This document provides a plan for establishing a human settlement on Mars called PHAME. It proposes sending crews of 4 astronauts every 2 years for a total of 24 settlers over 6 missions. Crews will travel in a modular Mars-Earth Transfer Spacecraft assembled in orbit. The settlement will be located in Hellas Planitia, Mars, which evidence suggests may be suitable for water and offers shelter. It outlines logistics for surface transportation using rovers and drones. A communication network called MAPIN will connect the settlers using telescoping towers, drones, balloons, and rovers to relay data through orbiting satellites back to Earth. The plan focuses on achieving sustainability through utilizing local resources and renewable energy.

1. Drexel University
P.H.A.M.E.
Planitia-Hellas Human Advanced Martian Environment
Institution: Drexel University
Faculty Advisor: Dr. Ajmal Yousuff
RASC-AL Team:
Senior: Tirthak Saha
Junior/Pre-Junior: Amanda Ireland, Rishiraj Mathur, Nidhi Kumar
Sophomore: Ronnie Joshi, Matthew Meisberger, Dipika Sharma, Chaitali Vyas,
Frederick Wachter, Matthew Wiese
Freshman: Kat Johnston

2. TABLE OF CONTENTS
1. Introduction
2. Logistics
2.1. Mission Timeline
2.2. Mars-Earth Transfer Spacecraft
2.2.1. Crew Rotations/ Initial Missions
2.2.2. ISRU
2.2.3. Martian Surface Logistics
2.3. Location
2.4. Communication
3. Living Spaces
3.1. The Habitat
3.2. Quality of Life
3.2.1. Crew Physical Health and Exercise Regime
3.2.2. Crew Mental Health
3.2.3. Animals and Plant Species
3.3. Medical Arrangements
3.3.1. Decompression Sickness
3.3.2. Muscular Atrophy and Bone Loss
3.3.3. Deep Space Surgery
4. Energy
4.1. Energy Generation
4.1.1. Assessment of Energy Needs
4.1.2. Planning
4.1.3. Solar Energy Utilization
4.1.4. Wind Energy Utilization
4.2. Energy Storage
4.2.1. Compressed Air Energy Storage
4.2.2. Electrochemical Flow Capacitor
4.2.3. Flywheel
5. Resources and Tools
5.1. Automation in Space
5.1.1. MAPIN
5.1.2. Human Assisting Technology
5.2. In-Situ Resource Utilization
5.2.1. Martian Regolith Acquisition
5.2.2. Water Extraction
5.2.3. Iron Ore Extraction
5.2.4. Metal Processing
5.2.5. METS Fuel Production
5.2.6. Presence of Perchlorate
5.3. Plant Growth
5.3.1. Botanical Chamber
5.3.2. Hydroponics
6. Emergency Situations
7. Budget
8. Appendix
9. References

3. 1. INTRODUCTION
Motivation to explore and research a new location depends on how much has been recognized and how much
has yet to be discovered. As Buzz Aldrin rightly put it, “Mars is there, waiting to be reached.” Mars has managed to
capture the attention of researchers, engineers, and people from other walks of life, from all parts of the world due to its
unique characteristics which is why it is called a habitable planet. Although the planet provides an unfriendly and
desolate environment, countless spacecraft missions have wandered its soil to gather more information. Whether to
advance scientific research or to explore extraterrestrial life, the Red Planet captures interests from all of mankind.
This paper describes project Planitia-Hellas Human Advance Martian Environment (PHAME) which intends
to support a settlement of 24 dwellers and achieve sustainability by the 40th year of its existence. This paper follows
through the travel to Mars, the construction of habitat, and the fabrication of strong network communication. To meet
the energy requirements, PHAME makes use of Solar and Wind energy harnessing technologies. Giving importance to
the health and safety of the crew, the mission includes many precautions for effects such as the Bends and provides
ways to perform surgeries in times of necessity. This paper also shines light upon reaping benefits from the regolith
itself by mining and processing, along with procedures to follow during an emergency. All in all, PHAME provides a
comprehensive plan for humans to finally colonize Mars.
2. LOGISTICS
2.1 Timeline
Please refer to Appendix A, Figure 9.
2.2 Mars-Earth Transfer Spacecraft
Driving right into the backbone of the mission, we can realize that one of the most intricate aspects of any Mars
mission architecture is its logistics. The six months journey to and from Mars as well as the required planetary
alignment adds significant cost, risk, and time to the mission. The key problems presented by long-duration missions to
and from Mars include, limited payload, transportation to and from Mars, extreme isolation from Earth, and significant
logistical risk. The solution to these key issues is a sound and efficient logistical plan in which humans, resources, and
other mission critical items will be safely transported to and from Mars. The Mars-Earth Transfer Spacecraft or METS
was determined to be the best option to reduce the issues of cost and risk. One of the main advantages of METS over
traditional spacecraft designs is that it will be assembled in Low-Earth Orbit (LEO). METS will be modular, much like
the International Space Station, which adds flexibility as each vehicle can be customized depending on the mission
specific payload. There are three main modules that will make up a METS: the Inflatable Habitation Module, the
Lander Module and the Propulsion Module, attached to the Orion Multi Purpose Crew Vehicle.
The Habitation module will provide the main living quarters for the astronauts on their journey to Mars. The
effective useable volume to weight ratio is significantly increased since the habitation module is inflatable. This
compares well to traditional tin can designs that are used on the International Space Station. The Lander Module,
henceforth referred to as the Crew Transfer Vehicle (CTV), will enable astronauts and payloads to land on the surface
of Mars. The CTV will utilize a Methane and Liquid Oxygen (LOX) propulsion system that will be capable of a
complete entry, descent, and landing from Low Martian Orbit (LMO) to the surface. A Methane LOX propulsion
system is used as it will enable the use of In-situ resource utilization (ISRU) for surface refueling, which is discussed
further in the section. The propulsion will comprise of a cryogenic propulsion system utilizing liquid H2 and liquid O2
to propel the METS vehicle on its six month journey from LEO to LMO, and will also be capable of returning the
vehicle back to LEO, once the specific mission or crew rotation is complete. The Orion MPCV will serve as the ferry
for astronauts to and from the surface of Earth. It should be noted that during a flight to Mars, the Orion provides
redundancy for the life support systems on the METS by providing additional storage for supplies and by serving as a
lifeboat in extreme circumstances. Each of these modules can be launched into LEO by existing Evolved Expendable
Launch Vehicles (EELVs) such as SpaceX‟s Falcon Heavy, NASA‟s Space Launch System (SLS), or any capable
launch vehicles that might be developed during the mission's timeline.
Crew Rotations / Initial Missions: Prior to any humans setting foot on Mars, several robotic missions will take
place in order to test the crucial functionalities critical to the mission. The initial mission to Mars will consist of a
simplified version of the METS spacecraft. Although no humans will be on board, the payload of METS will consist of
the first inflatable habitat, a scout rover, and a construction rover. Once METS reaches LMO, the scout rover will land
on the surface and collect geographical and soil data regarding the landing zone. The purpose of this initial mission is
to validate the compatibility of Hellas Planitia with the mission. The rover will analyze soil composition and look for
signs of water in any form, while also monitoring atmospheric conditions and locating an ideal location for the initial
habitat. This comprises of the Pathfinder Mission, which is to be completed before the first habitat is deployed. Once
an ideal location is found, the Crew Transfer Lander (CTL) will transfer the initial habitat and the construction rover

