors Orbiter
Camera. Ceraunius Tholus is about as high as Earth's Mount Everest. Source:
https://en.wikipedia.org/wiki/Ore_resources_on_Mars
9.2 SPACE INDUSTRIALIZATION PHASE TWO
In phase two of the development of our Solar System’s resources we begin to develop further more
environmentally hostile stellar bodies in the direction of the Sun. It is safe to assume at the completion of
Phase Two the future of humanity is significantly safer than it is now. This portion of development
includes establishing an infrastructure on Venus, Mercury and around the Corona of the Sun. It is clear
that the development of nuclear technologies harvested from the Moon, the plentiful resources found on
Mars, and well developed space circuits serve as catalysts for the completion of this part of the plan.
9.2.1 Venus
Venus is our second nearestneighbor

10 SPACE TRANSMISSION LINES
The transmission of power through space is of utmost importance for the future society which makes
use of the vast riches contained in our Solar System’s resources. The greatest power resource is our sun
which release on the order of 1026 Watts of Electromagnetic Radiation. This is about 6.3 x 107 W/m2 on the
surface of the sun, but we are unable to get this close with present materials unfortunately. They will burn
up, and the components likely would melt just moving through the Sun’s Corona. The Sun’s Corona and
the solar winds reach temperatures of up to 20,000,000 K, and extend well above the surface to about 12
times the Solar Radius. This is roughly 5 million miles (8 million km) from the surface. However we
can deduce that since intensity depends on the inverted square of radius, or 𝐼 ∝ 1
, and the power𝑟 2
received by Mercury being in the range of [14446, 6272] kW/m2 , we can multiply the ratio of the average
distance of Sun to Mercury and Sun to Corona’s Edge by the average minimum intensity of light received
on Mercury’s surface to find a good approximation of the lights power just outside of the Corona’s Edge.
(
𝐷𝑐 𝑜 𝑟 𝑜𝑛 𝑎→𝑠𝑢
𝑛
𝐷 𝑚 𝑒𝑟 𝑐 𝑢 𝑟 𝑦→𝑠𝑢 𝑛
2
(36 ∗ 109 𝑚
)2
(5 ∗ 109 𝑚
)2
) ~ ~49
𝑊
𝑚2
49 ∗ [14446, 6272] = [707000,307328]
𝑊
𝑚2
Or we can divide the intensity of power at the Sun’s surface by 12^2 or 12 radii to the second power
to receive a similar assessment,
6.3∗107 𝑊
122 𝑚2
𝑚2
= 437500 𝑊
. This is approximately 350 times the power
received per square meter on the planet earth. Similarly being so close to the sun, heat generators can also
easily be conceived, and with them the generation of laser or Gaussian beams. The power hungriness of
our current technologies in lasers and generating well collimated light on Earth would make the idea of
transfer of power via this method a losing venture, but with the amount of power generated near the Sun
and the vastness of the outer reaches of space this idea deserves strong consideration. Though we can
consistently develop power sources, factories and power transmission systems traditionally on a planet
like Mars or Earth. These power system models obviously need manipulation in order to be viable for
harvesting resources from gaseous planets (Jupiter, Saturn, Venus, Neptune, Uranus), Mercury and within
the Sun’s inner atmospheres. Optics and Electromagnetics are well-established (scientifically verified)
sciences which benefit our lives daily. Let’s attempt to work within the constraints of current technology,
and as technologies increase these concepts of interplanetary power transmission will ultimately be
improved.
10.1 SPACE LENSING
Space Lensing of well collimated light seems a sensible approach to this problem. This is because
light can be concentrated into extremely high-power Gaussian beams which can be directed and
controlled through Electromagnetic and Optical Engineering techniques. Let’s investigate how space
lensing could be used in our three phases.
10.1.1 Space Lensing Phase 1
During the industrialization and colonization of Mars and the Moon we could theoretically transfer
power at a loss from Earth to the aforementioned bodies. This might not be cost effective at this stage,
but it surely improves the needed infrastructure for phase 2 and phase 3. The Mars, Moon, and Earth
throughout the first two phases of the plan described above for space industrialization are by far the most

hospitable planetary bodies, and likely to remain the home of the majority human population until
approximately the end of the third phase I described. The power and resources brought from developing
towards the Sun are most easily delivered to the human colonies via a system of space lensing, and the
infrastructure to deliver the power from areas closer to the Sun to the surface of the colonies can be kept
in mind and developed during this stage. The transmission of power from space to Earth’s grid is a tricky
problem, but two ideas may include either the development of lensing vehicles or a lensing tower. For
instance consider the designs shown in Figures 8 to 13.
Figure 70: Lens Tower Receiving Light Beam From Above
10.1.1.1 Len’sTowers
In Figure 8 we see a lens attached to four poles. If at the points where our pole meets our lens
we develop a connection to absorb
some of the electromagnetic power we
can begin harvesting our energy well
ahead of our final lens before sinking
the power. That is we can do several
things here. Firstly, we can collimate
the light downwards from our space
source, and we can line our poles and
our lens with efficient photovoltaics
perhaps allowing our beams to
maintain our power electronics. This
collects light energy from the
structure, and allows us to control
power flow both through lens and
throughout its structure. This opensFigure 71: Lens, Mirror and Internal Reflection Light Guiding System

