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Approaches and Solutions for Martian Spacesuit Design
Conference Paper · September 2017
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68​th​​ ​International​ ​Astronautical​ ​Congress​ ​(IAC),​ ​Adelaide,​ ​Australia,​ ​25-29​ ​September​ ​2017.
Copyright​ ​2017​ ​by​ ​International​ ​Astronautical​ ​Federation.​ ​All​ ​rights​ ​reserved.
​ ​IAC-17-A5.IP.8
Approaches​ ​and​ ​Solutions​ ​for​ ​Martian​ ​Spacesuit​ ​Design
J.​ ​Lousada*​a​​ ​,​ ​G.R.​ ​Kamaletdinova​b​,​ ​D.​ ​Patel​c​,​ ​Y.​ ​Lakmal​d​,​ ​F.A.​ ​Oluwafemi​e​,​ ​A.​ ​De​ ​La​ ​Torre​f​,​ ​U.​ ​Heshani​g​,
M.P.Onevsky​h​,​ ​S.A.Skvortsov​i
​ ​ ​DLR​ ​(German​ ​Aerospace​ ​Center),​ ​joao.lousada@spacegeneration.org
Scientific laboratory of design and modelling of complex engineering systems, Tambov State Technical University,
106​ ​Sovetskaya​ ​street,​ ​Tambov​ ​392000,​ ​Russia,​ ​kamaletdinova.guzel@gmail.com
c​ ​
CQU​ ​(Central​ ​Queensland​ ​University),​ ​400,​ ​Kent​ ​Street,​ ​Sydney,​ ​NSW,​ ​2000,​ ​Australia,​ ​ ​s0274817@cqumail.com
d ​
SGAC (Space Generation Advisory Council), c/o European Space Policy Institute, Schwarzenbergplatz 6, 1030
Vienna,​ ​Austria,​ ​yasith.lakmal@spacegeneration.org
e​
Space Life Science Unit, Engineering and Space Systems Department, National Space Research and Development
Agency​ ​(NASRDA),​ ​Km​ ​17​ ​Airport​ ​Road,​ ​Abuja,​ ​Nigeria,​ ​P.M.B.​ ​437,​ ​oluwafemifunmilola@gmail.com
f ​
SGAC (Space Generation Advisory Council), c/o European Space Policy Institute, Schwarzenbergplatz 6, 1030
Vienna,​ ​Austria,​ ​andrea.delatorre97@hotmail.com
g ​
SGAC (Space Generation Advisory Council), c/o European Space Policy Institute, Schwarzenbergplatz 6, 1030
Vienna,​ ​Austria,​ ​uthpalahesh@gmail.com
h ​
Department of Information processes and control, Tambov State Technical University, 106 Sovetskaya street,
Tambov​ ​392000,​ ​Russia,​ ​maxim.onevsky@gmail.com
i ​
Department of Information processes and control, Tambov State Technical University, 106 Sovetskaya street,
Tambov​ ​392000,​ ​Russia,​ ​dfoxd@rambler.ru
*​ ​Corresponding​ ​Author
a​
b​
Abstract
The Human exploration of Mars is often seen as the next step in human exploration of the Solar System. Decades
of scientific explorations related to Mars recorded data on the environment of the planet, including geological
aspects, atmospheric composition, life aspects, and helped to create a foundation defining main hazards and security
risk assessment. Based on data from decades of observation and robotic missions to Mars, many agencies and
organizations around the world started planning the first human mission to Mars. Extravehicular Activities (EVAs)
will play a crucial role in any mission either long or short term as human participation is an essential step in the
future. Short term mission EVAs will allow to collect additional data about the planet and its environment, to run
external experiments, and to work on setting up a part of future habitats if needed. Long term mission EVAs will
help to run maintenance activities supporting the whole operation of the habitat or station and continue all needed
scientific activities. Previous studies were dedicated to the analysis of possible hazards for the habitat, station and
spacesuit. The most relevant hazards for the spacesuit design were defined including structural failures, power,
thermal control and life support systems off-nominal situations (ONS), communication problems, loss in data
management​ ​and​ ​problems​ ​related​ ​with​ ​humans​ ​in​ ​the​ ​crew.
Previous works related to the logical and physical level of model of knowledge database for automated control
system of the “artificial lungs” equipment helped to define basic conditions of human in this mission, dependence on
psychophysiological​ ​state​ ​and​ ​needed​ ​level​ ​of​ ​preliminary​ ​testing.