4. from the METS to the surface of Mars. The construction rover will then be deployed to cover the inflated habitat, as
will be mentioned in further detail in the Living Spaces section.
Due to the biennial Earth - Mars planetary alignment, it was decided that it is necessary to group several
missions together in order to avoid significantly extending the mission timeline. Once all systems are checked out, the
first of many colonists will embark on their journey to Mars. The first crew of four astronauts will launch two years
after the Pathfinder Mission, described earlier. Subsequently, crew transfers will occur every two years, due to which
the population will experience a steady increase from 4 to 24 dwellers over the course of 6 crew transfers. Table 1
below shows the basic schedule for the proposed mission to Mars.
Martian Surface Logistics: In addition to in-space logistics, the movement of humans presents another logistical
problem. Large-scale, human operated rovers will augment the colony, providing astronauts the ability to cover large
amounts of area, surrounding the colony. The rovers will, most importantly, be extremely lightweight and modular,
allowing the most volume and mass efficient means of transportation. They will also be equipped with hybrid power
systems to best deal with the Martian atmosphere. With a combination of a solar electric power system (detailed in the
Energy section) and Radioisotope Thermoelectric Generator (RTGs) the rovers will be able to tackle the most extreme
Martian dust storms.
Although the Martian atmosphere is only about 1% as thick as Earth‟s atmosphere, it is still possible to fly with
extremely lightweight vehicles. Robotic flying vehicles will greatly increase the range of Martian surface that can be
studied in detail compared to traditional rovers. These probes will serve several important roles in aiding human
exploration, such as mapping out hazardous terrain and spotting targets of interest or scientific value. Several vehicle
designs have been proposed by NASA such as a lightweight co-axial helicopter and the autonomous airplane ARES
(Aerial Regional - Scale Environment Surveyor) that validate the technology and its capabilities.
2.3 Location
PHAME will situate within the Hellas Quadrangle in the lower hemisphere of Mars which constitutes the impact
crater, Hellas Basin, and the plains, knows as Hellas Planitia. “Hellas Planitia, is located in the southern highlands
region of Mars” [1]. It is a roughly elliptic impact crater about 3000 km long by 1500 km wide. The topography of this
broad crater slopes down from an average highland altitude of about 2 km above the Martian reference radius (3394.2
km) to an average depth of about 6 km. [2]. “In the deepest parts of the basin, the atmospheric pressure is about 89%
higher than at the surface, which may even offer conditions suitable for water. The Mars Reconnaissance Orbiter
provides strong evidence that the Lobate Debris Aprons, or the geological features, in Hellas Planitia and mid-northern
latitudes are glaciers that are covered with a thin layer of rocks. Pure water ice makes up the bulk of the formation” [3]
“Even though Hellas is considered to be a relatively well preserved basin, especially when compared with some of the
other large basins such as Utopia, there is abundant evidence of fluvial, volcanic, tectonic and aeolian modification
within the basin rim region” [1]. This leads to abundant rich opportunities for sample return to gain data about Mars‟
inner core and history.
2.4 Communication and Automation
Communication with the spacecraft during its travel to Mars will be done through the Deep Space Network
(DSN). The DSN gives the ability for the navigation engineers to gather data in respect to the spacecraft‟s speed using
Doppler data, distance using ranging, and location in space using delta DOR [4].
Upon arrival to Mars, base camp will be the central communication hub for the MArs PIoneering Network
(MAPIN). This hub will be able to receive, transmit and store data while also determining all data transfer scheduling.
It will be able to keep track of all information systems that will be present on Mars. All operations and data generated
will give engineers and scientists back at home, a detailed description of all important data from Mars. This hub will be
able to communicate directly with Earth, if needed, for an emergency situation, but the main communication will be
done by relaying signals through the 2001 Mars Odyssey spacecraft, Mars Express, Mars Orbiter Mission (MOM),
Mars Atmosphere and Volatile Evolution (MAVEN), and PHAME that will continue to orbit around Mars after the
inhabitants have successfully landed on Mars [4].
The MAPIN communication network expands outwards from base camp through a system of nodes. These nodes
include telescoping communication towers, multirotors, solar balloons, and automated land vehicles and will appeal to
astronauts gone out for an EVA or another kind of mission. Refer to Table 2. for the primary and secondary tasks for
each of these communication nodes.
The main communication node that will be used refers to the communication towers. These towers will be
telescoping (as shown in Figure 2) with 5 sections that can extend and retract. This will allow for them to be
transported easier to Mars and will allow for them to retract on Mars for inclement weather. Telescoping

5. communication towers are currently being used by the Army for surveillance and communications purposes [5] and
can be adapted for the Mars environment.
The height of the telescoping communication tower and the local geography has the most impact on the distance
that it can communicate to. The geography around Hellas Planitia is relatively flat as shown in Figure 3, except for the
crater region which is about eight kilometers below the surrounding area. In respect to height, a simple structural
analysis of shear moments was made in order to determine an effective height. One of the largest forces that will act on
a tower is wind. Air pressure on Mars is significantly lower than that on Earth, coming to around 600 Pa and 101,300
Pa respectively [6]. This means there will be significantly less drag on an object that is facing normal to the direction of
the wind.
Other aspects to consider are weather anomalies and safety factors. Various weather anomalies occurring on
Earth relating to high winds were studied in respect to their average and maximum wind speeds. As can be seen from
Table 3, a safety factor of four as a design parameter will be enough to retain structural integrity through all weather
anomalies. Anomalies on Mars would be different than ones on earth, but a safety factor of four was determined to be
efficient since all the data and personnel tracking is dependent on MAPIN. Research on the fastest recorded martian
wind speed, gave conflicting answers of 60 mph [7] and 200 mph [8] from two different sources.. Due to these
conflicting numbers, the safety factor was added on to the fastest wind speeds recorded by the Viking Lander in the
1970s, performing the communication tower calculations with a wind speed of 240 mph (107 m/s) [7]. It was
subsequently determined that the height of the telescoping communication mast should provide a 10 km
communication radius around each mast. In order to achieve this, a mast height of 14.8 meters was calculated. Further
details on the calculations can be seen in Appendix C.
Another structural analysis was performed to determine the maximum force of the wind (240 mph) on the
telescoping communication mast. The maximum shear stress produced by this force is relatively low and the 14.9
meters mast will be able to withstand it. The details of these calculations can be seen in Appendix C.
These communication towers will be placed using up to four automated vehicles. These automated vehicles will
be designed to push the mast to any desired location. The mast will be placed on wheels and will have the ability to
anchor itself to the ground once at the correct location. It will also have solar panels to power the antenna. Automated
vehicles were used to move the telescoping mast so the communication mast can be easily moved, and reduces the
dependency on EVAs to perform service repairs since the communication mast can be transported back to base.
The remaining nodes include the multirotors, solar balloons, and automated land vehicles. The multirotors will
primarily be used for operations that are close to base for use in transportation and relaying communication signals if
astronauts move outside of the range of communication masts. Multirotors can be designed to transport significant
amounts of weight, which will also be aided by the reduced gravity on Mars. Multirotors on Earth are able to carry
loads of up to 10 kg for short periods of time, giving the possibility for multirotors on Mars to be able to carry loads
from 10 kg up to 30 kg with reduced gravity and air density. Solar balloons, on the other hand, will be used for
surveillance of land, weather data collection, and as a temporary communication, if needed be. Finally, automated
vehicles will be used to assist astronauts on missions, used to move the communication towers, and will be design to
have a highly efficient human-machine relationship with the astronauts. This means that they can switch between
autonomous, semi-autonomous, and manual to desire. They will keep data logs of the operations and health of the
astronauts in order to allow for the astronauts to be able to focus more on their tasks. They will be able to be
programmed to meet any specific needs of the astronauts, including but not limited to, being able to follow astronauts
without the need of constant course corrections, be able to transport and feed specific data to the astronauts, and
perform all operations in a way to ensure that the astronaut is never put in harm by the vehicle.
Communication will also be relayed through satellites, but this is not the primary method of communication, due
to the heavy bandwidth and energy requirements to involve 24 astronauts along with vehicles and communication
devices. Satellites will remain in geosynchronous orbit above the base to ensure constant communication for the
astronauts in situations where the communication masts are retracted during weather anomalies.
As mentioned earlier, the geography around the crater in Hellas Planitia is relatively flat. The crater itself is
about eight kilometers below the surface which create a communication problem unless the signals were rerouted
through one of the satellites orbiting Mars. If it is determined that there will be a large amount of EVA‟s and testing in
the crater, a communication tower will be placed at the border to ensure communication is stable throughout the crater.
Another issue is the sandstorms. If these storms are able to reach speeds of 200 mph [8], then this will effectively sand
blast anything that it storm comes in contact with. This means that all of the MAPIN components will need to be
designed to function under such conditions.