possibilities for plug-in chargers high above sea level, allowing grid-to-Aerovehicle charging and
Aerovehicle-to-grid redistribution.
Light Guides are often in the shape of lens, mirrors and total internal reflection as seen in Figure
9. It can be shown that a transfer matrix exists representing the metric changes to an input light rays
angle and position from a periodic array of lens. The Matrix Relation shown in Equation 7 represents a
periodic system of lenses with lens parameters described by A, B, C, and D.
Equation 7: Ray Output Position and Angle from an Input Light Ray Position and Angle into Periodic System of Lenses.
It can similarly be shown that in order for our path to remain harmonic (or to stably guide path from one
end of the system of the lenses to the other) the relation shown in Equation 8 must hold.
Equation 8: Condition for Stable Light Trajectory through System of Lenses
Figure 10 shows a hypothetical Lens Tower guiding a light beam from one lens to another. We
can imagine a level of wiring running down the poles allowing for PEHV to plug in and charge. This
allows for repair vehicles to scale the pulls and to charge, and for aerospace PEHV to plug in and charge.
We can also collaborate with PEHV aerospace and traction vehicles to harvest additional power, correct
complex light phases for maximum power deliverance, and create a system of transporting traditional
planetary resources (Hydrogen, Oxygen, Alloys, Minerals, Water, Lens Building Material, Computers,
Fuel Cells, Solar Cells,
Replacement Parts,
etc.) from one
planetary body to
another. We can also
imagine perhaps fields
of these lens towers
delivering high voltage
power to and from a
planet.
Figure 72: LensTower
Sending Concentrated
Light from One Lens to
Another

10.1.1.2 Hovering Lensing PHEV for Space Power Transmission
Figure 11 shows what could potentially aid in planet to space light power transmission. In the
figure I feature a multi-lens array which perhaps hovers and guides high voltage electromagnetic
radiation. Though one big lens could perhaps guide power more efficiently on this vehicle we maintain
several lenses to perhaps focus beams in a parabolic manner towards a lower PHEV (plugin hybrid
electric vehicle) Power Receiver/Transmitter, Stationary Power Conversion Hub, Lens Tower or any
combination of the three. I imagine the grid-(to/from)-vehicle charger from the lens tower or a lower
power charging station.
Figure 73: Hover Lens Used to Transmit Power from Space to Planetary Surface
Figures 12 through 14 show a basic PHEV hover lens scheme. In this vehicle we use 6 separate
turbofan engines to generate lift through jet streams preferably of the air and water variety. In the Earth’s
atmosphere we can rely mostly on air molecules with a strong enough propeller to air compressor
turbofan system connected to transmissions and torqued through electric machines. If enough power is
communicating between lenses we imagine that losses from producing electricity for the turbofans is
similar to losses of electricity in civil planetary Power Processing Plants such as lighting for workers,
transportation, infrastructure repair vehicles and all the various costs going into maintaining a working
Power Plant. Of course we wrap our vehicle up with the appropriate band gap solar cell, and allow the
intensely focused light to power our turbofans. We also consider hydrogen fuel cells, and especially for
low atmosphere planets. On gaseous planets we may make tradeoffs between received lensing power, and
on board gaseous chemical energy conversion (Venus has an atmosphere nearly 90 times denser than the
Earth’s atmosphere allowing for the propulsion of gas molecules, and thus providing momentum for lift).

Figure 74: Side View of Hover Lens Plug-In Electric Hybrid Vehicle Detailing Turbofans Which Intake Air Molecules from
Above compresses them and Exhaust Jet Streams Below
Figure 75: Upper View of Hover Lens Plug-In Hybrid Electric Vehicle Detailing a Photovoltaic Surface Powering the Turbofans
through the Well Collimated Light Received from Solar System Infrastructure