Potential solutions for listed ONS will be discussed in this paper in greater details. This paper will examine past
experience in spacesuit design and its restrictions including aspects of mobility and operability, the conditions they
are​ ​created​ ​to​ ​work​ ​in​ ​and​ ​its​ ​applicability​ ​in​ ​Mars​ ​conditions.
This paper will pay special attention to materials which could be used in the spacesuit design, possible electronics
and​ ​combination​ ​of​ ​life​ ​support​ ​systems​ ​required​ ​for​ ​the​ ​spacesuit.
Keywords:​ ​Mars,​ ​Spacesuit,​ ​Safety,​ ​Design
IAC-17-A5.IP.8
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Copyright​ ​2017​ ​by​ ​International​ ​Astronautical​ ​Federation.​ ​All​ ​rights​ ​reserved.
Acronyms/Abbreviations
EVA​ ​–​ ​Extravehicular​ ​Activity;
ONS​ ​–​ ​Off-Nominal​ ​Situation;
LSS​ ​–​ ​Life​ ​Support​ ​System;
PLSS​ ​–​ ​Portable​ ​Life​ ​Support​ ​System;
IVA​ ​–​ ​Intra-Vehicular​ ​Activities​ ​Spacesuits;
LEO​ ​–​ ​low​ ​Earth​ ​Orbit;
EMU–​ ​Extravehicular​ ​Mobility​ ​Unit;
MCP​ ​–​ ​Mechanical​ ​Counter​ ​Pressure;
ECG​ ​–​ ​Electrocardiogram;
LCVG​ ​–​ ​Liquid​ ​Cooling​ ​and​ ​Ventilation​ ​Garment;
OBDH​ ​–​ ​On-Board​ ​Data​ ​Handling;
PSA​ ​–​ ​Pressure​ ​Swing​ ​Adsorption;
RAC​ ​–​ ​Rapid​ ​Amine​ ​Cycling;
UCD​ ​–​ ​Urine​ ​Collection​ ​Device;
DACT – Disposable Absorption Containment
Trunk;
EDS​ ​–​ ​Electrodynamic​ ​Dust​ ​Shield;
WFM​ ​–​ ​Work​ ​Function​ ​Matching.
1. Introduction
Due to the development of technologies and
population of ideas of colonization, the idea of Mars
mission is becoming more and more feasible. Based on
data from decades of observation and robotic missions
to Mars, many agencies and organizations around the
world started planning the first manned mission to
Mars.
In a short-term missions, EVAs will allow to collect
additional data about the planet and its environment, to
run external experiments, to work on setting up a part of
future habitats if needed etc. In the long term missions,
EVAs will help to run maintenance activities supporting
the whole operation of the habitat or station and
continue​ ​all​ ​needed​ ​scientific​ ​activities.
EVA is defined as any activity completed by an
astronaut outside a spacecraft beyond Earth’s
atmosphere or a planetary surface other than Earth’s.
EVA systems comprised of the following components: a
spacesuit; a portable life support system (PLSS) that
provides a breathable atmosphere and removable of
Carbon Dioxide; subsystems providing stable
pressurization, temperature regulation, mobility, power,
and communications; waste collection; particle and
radiation protection; rovers and mobility aids; tools that
enable​ ​crewmembers​ ​to​ ​accomplish​ ​mission​ ​tasks.
Many studies were dedicated to psychophysiological
state of human in long term missions as it will influence
on overall success of the mission and the crew’s
performance. It helped to form a knowledge database
IAC-17-A5.IP.8
which can be used in preliminary testing and ground
missions as well as to choose optimized modes for
potential​ ​flights​ ​[1].
Previous studies [2, 3] were dedicated to the analysis
of possible hazards for the habitat, station and spacesuit.
The most relevant hazards for the spacesuit design were
defined including structural failures, power, thermal
control and life support systems off-nominal situations
(ONS), communication problems, loss in data
management and problems related with humans in the
crew. This paper will examine past experience in
spacesuit design and its restrictions including aspects of
mobility and operability, the conditions they are created
to work in and its applicability in Mars conditions. Also
it will be focused on technologies used for a spacesuit
design including materials, possible electronics and
combination of life support systems required for the
spacesuit.
2.​ ​Development​ ​of​ ​the​ ​spacesuit​ ​technologies​
Spacesuits​ ​are​ ​divided​ ​in​ ​3​ ​groups:
●Rescue (IVA) suits (Intra-Vehicular Activities
spacesuits) – special suit used by astronauts in case
of decompression of the module or in case of
crucial​ ​ONSs​ ​related​ ​to​ ​environment​ ​onboard;
●EVA suits used for activities in outer space, on the
surface​ ​of​ ​the​ ​aircraft​ ​or​ ​around​ ​it;
●EVA suits for operation on the surface of different
celestial​ ​bodies.