6. 3. LIVING SPACES
3.1 Habitat
One of the biggest concerns in sending humans to Mars will be constructing sustainable living quarters, made of
indigenous material, while providing ample radiation protection. Working within these restrictions, PHAME‟s habitat
has led to the implementation of large interconnected igloo-like domes made from hardened Martian soil. This type of
structure requires a small and compact inner-core to provide an airtight and pressurized environment, while the
majority of the structure is made from locally harvested materials.
The process of building one of these habitats is completely autonomous, and is also finished and quality assured
before an astronaut steps inside. Upon landing of the first module, a shipping container sized storage box will deploy
the inner core out of one side and start to inflate with compressed air. This container will also be used for storage of
furniture, equipment and machinery. Once fully inflated, a robot will autonomously make use of the Icy Soil
Acquisition Device (ISAD), the front chamber of which is made to be used as a scoop. The ISAD performs the
function of removing bulk material. The rear chamber contains a high-speed cutting tool, which can penetrate and
acquire harder icy soil. [9] The ISAD is used to remove Martian soil from the surrounding area and deposit the soil
around the perimeter of the inflated habitat. The robot then hardens the soil by applying heat and pressure with on
board machinery, repeating this process until the entire inner-shell is covered with weather and radiation protecting
hardened soil.
The dome shape of the habitat allows for the robot to traverse up and down the structure of the habitat for
deposition of material at the top without falling off. Once the astronauts arrive, they will attach the airlock and other
necessary utilities while the building robot covers the airlock with Martian soil to finish the habitat‟s structure. After
this, construction of the second habitat will begin for the next four crew members to arrive. Finally, each of the new
domes will be attached with another airlock in order to connect them to the other domes. This type of construction will
provide astronauts the capability to move effortlessly from dome to dome without stepping outside, increasing safety
and efficiency.
At full capacity, there will be seven habitat modules interlocked together, six of which will house four crew
members each with the seventh will contain a botanical chamber. As seen in Figure 4, each of the six habitats will
comprise of two levels. The first area is the main working area, which is split into four quadrants for each member to
work that can be reconfigured using inflatable wall-like dividers. The upper level comprises of the sleeping quarters,
incorporating inflatable mattresses for ease of transportation. Once the first crew arrives to the robotically built
structure, they will unpack equipment and furniture from the storage unit, including the second level sleeping quarters
to finish the interior construction.
Humans on Earth have been building dwellings from soil for thousands of years, and the International Space
Station has already proven that technology can provide bare necessities of life outside of our planet‟s atmosphere. The
two main areas that need further research and development to prove this idea to be viable is the robotic building
machines and the thin inflatable shell that will create the seal between a safe haven and the untamed Martian world.
The inflatable shell contains multiple layers, each having their own specific function. The inflatable shell will have to
be thin and flexible in order to be deflated and stored inside the storage container, yet strong and resilient enough to be
leak-proof and protective. Materials used for other inflatable habitats such as the Bigelow Space Habitat was used as a
reference point to form a suitable composition. The outermost layer will feature a thin film made up of multilayered
insulation composed of aluminized kapton and mylar to reflect thermal radiation [10]. Under this film are the multiple
layers of Kevlar-like fabric to protect against dust. The middle layers will serve the purpose of radiation shielding using
a fabric woven from boron nitride nanotubes (BNNTs) saturated with hydrogen. The innermost layer will be composed
of beta cloth, a strong fire-resistant cloth currently widely used for aerospace applications. These four layers will
comprise the inflatable walls of the habitat and will protect the crew from the dangers of the Martian environment.
Since both the shell and robotic technology has not been tested for this kind of scale in such a harsh and remote
environment, a TRL level of 5 will represent the habitat system. The research from other inflatable space habitats show
that it is feasible, but the specific technology still is in need of development.
3.2 Quality of Life
Health and Exercise: The living spaces answer many questions about the quarters and the daily protection from
radiation, but raises questions regarding their general health and well being. In order to assess the potential for healthy
colonizers on Mars, a highly specific diet and exercise is implemented. There exist three macronutrients that human
beings must consume in order to survive: Fat, Protein, and Carbohydrates. Recent studies have suggested that protein
can aid in bone density loss, thus a diet higher in carbohydrates and fats is necessary. The ratio of macronutrients
necessary for survival depends on the gender, body type, height, and weight of the colonizer, but micronutrients such
as vitamin D and Calcium will be necessary, in any case, to maintain the bone density of the colonizers at an

7. appropriate level [11]. Paired with nutrition, exercise is important to maintain the overall health and strength of the
colonizer. NASA is currently utilizing exercising machines in the ISS which combat the difficulty of exercising in a
zero gravity environment [12].
Environment Psychology: In order to maintain a sustainable living environment, a few factors that affect the
quality of life of colonizers need to be taken into consideration. Sleep cycles, temperature, lighting, and decorum
within the habitat have huge impacts on the crew. The dome-like shape of the habitat will certainly amplify noise. In
such a situation, noise cancellation in the sleeping quarters will aid in keeping the colonizers healthy and alert.
Materials such as Acoustic Foam can make this possible. Furthermore, Lensed Indirect Lighting can be used to
substitute natural lighting. Studies conducted by Cornell University show that this type of lighting slows the tiring of
eyes and the loss of focus. Green and blue lights significantly influence emotions, efficiency, and heart rate, creating an
environment that will proactively allow the astronauts to remain calm and centered. Thermal comfort is also an
important factor, and typically environments that are too cold or too warm will result in both unhappiness and a lack of
productivity [13]. Some other issues that astronauts face relate directly to their mental state and their psyche. Without
the earth, one tends to fight the absence instead of yielding to it. This brings about irrational behavior and also the
Earth Out of View phenomenon.
PHAME tackles such repercussions by applying layers of paint to rooms and chambers according to the purpose
they tend to. It creates a specific decorum in the rooms and chambers according to the purpose the rooms tend to. It is
believed that color can affect human emotions and can induce physiological responses. Red stimulates and invigorates
the physical body. It increases circulation, muscular activity, blood pressure, respiration, nervous tension, heart rate,
and hormonal and sexual activity. [14] It stimulates the nervous system, liver, adrenals, and senses in general. In
general, longer wavelength colors (red, orange) are viewed as arousing, whereas shorter wavelength colors (green,
blue) are viewed as calming, and it is thought that longer wavelength colors, relative to shorter wavelength colors,
impair performance on complex tasks [15].
3.3 Medical Arrangements
Building a habitat on planet Mars is a complex and expensive process. Since the plan involves 24 people residing
on Mars for as long as 40 years, it needs to include special measures to counteract the harmful effects of the different
environmental conditions like dust, radiation, hypogravity and, possibly, hazardous microscopic life. The effects on the
human body can be understood in the terms of different systems like the musculoskeletal, the cardiopulmonary,
physiological regulation, etc.
Decompression Sickness: The first and the most frequently encountered problem faced by astronauts is the
Decompression Sickness (DCS) which occurs primarily because the gravity on Mars is reduced by roughly one-third,
as compared to that of the Earth. There have been several studies in the past decade that suggest replacing nitrogen
with helium or neon gases to counter the effects of DCS. [16] Oxygen Prebreathe (PB) is one of the conventional
processes to mitigate the cause of the DCS. PB before decompression, eliminates dissolved nitrogen and therefore
decreases the risk of DCS in astronauts. Factors that affect tissue perfusion, such as position, temperature, and exercise
are known to decrease denitrogenation kinetics during oxygen breathing. Although denitrogenation sessions usually
last 4 hours, much time can be saved by incorporating light exercise. It was found that with two hours of ground level
denitrogenation with light exercise prior to decompression saves subjects from severe DCS as compared to the
conventional 4 hours of denitrogenation. This is so because factors that affect tissue perfusion, such as body position,
temperature and exercise are known to increase denitrogenation kinetics during oxygen breathing. Light exercise
improves blood circulation which in turn quickens the denitrogenation.This was considering a 4 hour simulation of
extravehicular activity at off-nominal pressure modes. In comparison to that, two hours of the conventional oxygen
prebreathing was not enough to protect half that number of test subjects against DCS at emergency pressure level. In
this study, severe bends had occurred after 30 minutes of exposure at this emergency pressure mode. [17] In such a
way, light exercise during PB brings about a drastic time save in the EVA process.
It is possible to develop a non-invasive ultrasonic monitoring device capable of providing an early warning of
impending decompression sickness before any symptoms occur. By monitoring the flow of blood in the pulmonary
artery, one can detect the presence of gas emboli passing through this vessel. Quantification of the number of gas
emboli passing through the pulmonary artery may provide a clear indicator of imminent decompression sickness. Two-
dimensional arrays have been designed and fabricated for use at 5 and 2 MHz with either CW (Continuous Wave) or
pulsed Doppler. Microprocessor-controlled electronics selectively activate portions of the ultrasonic arrays, which have
been tested on human subjects [18].
Muscular Atrophy and Bone Loss: The other problems humans encounter are pertaining musculoskeletal system
are muscular atrophy and bone loss. Findings suggest that very intensive exercises, which impose high loads on the
musculoskeletal system for brief periods, may be more efficient in preserving bone and skeletal muscle conditioning