Figure 76: A Clearer Side view Render of a Hovering Lensing Plug-In Hybrid Electric Vehicle Illustrating Titanium Turbofans
and Solar Cell Surface
10.1.2 Space Lensing Phase 2 and Phase 3
Phase Two of space lensing involves guiding from Venus, Mercury and the Sun. It is easy to
perceive building orbital lensing satellites which directed our power along well-collimated beams towards
destination control, repair and power hubs. We can investigate various properties of the solar system, and
develop an idea of the numbers we would want to work with. Suppose assembly-lines on Earth were
developed in the manner of modern car factories for the express purpose of building PHEV Aerospace
Vehicle Developers. The equivalent of future tractors (considering the thrust delivered from modern day
turbojet and the work considered here for high by-pass ratio electric machine driven turbofans) will with
the continuance of humankind eventually deliver tractors to the moon. Infrastructure will provide cost
beneficial ways of providing this service, and being at the forefront of the Space Age is perhaps the
pinnacle story in our collective people’s history. Colonization and tourism certainly provide long-term
interests. Service providers after initial infrastructure builds will see returns in transportation,
import/export, power delivery, service economics, rent/sales of developed plots, high speed data transfer,
communication, shipping and more.
The Auto Industry builds approximately 165,000 new passenger cars per year. If we only
included vehicle manufacturing costs and 5,000 aerospace PHEV were produced per year, for the express
purpose of delivering power from the sun, at a cost of 10000 per vehicle a year gives a total cost of
$50,000,000. Let’s say these vehicles were developed for the express purpose of building, maintaining,
and delivering lensing arrays to orbit the Sun and build circuits from space resource interests towards
Space Bases, Earth and Planetary Colonies. If we sought a spiral trajectory inwards (we will discuss in
navigation) we would be able to deliver concentrated light and power before reaching the Sun. As
discussed above the closer the distance to the Sun the more power delivered. Figure 15 details arrays of
light power transmission lenses orbiting the sun (not to scale of course).

Figure 77: SolarHarvesters
10.2 SPACE GEL (MIRROR AND DIFFRACTION BASED ELECTRO-OPTICAL SPACE
TRANSMISSION LINES)

Figure 78: Solar System Fact Sheet
11 NAVIGATION AND CONTROL
This is under construction (finished in couple days) but necessary for building space transmission lines
and propelling vehicles to relativistic speeds. The Light Trolley idea of propulsions, and zig zagging in
gravitational potential well for deceleration.
12 NOVEL SEMICONDUCTOR LAYERING TECHNIQUE FOR
PHOTOVOLTAIC ENERGY
In order to power our vehicles and considering the alteration of received light intensities we
consider a cheap method of layering photovoltaic layers in a manner to modulate the statistical frequency
with which the electrons are received, generating a tapering effect. Given two connections along the
length of our layered Solar Cell we can use DSP techniques in order to maximize solar harvesting power
intake.

12.1 INTRODUCTION
Figure 1: Theoretical Spatially Modulated Solar Cell. (Top) From left to right ohmic contact, q+ electron capture
layer, q electron capture layer, 5 periods of Semiconductor A and Semiconductor B in this order M = { [0.5*A,0.5*B],
[0.6*A,0.4*B], [0.7*A,0.3*B], [0.8*A,0.2*B], [0.9*A,0.1*B]}, and a window layer. (Bottom) View of periodic structure
with high band gap (orange) SA on left side of each slab and the low band gap (blue) SB on the readers right.
Shown in Figure 1 we have a potential Spatially Modulated Superlattice Solar Cell (SMSSC)
design. The SMSSC’s defining characteristic is the periodic distribution of Semiconductor A

(SA) and Semiconductor B (SB) where in this instance the distribution =[0.5*SA,0.5*SB],
= [0.7*SA,0.3*SB], = [0.8*SA,0.2*SB], and finally ==[0.6*SA,0.4*SB],
[0.9*SA,0.1*SB]
is used.
Figure 2: Fig.27 is borrowed from Sze ~ The Physics of Semiconductors pg. 125

Figure 3: Fig.28 is borrowed from Sze ~ The Physics of Semiconductors pg. 128
Hetereojunctions can be classified as Anisotype n-p and p-n hetereojunctions or as Isotype n-
n and p-p heterojunctions. Also upon inspection we see where the isotype big band gap to
small band gap juncture meet they bend opposite to the anisotype juncture. So for instance
two possible band gaps could be imagined as shown in Figure 4 and Figure 5 where the top
band gap diagram shows an nn isotype heterojunction repeating structure with equal lengths,
and the bottom band gap diagram reflects an nn isotype heterojunction repeating structure
with a slowly decreasing SCA width and a slowly increasing SCB width.
Figure 3: A repetitive isotype nn heterojuncture between a semiconductor with a large band gap and a semiconductor
with a small band gap
Figure 3: A repetitive isotype nn heterojuncture between a semiconductor with a large band gap and a semiconductor
with a small band gap where the width of the first semiconductor is decreasing and the width of the second is
increasing
[Spherical Purpose and Derivation Here]
TermStart.n
b 5

Figure 79: Parabolic Harvesting Technique
13 QUANTUM HEAT ENGINES AND REFRIGERATORS
The quantum heat engine generates power from the heat transfer between a hot and cold reservoir.
The engine can be described by readily through the laws of quantum mechanics. The idea for the
quantum engine was developed at Bell Telephone Laboratories in Murray Hill New Jersey during the late
1950’s by Scovil and Schulz-Dubois [1]. They showed a connection between the efficiency of the Carnot
engine and the 3-level maser. Quantum Refrigerators are designed similar to the heat engines except with
the purpose of spending power in order to pump heat from a cold to a hot bath. Quantum Refrigeration
most currently has found purpose in optical pumping or laser cooling. Heat Engines and Refrigerators may
operate on the scale of a single particle, and therefore justify the need for a quantum thermodynamic
technique.

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