The first spacesuit of USSR was called “SK-1” and
was used for “Vostok” series. NASA's first spacesuits
were developed for the Mercury program. SK-1 and
Mercury fell under the category of rescue suits and were
based on simple pressurized suits. Next step was related
with development of a new spacesuit that would allow
human to perform EVAs. The main issues needed to be
solved were: guarantee of the maximum human safety,
thermoregulation, radiation protection, low weight of
the equipment and possibility to perform actions
(flexibility). Solutions were realized in Berkut and
Gemini spacesuits. These suits did not contain their own
life support systems. The Gemini spacesuit was
connecter with the spacecraft by the cord/tube called
umbilical and Berkut had an open life support system
placed in a special “backpack” and also an additional
systems​ ​connected​ ​by​ ​a​ ​cord/tube.
Next generation of spacesuits, which replaced
Berkut suit was Yastreb. It had a new life support
system, which had a regenerative respiratory system.
Early Apollo suits were analogues of Yastreb suits.
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Further development of these spacesuits was dedicated
to Moon programmes (3rd category). Main challenges
of the realization became maneuverability (including the
option of working with additional devices needed for
exploration or repair) and integration of life support
systems. Apollo suit had a special inside suit equipped
with special biotelemetry sensors. Russian prototype of
Moon​ ​suit​ ​was​ ​called​ ​Krechet​ ​[4,​ ​5].
Modern time examples of “rescue suits” are
Sokol-KV2 used today in the Soyuz ships or the ACES
of the missing space shuttle. EVA suits used for off-site
spacewalks are NASA's Extravehicular Mobility Unit or
Russian​ ​Orlan-MK.
Two companies, Boeing and SpaceX, will use new
spacesuits for astronauts riding on their respective
Starliner and Dragon spacecraft. Boeing unveiled its
Starliner spacesuit, while SpaceX continues to work on
its​ ​Crew​ ​Dragon​ ​suit​ ​[6].
At the moment spacesuits are not optimized and
long-distance missions require a new generation of IVA
and EVA spacesuits. Most modern EVA spacesuits
using nowadays are designed to operate in microgravity
and vacuum, since they are only being used in Low
Earth Orbit (LEO). A Martian spacesuit will require a
novel design, with specific features that mitigate the
hazards​ ​of​ ​the​ ​Martian​ ​surface.
3.​ ​Initial​ ​conditions
To define requirements for Martian spacesuit, it is
needed to specify conditions of the environment and to
list expected actions taking during explorations and
general operation. Temperature on Mars can vary from
-125​o​C to 20​o​C. The atmosphere is 100 times thinner
than Earth. The air consists of CO​2​. Giant dust devils
routinely kick up the oxidized iron dust that covers
Mars' surface. The dust storms of Mars are the largest in
the solar system, capable of blanketing the entire planet
and lasting for months. The Martian “snow/ice” made of
carbon​ ​dioxide​ ​rather​ ​than​ ​water​ ​[7].
Based on this, the spacesuit has to protect against the
low temperatures and low pressure of the Martian
atmosphere. Technical requirements for a Mars EVA
suit include mitigation of the thermal fluctuations
resulting from the Martian atmosphere, limitation of
dust contamination, prevention of organic venting, and
radiation protection. The main biomedical requirements
for a Mars EVA suit include a low EVA system mass,
high mobility and dexterity of space suit enclosure with
optimized joint design, provision of water, waste
collection, and a life support system that works at a
minimum of 8 hours, automatic thermal control system
and​ ​conditioning,​ ​and​ ​sun​ ​visor​ ​assembly.
IAC-17-A5.IP.8
There are five primary justifications for manned
extravehicular surface operations on Mars: Geological
exploration, Exobiology, other Mars Science, Base
Construction, and Maintenance [8, 9]. Based on this,
following​ ​actions​ ​could​ ​be​ ​performed​ ​(figure​ ​1):
• Organisation​ ​and​ ​system​ ​check​ ​after​ ​landing;
• Solar panels deployment checks to have power for
laboratory​ ​and​ ​provide​ ​power​ ​to​ ​critical​ ​systems;
• Use the regenerative cells when necessary
otherwise​ ​shut​ ​them​ ​down;
• All​ ​the​ ​systems​ ​should​ ​be​ ​ready​ ​for​ ​check;
• Determination of the direction of further
investigation;
• Investigation of the geology and mineralogy of the
surrounding​ ​area;
• Exobiological​ ​researches;
• Water exploration on Mars or evidences of water,
valleys,​ ​reservoirs;
• Deep drilling below the surface to check the
resources;
• Other​ ​experiments;
• Communication​ ​with​ ​Earth​ ​and​ ​control​ ​center;
• Reporting​ ​and​ ​protocolling.