8. within "safe" limits for longer periods than low intensity activities such as treadmill running and bicycling. Basic
biomedical support of manned space missions to Mars base should include routine assessment of skeletal density,
muscle strength, cardiac output and total energy expenditure. This information can be used to periodically re-evaluate
exercise programs for crew members. Along with that, clodronate, a new diphosphonate effective in preventing
hypercalciuria and negative calcium balance in normal human bed rested subjects, may prove effective in preventing or
lessening skeletal mineral loss in space [19].
Coagulation of Blood: Other physiological functions that hypogravity affects, surprisingly enough, is
coagulation of blood (or clotting). This directly hampers the wound closure and biological tissue reconstruction in
astronauts. However, a study shows that a Nd:YAG laser turned to 1.32 micrometers wavelength when used at low
power levels to obtain deep tissue penetration with low thermal effect achieves cauterization which limits blood flow.
In such known laser systems, high intensity optical energy by one or more lasers is applied in sufficient quantity to sear
or burn the vessels.
Surgery in Space: Everything from a simple cut to, probably, advanced surgeries could be acted upon by a laser
causing thermal heating of the biological tissue proteins such that the collagenous elements of the tissue form a
"biological glue" to seal immediately and/or to reconstruct the tissue being heated. The collagenous glue is absorbed by
the body during the healing process, so it inflicts no potential threat. [20] Although astronauts are screened for health
issues before leaving Earth, astronauts may need surgery in situations of emergency. The ISS has an escape capsule
standing by in case of emergencies, however, in our plans for Mars, this won‟t be an appropriate option. Surgery in
space is expected to be extremely difficult. Bodily fluids like blood will float free and contaminate the cabin due to the
absence in space or lesser gravity on Mars. Medical tools need to be relatively light but capable of handling many kinds
of situations. The fist-sized robot, a product of Virtual Incision in Lincoln, Nebraska, weighs 0.4 kilograms and has two
arms loaded with tools to grab, cauterize, and suture tissue. They can be controlled by humans through a video camera.
The feed relays to a control station, where a human surgeon operates it using joysticks. It slides into the body through
an incision in the belly button. Once the abdominal cavity has been filled with inert gas, the robot can do many things
like removing an ailing appendix, cutting pieces from a diseased colon or repairing a perforated gastric ulcer.
Prototypes have performed several dozen procedures on pigs. The team says their next step is to work in human
cadavers and then test the technology on a living human on Earth. Remote-operated technologies are generally at a
disadvantage in space, because the further away a spaceship gets, the greater the time delay in communications signals.
Virtual Incision will avoid this problem by training astronauts to perform procedures on each other [21].
4. ENERGY
4.1 Energy Generation
Some critical objectives of the initial manned Mars missions are to establish a human habitat, power life support
systems, enable science and exploration activities, and produce propellant. The achievement of these objectives is
dependent on the ability to generate sufficient power to meet the energy needs of the systems and processes involved.
The type and design of a power generating system is interrelated with our specific mission scenario considered.
However, the following three energy needs are assumed for a Mars mission: baseline life support, science/exploration
activities (such as rover operations or drilling), and ascent vehicle propellant production. The relative requirements and
timing of these needs will determine the niche wind energy will fill. As such, the following niches for wind energy
generation in the manned Mars mission planning and implementation are assumed; first off as a secondary power
supply in an all-solar mission to lessen the effects of dust-storm power reductions, and secondly as a cooperative power
supply to enable non-nuclear unmanned precursor mission of extended surface duration. The utility of wind energy
production systems in an all-solar mission would be to allow the reduction of mass (and therefore cost) of the solar
arrays needed to meet dust storm conditions.
Energy Needs for an All-Solar Mission: The scenarios for using solar power are as follows; first as a primary
power supply in an early Martian settlement with rudimentary in-situ construction capabilities, secondly as a mobile
power supply option to enhance and/or enable long-distance rover operations, and finally as stable primary power
resource for a long term settlement plan.
The current estimates of energy needs for an all-solar mission call for an energy budget of 17 kW of continuous
energy during the day and 9 kW of continuous energy during the night for clear conditions [22] as summarized below
in Table 4.
It is noteworthy that the daytime value for clear conditions includes 17 kW of continuous energy during the day
for rover and Field Activities (FA). During dust storm conditions, the daytime utilization needs drop to 16 kW
continuous, as rover operations will be curtailed.

9. The calculations for daily and total energy requirements (assuming no power losses) for the initial outpost are
summarized below Table 5.
However, due to losses during dust-storms (radiation reaching the array may drop to 15% of clear condition
values), an all-solar mission must utilize a solar array eight times larger than needed for the baseline requirements
during clear conditions. Given this requirement, the daily solar power produced during clear conditions should be eight
times the base value provided above.
 Base Energy Requirement per day = 300 kW-hr
 Required Solar Energy Base Value = 8*300 = 2400 kW-hr
Therefore, after combining the two scenarios, i.e. clear and dust storm conditions, mentioned above we are able to get
Table 6.
It should be noted that daily rover operation requirements during a clear 12 hour day equal 12 kW-hr and over
the course of 14000 clear Martian days, the total rover energy requirement is 168 MW-hr. Additionally, Baker and
Zubrin [23] propose that 107 tons of methane/oxygen propellant (for ascent and Earth-return) can be produced on Mars
from 5.7 tons of hydrogen brought from earth and carbon dioxide from Martian atmosphere. The energy needs for this
activity are 370 MW-hr over the 600 day mission. There is expected to be, judging by the numbers derived above,
sufficient excess energy production to meet these needs.
Solar Energy Utilization: The proposed plan is to use compact, deployable solar panels constructed using the
principles of origami folding. This kind of a compact folding mechanism is called Miura Folding, named after Koryo
Miura. Recently, independent student teams at Brigham Young University and Drexel University have both
successfully applied these folding techniques to solar panels used on satellites and CubeSats respectively. These solar
panels have a high stowed-to-deployed volume ratio and Drexel University‟s team has shown that for a particular
design, power generation by origami solar panels is increased by almost 30% over solar panels that have the same
stowed volume. This is due to the higher usable area of the panels once deployed. Research will be performed on
creating the Origami solar panels due to the promising findings of previous research that has been done. These solar
panels will be easier to load and transport since they can be compacted and perform the same or even better results than
conventional solar panels.
Wind Energy Utilization: This paper proposes the use of Vertical Axis Wind Turbines (VAWT) for the
generation of wind energy during the aforementioned dust storm periods. These wind turbines offer a much more
sturdy, flexible and lightweight option than conventional wind energy harnessing technology such as Horizontal Axis
Wind Turbines (HAWT). The disadvantage of the HAWT, however, is that it is generally heavier and it does not
produce well in turbulent winds. This will be an issue on Mars since the winds of the dust storms reach speeds of 60
miles an hour [24]. VAWT are powered by wind coming from all 360 degrees, and even some turbines are powered
when the wind blows from top to bottom. Because of this versatility, vertical axis wind turbines are ideal for
installations where wind conditions are not consistent such as Mars‟ dust storms.
4.2 Energy storage
Presently, the ISS uses lithium and rechargeable Li-ion batteries for energy storage. A problem with these
batteries are that, “primary and rechargeable batteries are heavy, bulky and have limited capability to function in
extreme space environments such as high and low temperatures and radiation”. Also, “safety concerns exist with some
of the primary lithium and rechargeable Li-ion batteries” [25].
Fuel cells use oxygen and hydrogen as fuel to create electricity using stored energy; if the process was run in
reverse, the fuel cells could be used to store electricity as well. The electricity generated from wind or solar can be used
to split water mined on Mars into hydrogen and oxygen in a fuel cell operating in reverse. “The hydrogen can be
stored, and used later in the fuel cell to generate electricity at night or when the wind isn't blowing” [26]. This oxygen
also serves a dual purpose since it can be used for breathing.
Compressed Air Energy Storage (CAES) plants, in fact, work on a similar principle of pumped-hydro power
plants. “But, instead of pumping water from a lower to an upper pond during periods of excess power, in a CAES plant,
ambient air is compressed and stored under pressure in an underground cavern” [27]. Therefore, turbo-compressors can
compress air from the Mars atmosphere and store it underground. Whenever energy is required, the compressed air is
expanded using turbo-expander. The only concern is the energy needed for this procedure. This need can be satisfied if
the thermal energy is stored and released while the air is compressed and used during expansion. This process can
approach 100% efficiency if it were able to have perfect insulation. The above technique is called adiabatic CAES. It‟s
a convenient method for large-scale energy storage.

10. PHAME will also utilize Electrochemical Flow Capacitors (EFCs), which are currently in development by
Drexel University undergraduate students. In contrast to traditional flow batteries subjected to Faradaic reactions, the
electrochemical flow capacitor is a rechargeable electrochemical energy storage system that is based on the working
principles of super capacitors. The EFC utilizes a fluid carbon‐electrolyte „slurry electrode‟ for capacitive energy
storage. During operation, the slurry is pumped from a storage reservoir through two polarized plates as part of the
charging process. Once fully charged, the slurry is pumped out of the cell and stored in external reservoirs until the
process is reversed and the slurry is discharged. The charged slurry stores charge in electrostatic form at the
carbon/electrolyte interface, which allows for rapid charging and discharging leading to a higher power density.
Faradaic charging processes have losses that cause degradation of the device over time compared to electrostatic
charging, which has near 100% efficiency.
The Flywheel is yet another method that has great potential to become a primary storage system. It, “stores
energy mechanically by spinning high strength composite rotors at high speeds”. Theoretically, “the maximum energy
density for potential flywheel materials is a simple ratio between maximum allowable material stress and density”. But
the primary limiting factor is the “maximum allowable material stress that current materials can achieve” [28]. There is
scope for research in nanotechnology to create a “carbon nano fiber rotors” with greater tensile strength, less density
and light weight [25].
The energy storage will be divided into three parts. 60% of the energy will be stored in fuel cells because, along
with the storage, it will also satisfy the need of oxygen. This will be the primary storage technique in the storage
system. The other 24% of the energy will be stored in CAES plants. This is used as a secondary storage system because
of the need to insulate the underground storage system. The remaining 16% of the energy will be stored in
electrochemical flow capacitors. The high cost and major demand of resources for initial setup of electrochemical flow
capacitor is the reason for such a small percentage of the energy being stored using this method. Also, its lifetime is
100,000 cycles whereas fuel cells and CAES have limitless cycles. Since, the sun and time has no effect on
electrochemical flow capacitors it can be used anytime throughout the day and year.
5. RESOURCES AND TOOLS
5.1 In-Situ Resource Utilization
Martian colonization has evidently been debated for years and many of the discussions have given birth to a
crucial concept termed, In-Situ Resource Utilization (ISRU). ISRU refers basically to combining methods to utilize
Martian regolith to its maximum potential, reaping various minerals and metals for later use. PHAME segregates
mission ISRU into distinct parts: Martian Regolith Acquisition, Water Extraction, Iron Ore Extraction, Material
Processing, METS Fuel Processing, and Presence of Perchlorate.
Martian Regolith Acquisition: PHAME understands the importance of In-situ resource utilization (ISRU) and
makes use of multiple calculated steps to mass produce water, fuel and other metals to meet the needs of the habitat
and help it reach sustainability. A habitat on Mars requires a certain mastery in creating usable materials like Iron,
Silver and Lead. Including the aforementioned, it also needs to support sample return missions and the ability to create
an underground tunnel system, for emergencies. Yet another soil acquiring mechanism is needed, which is used to
drive the igloo-like domes to their completion. Another is used for acquiring samples of regolith for the purpose of
research. PHAME, therefore, incorporate three very different kinds of drills: Sample Return, Scoop and Tunnel Boring.
These three are imperative for ISRU, research and the sustainability.
EVAs, as compared to mining for ore, have gone through much research and improvement since its early stages.
The Ultrasonic/Sonic Diller/Corer (USDC) is a percussive and rotary drill to overcome many limitations pertaining to
drilling hard impenetrable surfaces on Mars. A series of modifications of the USDC basic configuration led to the
development of the Auto-Gopher for deep drilling in rocks and regolith. “The developed low mass Auto-Gopher uses
low power and low WOB/preload, and it is not constrained by the mass of a lander/rover to penetrate the formation and
acquire cores.” [29] “During the rotary-only test, the average power was 90 Watt at 25% efficiency – i.e. the power
required to drill was 25 Watts while the rest was attributed to electrical/mechanical losses.” Drilling at the rate of 40
cm per hour, the Auto-Gopher drilled to a total depth of 2 meters in 15 hours, producing core samples every 10
cm.”Total energy to reach the 2 m depth was 500 Whr.” [30] In addition to the wire-line Auto-Gopher, HoneyBee
Robotics, in partnership with NASA, has designed the One Bit One Core (OBOC) architecture for a totally automated
system for acquiring regolith cores and securing them and saving them of any chances of contamination or loss of
material. [31]
A venture like Mars colonization needs the ability to manufacture for the purpose of maintenance and
construction. The elaborate systems and machines will surely require repairing (or replacement of parts) at some point
of time. This calls for the usage of a tunnel boring machine. A tunnel boring machine hacks through material and

11. releases it from its posterior end. This loose material will then be transported and can theoretically be filtered for water,
ores of Iron, Silver and Lead. Having integral uses for each of the above mentioned elements, boring seems to be an
imperative branch of the materials and resource obtaining system.
As an example, “steel will enable fabrication of buildings, parts for vehicles and machinery, beams, pipe,
fasteners, tools, sheet metal, cooking implements, appliances, cutlery, and countless other things.” [33] The Los
Alamos National Laboratory, in collaboration with Texas A&M University, recommends using “a fission powered,
nuclear SubSelene to provide the heat to melt rock and form a self-supporting, glass lined tunnel suitable for Maglev or
other high-speed transport modes. It was estimated that each SubSelene device will mass 320,000 kg, equally divided
between the tunneler and the waste heat rejection areas, and will have a unit development cost of $50M.” [32] “In this
concept, a reactor provides 3 megawatts of thermal power at about 1,300 degrees centigrade, to each of 134 individual
rock-melting heaters. This tunneler design would produce a 5-meter-diameter hole, using a total of 400 megawatts of
thermal energy, which could advance at a very fast rate of 80 meters per day. The system could be entirely automated.”
[33]
As discussed in the Habitat section, PHAME incorporates a collection of inflatable habitats that will be used by
the colonizers for the purposes of research and recreation amongst other activities. Such establishments demand a
unique nature of protection from Galactic Cosmic Radiation (GCR) and Solar Particle Events (SPE). Many tests have
been done regarding the optimal protection and the ionizing radiation dose (quantified using Sievert and Gray units)
one human can withstand. It was earlier found that in constructions and habitats on the ground, it is estimated that
between 2 and 3.5 meter of loosely piled regolith will be required to provide sufficient protection. [34] Whereas
research done by Donald Rapp [2006], particularly, stands out as it goes to considerable depth with very viable
solutions. By differentiating between the radiation values (quantified using Sievert) and the radiation that is actually
absorbed (quantifies using Gray), Rapp has used point estimates to describe the kind of radiation one would experience
in the Martian atmosphere. The Martian atmosphere itself reduces the effect of GCR during a Solar Minimum from
about 57 cSv/yr to around 32 cSv/yr while the effect of GCR during a Solar Maximum from 22 cSv/yr to 15 cSv/yr.
Also, the effect of a large SPE gets mitigated from around 100 cSv to around 30 cSv per event. Calculations done were
in terms of converting energy values of particles (eV) to their Blood-Forming Organ dose equivalents. It was found
that only a 50-cm thickness of regolith (75 g/cm2 assuming a regolith density of 1.5 g/cm3 ) will reduce the GCR
related BFO dose-equivalent to approximately 25 cSv/yr and the SPE related to 15 cSv [35]. As a result of the above,
all the habitats in PHAME are covered with a 5 m layer of Martian Regolith, providing an inexpensive and simple
solution to safety from radiation. Hence, after the inflation of the habitat, the ISAD will be commanded to carry out the
process of digging and depositing hardened regolith as an extra layer for radiation protection.
Water Extraction: Looking through the aspects of our paper focused on attaining resources via methods of
drilling, we now arrive to the aspect of purifying water for daily consumption and usage. Deviating from its obvious
uses, water can also potentially be used for “minerals smelting, minerals processing, and manufacturing processes.”
[36] The regolith will be acquired using the ISAD and will be deposited on a conveyor belt that is connected to an
oven. This oven is used to heat up the soil and collect water. “In order to obtain 1000kg of water, the system must
process 100,000 kg of soil. The vast majority of energy that must go into this system goes into the actual heating of the
soil, 10.30 kW-hr kg-1
of water. In addition, a small amount of energy is required to run the bulldozer and the conveyor
belts, 0.12 kW-hr kg-1
.” [36] Stoker is using a bulldozer, but we are using the ISAD. Viking measured up to 1% water
content in soil, [37] [38], consistent with the Phoenix lander [36], detecting loose ice cemented soil at a depth from 1
cm to 5 cm overlaying a hard ice-cemented material. The top 5 cm of the soil is loose and easy to dig, avoiding deeper
hard permafrost material. [36]
Iron ore Extraction: “The metals Iron (Fe) and Copper (Cu) are much easier to reduce from their oxides or other
compounds than are other common metals such as aluminum, Al, or magnesium, Mg. Relatively simple chemical
methods can therefore, be used to recover iron.” [39] Metal ores will be procured by using the SUBSLENE. “Iron,
however, prefers to be combined with oxygen and its ores, e.g., hematite (Fe2O3) and magnetite (Fe3O4), are well
represented, although not uniformly distributed, in the Earth‟s crust.” [40]
Mars seems to be more promising in terms of providing an abundant supply of iron and aluminum (refer to
Appendix) as compared to the other metals and minerals. The manufacturing processes of the same are adapted from
Stoker‟s paper enumerating the possible production methods for Fe.
Caption: Typical Soil Analysis of celestial bodies of interest
Metal Processing: CO will be used to reduce (solid) FeO at a temperature below 800 o
C. Thus, the atmosphere
could facilitate iron production. [40] Once an Iron Oxide concentrate is obtained, it can be reduced to native iron by
reduction by either hydrogen gas (H2 obtained by electrolysis of water) or carbon monoxide gas, CO, which can be
extracted from the atmospheric CO2. [39] When using H2 gas,

12. ( )
while, when using CO,
( ) ( )
Paying heed to the equations above, it turns out that iron manufacturing is not only feasible, but relatively
convenient, in relation to Mars‟ atmospheric CO2 content.
METS Fuel Processing: In order to maximize payload efficiency and make use of Martian resources, the Crew
Transfer Lander will use a combination of in-situ resource utilization methods to be refueled on the Martian surface.
Prior to the launch of the initial human mission to Mars, robotic test missions will demonstrate key technologies vital
to the colonization effort. One of these technologies includes the fabrication of methane and liquid oxygen on the
surface of Mars to be used by the CTV. In order to produce these substances, an automated process will make use of
both the Sabatier and reverse fuel cell reactions. The Sabatier reaction is detailed below:
Not only does the reaction produce the Methane needed to fuel the CTL, it also produces water which could be
reused by the habitat. The energy produced by the Sabatier reaction will be used to drive the reverse fuel cell. A reverse
fuel cell will be used to produce the hydrogen gas needed by the Sabatier reaction as well as the oxygen needed to
produce the liquid oxygen oxidizer. The reverse fuel cell will utilize the following reaction:
As seen both reactions share similar inputs and outputs and because of this they can be ran in tandem to increase
sustainability. By using these two reactions it is possible to significantly decrease the amount of reaction mass that
needs to be brought to the Martian surface, therefore increasing the amount of critical payload that can be brought to
Mars.
Presence of Perchlorate: One of the most important findings of the Phoenix suggests the presence of Perchlorate
(ClO-
4). Since its discovery on Mars, ClO-
4 has become the focus of interest due to its possible role in destroying
organics in thermal stage of analytical instruments sent to Mars to detect organics. [42]
“The most beneficial use of ClO-
4 on Mars would be as a source of O2 for human consumption and to fuel
surface operations. For example, humans breathe or consume 550 litres of oxygen per day. Based on the amounts of
ClO-
4 measured in Martian regolith, a daily supply of oxygen for one astronaut could be obtained by complete
dissociation of ClO-
4 contained in 60 kg of regolith (40 litres).” [43]
5.2 Plant Growth
One of the most basic necessities for the survival of humans in any setting is the availability of proper, nutritious
food. Thus, food and its production is an integral part of this mission to Mars, more so, because of the duration of the
mission and its ultimate goal of self-sustainability. The goal of this section is to identify the need for appropriate food
production techniques, the methods used in current as well as previous space missions, and alternate methods used for
the mission proposed in this paper.
The traditional way of meeting the nutritional needs of an astronaut on a space mission is to provide packaged
food, rich in the required nutrients and vitamins. This process has ranged from food squeezed into toothpaste like tubes,
to the use of spoon bowls for a wider variety of food items. This has been extended to a more recent multi cuisine
menu consisting of a variety of food items like Kung Pao chicken, dry fruits, and pasta. Even though this is an efficient
way to provide a tasty and healthy meal to the astronauts, it is limited to short term or LEO (Low Earth Orbit)
missions. This is not an ideal method for the 40 year mission to Mars and thus there is a need for an alternate method of
providing food to the inhabitants of Mars. Two methods are being incorporated to deal with the inadequacy of
packaged food for the proposed Mars mission; firstly by growing plants on Mars in simulated environments and
secondly, using hydroponics.
The concept of the Botanical Chamber is similar to that of a greenhouse. However, unlike a typical greenhouse,
the botanical chamber will be completely insulated from the outside conditions and variables like lighting, temperature,
humidity, internal pressure, and atmosphere will all be controlled internally. The chamber will be constructed along
with the rest of the habitat and the required conditions for the plants‟ growth will be set when the first cycle of humans
land on Mars. Since the botanical chamber will be covered with a layer of regolith leaving the interiors bereft of
sunlight (as mentioned in the Drilling section), artificial LED lighting will be used. LED lighting of specific
wavelengths can be used to more effectively grow plants with promising results. Their small size, durability, long

13. lifetime, cool emitting temperature, and the option to select specific wavelengths for a targeted plant response makes
LEDs more suitable for plant-based uses than many other light sources [44].
Different crop species have different optimum growing temperatures and these optimum temperatures can be
different for the root and the shoot environment and for the different growth stages during the life of the crop [45].
Thus, in addition to maintaining a general room temperature, it will also have to be modified when required. Similarly,
the humidity inside the chamber will be controlled using humidifiers. The atmospheric pressure on Mars is less than
that of Earth, and the low pressure will make plants act as if they're drying out [46]. Thus, pressure controllers can be
used to maintain a standard atmospheric pressure inside the chamber.
Plants and Animals: In order to assess the potential for a self-sustainable colony on Mars, the long term survival
and reproduction of plants and animals must be taken into consideration. According to the journal by Christopher
McKay, “It is likely that microbes and plants will adjust easily to Martian gravity, and some animals might cope just as
well.” [47] The concept of sustainable plant growth beyond Low Earth Orbit (LEO) is not far off. In 2010, the
University of Florida was able to send flowers to the International Space Station (ISS). This research proved that plants
can survive quite well in a microgravity environment, due to the fact that the plant cells do not require gravity for
proper growth, and the roots of the plant simply interact with the surfaces that they encounter when they grow. This
research can be applied to Hydroponics, which, is a method of growing plants in nutrient rich water, as opposed to soil.
During the 6-month voyage to Mars, plants can be grown in hydroponic plant chambers, which are self-sustainable and
can adjust to the environments of varying gravity. In the past, growing plants in a microgravity environment has been a
challenge due to the fact that capillary action is unaffected by any forces of gravity or the lack thereof [42]. Due to this,
plants retain far more liquids in microgravity than necessary. For this reason, the hydroponic plant chamber would be
equipped with a centrifuge to rapidly spin the plants and siphon off excess liquids, allowing the plants to grow
effectively. Thus, upon arrival to Mars, a source of nutrient-rich produce will be readily available for the colonizers.
In light of the fact that human beings are similar to many animals and countless health issues arise for astronauts
during a long period in microgravity, it is safe to assume that animals would not adapt readily [43]. In 1989, the
Discovery brought a fleet of 32 chicken eggs within an incubator aboard the ISS. Half of the eggs were developed for
nine days, and the other half were developed for two days on Earth before being sent to the ISS. Eight of the eggs that
developed for nine days on earth before being sent, hatched and survived, while none of the second half of the eggs
hatched that developed for two days beforehand [44]. The results from this experiment prove what was assumed:
gravity is an important factor for the proper growth and development of animals. However, potential applications of
this experiment can be expanded, in that egg incubators can be equipped with a centrifuge in order to aid the proper
development of the chickens. An issue that arises for using chicken eggs on the proposed Mars mission would be
keeping the chickens dormant within the egg during the trip to Mars. That being said, sources of protein such as fish
have the ability to remain dormant in a frozen pond during the cold winter months, and if this environment were to be
simulated, there exists the potential to transport a source or sources of food to Mars.
Areas of Research: The preparation for a sustainable colony will offer the opportunity for conducting research
that encompasses many areas of engineering, technology, and science. Due to the fact that animals have seldom been
taken beyond Earth‟s atmosphere, the 6 month voyage to Mars presents the opportunity to determine various ways to
transport and care for them. Research can be conducted on Mars as well, because breeding animals is a necessity in
order to keep colonizers healthy and maintain their proper macronutrient ratios. Furthermore, the concept of apiculture
can be addressed. Bees are essential for plant maintenance and reproduction and for producing honey, which is not
only a natural sweetener, but a natural antibiotic.
As mentioned above, the hydroponics technique will be primarily used during the six month voyage to Mars.
Once the first crew lands, the hydroponic plant chambers will be transported to the botanical chambers where they will
further develop. While the hydroponic plant chamber seem to be a promising solution for the provision of food, further
research will be conducted to test the conditions on Mars and how they affect plant growth and development. Initial
research will be pertaining to the growth of plants in Martian regolith. This is reinforced by an experiment conducted
by researchers from the Netherlands that showed that 65% of the plants grown in simulated Martian soil at roughly 60
F grown using only demineralized water, can live beyond 50 days [47].
Another aspect of research will be deciphering the variety of plants that could be grown on Mars. Plant seeds can
be stored by drying them in 100 F for about 6 hours in either direct sunlight or in an oven. Using this method, seeds of
cauliflower, carrots, lettuce, onion, etc. will be stored. [40] These seeds will then be used for research purposes in both
the hydroponics plant chambers as well as in Martian soil. Some of the plants that can be potentially grown include
potatoes (sweet and white), soybeans, wheat, peanuts, dried beans, lettuce, spinach, tomatoes, herbs, carrots, radishes,
cabbage and rice [48]. Besides this, the plants grown in the botanical chamber can be tested for their medicinal uses, as
elaborated on in Quality of Life.

14. To summarize the above, the colonizers will initially use packaged foods like the ones used on the ISS while the
botanical chamber and hydroponics is being set up and tested on. Once the botanical chamber is stabilized with a
considerable plant produce, its harvest will be used to replace the packed food and be eventually expanded to a fully
functional bio-farm on Mars.
Medicine: While a self-sustainable colony is conceivably possible, there are many major obstacles that must be
overcome in order to achieve this magnificent feat. To illustrate, medicines are not something that usually come to
mind, but are very necessary for maintaining the health of the colonizers. Fortunately, each type of medicine, as well as
chemicals, is derived from some sort of plant. In order to keep medicine production alive after supplies can no longer
be sent to Mars, the hydroponic plant chamber can be used to produce not only food, but necessary medicines and
chemicals as well.
6. EMERGENCY SITUATIONS
There are many different components, in this mission, which will have to work in tandem to create and sustain a
successful Mars habitat. As with any complex mission, there are many opportunities for things to go wrong, which is
why emergency protocols will be in place to ensure the safety of the astronauts and everything else. The Martian
habitat will need to be prepared for these major emergency situations; Radiation spikes, Power failures, Dust storms,
Depressurization, and Space object collision.
On the Earth, the ozone layer protects humans from the harmful radiation of the sun, but the Martian atmosphere
does not have such a convenient provision. Therefore, the astronauts will need be protected from constant radiation,
particularly solar events that may occur during the mission. Power failures on Earth can be very inconvenient, but a
failure during the Mars mission can create life threatening issues. Dust storms also present a major issue, because they
can last for several months on Mars, and can potentially sabotage structures. The Martian atmosphere is one hundred
times thinner than Earth‟s, making it important to plan for possible depressurization in the buildings or during an EVA.
Finally, due to the thinner atmosphere and close proximity to the asteroid belt, there is a greater possibility of falling
space debris harming the habitat.
6.1 Solar Radiation and Solar Storms
As mentioned in the Habitat and Regolith Acquisition sections, the buildings will be covered with hardened
Martian soil, which will be able to protect the astronauts from the usual amount of radiation. However, this will not
protect the astronauts from the radiation blast of a solar flare. These solar flares are capable of damaging electronics,
and they pose major health issues to unprotected humans. NASA and the National Oceanic & Atmospheric
Administration (NOAA) monitor the sun for flares using specialized satellites and sensors and will be in direct
communication with Mars to alert astronauts of any irregular solar activity. PHAME also includes a centrally located
underground bunker during the initial construction phase; the first astronauts on Mars will be tasked with using the
precious metals found during drilling to fortify this bunker even more. A combination of Lead, Nickel, and Calcium
lining the walls of the bunker will protect the astronauts from any extreme radiation. Although, this paper exceeds to
securing usable iron, other metals are also very much extractable.. In order to reach our sustainability goal for year 40,
a set of CubeSats, which report data directly to our habitat, will be used to watch the sun for irregular solar activity.
These have been proven to work during their initial tests in 2012, when TRIO-CINEMA launched and was successful
at measuring variations in the Earth‟s magnetic field and monitoring fast moving particles. These CubeSats will not be
launched until at least 2030, so more research and development will be done in order to optimize them and make them
as reliable as an average satellite.
6.2 Dust Storms
Martian winds are more frequent and more violent than those on Earth, because Mars has a lower thermal inertia.
These high winds can cause large dust storms, which can affect the habitat for months. Dust storms lower the surface
temperature and spread large amounts of debris, and this debris can significantly erode structures and inhibit the
performance of solar energy. In order to prepare for a dust storm, all buildings will be designed with airtight seals to
prevent debris penetration. During dust storms that last for extended periods of time, the astronauts will not be allowed
to leave the habitats, but they can move from building to building via a network of underground tunnels that connect at
the underground bunker. These tunnels will eventually be constructed using the SubSelene and internal layering using
Lead.
6.3 Power Failures & Depressurization
A power failure during the mission is capable of leading to a whole plethora of issues, so it is crucial that we
have procedures to put into effect in case the power does go out. Since the astronauts will have to exercise everyday to
keep healthy in the low gravity environment, the exercise equipment will be connected to supercapacitors, which will
convert the mechanical energy to electricity and store it for a certain amount of time. These supercapacitors eventually

15. lose their charge, when they aren‟t used, so they will continually charge and discharge until they get used in a real
emergency situation.
Depressurization could arise from a power failure or leakage of pressure in the habitat, and we can model our
response to the situation in the way the ISS does. Since there will be multiple buildings connected by tunnels in the
settlement, the astronauts will have to put on their EVA suits and isolate the affected buildings via a vacuum sealed
door to avoid a pressure drop in the rest of them. A pressure gage will be installed in each room to make it easier for
the astronauts to identify the problem, and they will work with mission control on Earth to correct it. Any EVA on
Mars will need to be accompanied by a rover similar to the one used on the Apollo missions; this rover will be different
in that it will be built to drive on the Martian terrain and it will have backup life support systems. In case of
depressurization during an EVA, the astronaut that is affected will be able to use the rover‟s support system until they
are transported back to the habitat.
6.4 Protection from Space Debris
Finally, the close proximity of the asteroid belt and the thinness of the Martian atmosphere allows the possibility
of falling space debris to damage the settlement. Planetary evacuation may not ever have to be resorted to, but it is
important to have procedures in place in order to minimize losses. One situation in which planetary evacuation would
be necessary would be an imminent space object collision that could cause settlement-wide damage. In October of
2014, the C2013/A1 comet flew past Mars [45]. The path of the comet had been tracked since January 3, 2013. As the
comet came closer to Mars, simulations became more accurate. Similarly, if a comet were to impact Mars, there would
be ample time for evacuation, receiving data about the collision beforehand. NASA reported on the comet passing by
Mars in October 2014, which had a 1 in 2000 chance of hitting the planet. This comet is 1-3 kilometers in diameter,
and it travels at a rate of 56 km/s. If it crashed into Mars, it would hit with as much energy as 35 million megatons of
TNT, which would be capable of extinguishing any life on Mars either by direct impact or rapid climate change.
Astronomers on Earth are already tracking potentially threatening objects for Earth and Mars via advanced earth
telescopes, so we will continue to rely on them to warn the astronauts of any inbound objects. Threats will be detected
early on, and a decision will be made to evacuate prior to the date of the flyby. If evacuation is necessary, the Orion
MPCV that was used to launch astronauts that stays docked to the CTV will be used as a safe haven until the threat is
clear. To meet our sustainability goal, we will have to launch a space telescope, which will orbit Mars and search for
threatening objects specifically. This will be done sometime in the last 10 years before year 40.
7. BUDGET
The money required for the mission supplies is $22.228 Billion.
This excludes the cost of employees and contractors. This value
was multiplied by a safety factor of two to compensate for any
potential errors in estimation. In order to determine the final
cost for the mission including personnel cost is estimated to be
about $ 44.965 Billion. This adds up to about $1.124 Billion
per year. An expanded version of the TRL‟s and budget chart
can be seen in Figure 8.

16. 8. CONCLUSION
With the research conducted so far, the exploration of Mars has been deemed to be possible and safe for
human settlement. While the colonization of Mars is a distinct possibility, there are many constraints involved with it.
These constraints include the ones mentioned in the mission statement such as the budget and the current generation
technology. Despite these limitations, the mission construction aims to cover all possible avenues, while also
incorporating the resources present on Mars.
It is important to note that while the ideas proposed for the mission are revolutionary, they are based on
extensive research conducted but need further practical testing to validate their functionality. Additionally, the current
performance capabilities of the proposed concepts can be maximized during the adaptation, and subsequent
implementation of project PHAME. That being said, there is always a factor of uncertainty associated since it is not
possible to accurately predict the behavior of machines and/ or other operating concepts on the Martian surface.
PHAME would enable a mission spanning a period of 40 years to achieve the goal of sustainability on
Mars and gradual independence from Earth. The colonizers will include a unique team of trained doctors, engineers,
psychologists and dietitians who would be fully capable of performing operations on Mars and also be adept in the
crucial functionalities of the various aspects of the mission. As this mission involves numerous inevitable risks, the
team would be equipped, both mentally and physically, to tackle any emergency situations that might arise.
The mission has been designed with a budget of $44.965 Billion, which includes the money directed
towards advanced research for the mission as well as their implementation on Mars.
Thus, PHAME aims to lay down the blueprint for the future colonizers of Mars, taking all possible
aspects into consideration. Restating Buzz Aldrin‟s quote, “Mars is there, waiting to be reached.”

17. 9. APPENDICES
APPENDIX A - FIGURES
Figure 1. Logistical Diagram depicting the events of one METS trip to and from Mars.
Figure 2. Telescoping communication mast example [3].

18. Figure 3. Geographical elevation map around Hellas Planitia [4].
Figure 4. 3D rendering of Mars habitat.
Figure 5. Various parts of the Auto-Gopher.

19. Figure 6. Image of the Icy Soil Acquisition Device (ISAD).
Figure 8. Expanded TRL‟s and budget chart.

20. Figure 9. Research & Development Timeline
Figure 10. Mission Timeline
APPENDIX B - TABLES
Table 1. Communication node descriptions and tasks.
Table 2. Wind speed comparison from Earth weather anomalies and Mars.

21. Table 3. Summary of Energy Requirements.
Table 4. Calculation of Total Energy Requirement over 40 Years.
Table 5. Total Energy Production Over 40 Years.
Table 6. Battery comparison chart.
Table 7. Materials available from Martian Soil [32].
Table 8. Presence of elements on various planets. [41].

22. Table 9. Abbreviations used.
BFO Blood-Forming Organ
BNNT Boron Nitride Nanotubes
CAES Compressed Air Energy Storage
CTL Crew Transfer Lander
CTV Crew Transfer Vehicle
DCS Decompression Sickness
DSN Deep Space Network
EFC Electrochemical Flow Capacitor
EELV Evolved Expendable Launch Vehicles
EVA Extra-Vehicular Activities
FA Field Activities
GCR Galactic Cosmic Radiation
HAWT Horizontal Axis Wind Turbine
ISAD Icy Soil Acquisition Device
ISS International Space Station
LOX Liquid Oxygen
LEO Low Earth Orbit
LMO Low Martian Orbit
MAPIN Mars Pioneering Network
METS Mars-Earth Transfer Spacecraft
MPCV Multi Purpose Crew Vehicle
PHAME Planitia-Hellas Human Advanced Martian Environment
PB Pre-Breath
RTG Radioisotope Thermoelectric Generator
SPE Solar Particle Event
USDC The Ultrasonic/Sonic Diller/Corer
VAWT Vertical Axis Wind Turbine
APPENDIX C - FORCE BY MARS WIND ON TELESCOPING COMMUNICATION MAST
To calculate the shear moment caused by the wind on the base of the structure, Equation 1.3 and 1.4
were used to determine of the force of the wind on the mast and the shear moment at the base
respectively. Symbol definitions for each equation can be seen in Table 8.

23. Table 8. Equation 1.3 and 1.4 symbol meanings.
The antenna was assumed to be cylindrical, since most telescoping masts on Earth have this type of
structure, giving the structure a profile drag coefficient of 1.2 as seen in Figure 9. The length/width
correction factor was found using Figure 10, with an assumed length/width ratio of 40, equalling to a
0.98 length/width correction factor. The height of the structure was determined using Equation 1.5
using pythagorean theorem according to Figure 11, where R is the width of Mars (m), d is the
communication range (m), and h is the height of the structure (m).
Figure 9. List of profile drag coefficients [47].
Figure 10. Graph of length/width correction factors [47].

24. Figure 11. Geometry relationship used to calculate communication mast height based on radial
communication distance [48].
The height was then used to calculate the cross section area by multiplying the height by the height
divided by 40 (length/width ratio), assuming the tower is relatively rectangular. The wind velocity
was converted from 60 mph (highest wind speed according to the Viking Landers) into m/s, which is
about 26.82 m/s. A safety factor of 4 was added in to ensure the structure could remain standing with
winds up to 240 mph. Air density was calculated using Equation 1.6 below, where p (dry air) is the
air density, p is the air pressure, R is the gas constant, and T is the temperature. Table 9 shows the
data used in order to calculate the air density.
The data mentioned in the two previous paragraphs was then used to calculate the force by wind in
Equation 1.3. The moment of this force was determined by assuming the force acted at the top of the
communication tower to determine the maximum moment. This is calculated by multiplying the force
by wind with the height of the tower.
For Equation 1.4, the outer diameter was given as the width of the structure that was calculated in
order to determine the cross sectional area of the structure for Equation 1.3. The thickness of the
telescoping mast was assumed to be 2 inches in order to give sufficient structural support. Based on
these values, the max shear stress on the base was determined to be 6.233 MPa. The data used for
calculating Equation 1.4 can be seen in Table 10. When comparing this value to the maximum shear
stress of various metals shown in Table 11, aluminum was determined to be a good candidate to be
used on the mast since it is a lightweight and easily accessible metal that will be able to withstand the
shear moment caused by wind on the telescoping communication mast.
Table 9.. Mars atmospheric data for calculating air density.

25. Table 10. Data used to calculate maximum shear moment on the communication mast.
Table 11. Shear strength of multiple materials.

26. APPENDIX D: Compliance Matrix
2015 RASC-AL Technical Paper Compliance
Matrix
Earth Independent Mars Pioneering Architecture Theme
Y/
N
Is the overall system architecture sufficiently addressed? Y
Have you proposed synergistic application of innovative capabilities and/or new technologies for evolutionary architecture
development to enable future missions, reduce cost, or improve safety?
Y
Does your scenario address novel applications (through scientific evaluation and rationale of mission operations) with an objective of
NASA sustaining a permanent and exciting space exploration program?
Y
Have you considered unique combinations of the planned elements with innovative capabilities/technologies to support crewed and
robotic exploration of the solar system?
Y
Have you addressed reliability and human safety in trading various design options? Y
Have you identified the appropriate key technologies and TRLs? Y
Have you identified the systems engineering and architectural trades that guide the recommended approach? Y
Have you provided a realistic assessment of how the project would be planned and executed (including a project schedule with a test
and development plan)?
Y
Have you included information on annual operating costs (i.e., budget)? Y
Have you given attention to synergistic applications of NASA’s planned current investments (within your theme and beyond)?
*Extra credit given to additional inclusion of synergistic commercial applications*
Y
Does your paper meet the 10-15 page limitation? Y
Team Info Graphic of Concept/Technology
Institution: Drexel University
Paper: Planitia-Hellas Human Advanced Martian
Environment (PHAME)
Adviser: Dr. Ajmal Yousuff
Team Leader: Rishiraj Mathur
Competition: Undergraduate RASC-AL Competition
(Insert graphic/image here)
Summarize Critical Points Addressing Theme Compliance and Innovation

27. (At a minimum, please quickly address the bullets. Feel free to summarize additional key components of your concept,
using up to one additional half page if extra space if needed.)
 24 people continuously living on the surface of Mars, completely self-sufficient beginning in 2054
PHAME uses a crew rotation of 4 people every two years. The mission starts with no crew, and gradually builds up to 24 with crew
transfers.
 Crew rotation from Earth every 2 years after 2054
This project achieves complete sustainability by the 40th year and hence, plans no subsequent crew rotations after 2054.
 Gradual build-up of capabilities, infrastructure and risk reduction
In the 40 year span, this mission leads the human colony to sustainability with reference to energy requirements, medical issues
and life on the surface. As each year allows up to 3 launches to Mars, gradual building up of equipment is fairly simple, judging by
the magnitude of the resources and tools used.
 Budget accurately reflects the constraints listed in the themes description
Our budget reflects the total cost of the mission, cost of travel to Mars and every sub-section of every section. PHAME does not
make use of any resource that has a limited budget span and might discontinue.
 In-situ Resource Utilization (ISRU) and reusable systems
PHAME makes heavy use of the Martian environment and produces many of the crucial resources humans and automated systems
will require for functionality. Everything from fuel for return flights to Earth to drinkable water and usable iron.
 Development of new technologies and infrastructure necessary for ISRU and transportation
PHAME also incorporates research and sample return opportunities. It includes a botanical chamber equipped for research towards
plant growth using Martian soil, and animal breeding on Mars.
 Innovation in crafting a concept that will extend humanity’s reach beyond LEO – PHAME incorporates launch logistics that
includes the assembling of three different modules into a single spacecraft enabling travel beyond LEO. Additionally, fuel
production protocols have been addressed outside of Earth.

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