Fig.​ ​1.​ ​Operation​ ​in​ ​the​ ​spacesuit.
4.​ ​Design​ ​solutions
The EVA systems, the spacesuit and PLSS together
known as the EMU or Extravehicular Mobility Unit, are
required for accomplishing those surface operations
goals​ ​(table​ ​1).
Table 1: Gas-pressurised suit attributes and Mars
requirements.
Property
Weight​ ​on​ ​Earth
(kg)
Apollo​ ​EMU
100​ ​(17​ ​on
moon)
Space​ ​Shuttle
EMU
131
Mars​ ​EMU
<45
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Weight​ ​on​ ​Mars
(kg)
Weight​ ​location
Bulk
Glove/arm
flexibility
Leg/torso
flexibility
Gaseous
leakage
Durability/
maintainability
Cooling
Outergarment
protection
38
50
<17
Back
High
Low
Back
High
Low
Distributed
Low
High
Low
Low/none
High
High
High
Low/none
Low
Low
High
Sublimation
Vacuum
multilayer
Sublimation
Vacuum
multilayer
?
?
An EMU must provide a safe, comfortable
environment for its occupant, maintaining atmospheric
pressure, temperature, acceptable O​2 and CO​2 levels,
protect from contamination (physical and biological),
handle other metabolic wastes, and provide physical
protection from tears and punctures. To maximize
useful work per EVA, 8 hour endurance is required. A
30 minute backup life support system should be
installed to maintain current safety levels. The EMU
should provide constant communications with other
suits, rovers, or bases. The occupant should be able to
walk at 6.5 km/hr and drive a rover while wearing the
EMU. The EMU must provide all of these in a package
which is light and mobile enough to allow the primary
EVA goals to be accomplished as easily as possible.
The Mars environment presents a unique challenge to
EVA operations: significant surface gravity. Its surface
gravity is 0.36 earth's. The moon, the only other surface
EVA location to date, has less than half this gravity.
EMU systems have traditionally been quite massive.
The Apollo suits massed 38 kg, with a 62 kg PLSS for a
total of 100 kg. A total EMU mass of 100 kg would be
overwhelming on the Mars surface; obviously system
mass must be reduced. The baseline rule determined by
the study group was that the Mars EMU perceived
weight (mass x gravity) on Mars should not exceed the
Apollo EMU perceived weight on the moon. The target
system mass was therefore determined to be 45 kg. This
massively lower allowable EMU mass requires a
fundamental​ ​rethinking​ ​of​ ​suit​ ​design​ ​concepts​ ​[8].
4.1.​ ​Layout​ ​design
Layout definition is based on the description of
every​ ​part​ ​of​ ​the​ ​spacesuit​ ​(figure​ ​2):
1. PLSS: Contains water cooling equipment,
removes the exhaled CO​2​, fan to circulate the
oxygen,​ ​two-way​ ​radio​ ​transmitter
IAC-17-A5.IP.8
2.
3.
4.
5.
6.
7.
8.
9.
Upper Torso: hard upper torso, covers chest
part and support arm assembly, also covers the
back part. It also contains tubes to drain the
water​ ​and​ ​to​ ​allow​ ​oxygen​ ​flow.
Arms: arms available in different custom sizes,
sizing rings can make the length more longer
or​ ​shorter
Gloves: it is very important that astronauts can
do movements of their fingers quickly while
performing EVA or collecting rocks from
MARS. Simultaneously it is very important
that gloves save the life from harsh
environment of the planet. Bearing can fix the
gloves​ ​to​ ​arm.
Displays​ ​and​ ​Control​ ​Module:​ ​one​ ​can​ ​operate
primary​ ​life​ ​systems​ ​from​ ​this​ ​module​ ​and​ ​this
is​ ​also​ ​a​ ​control​ ​module​ ​for​ ​the​ ​mini​ ​spacecraft
In-Suit Drink Bag: valve can be set near to
mouth so while performing any activity on
celestial planet or in space one can bite the
valve to open the water tube. Releasing the bite
will close the tube. The water bag will be
attached​ ​in​ ​the​ ​upper​ ​torso​ ​with​ ​the​ ​Velcro.
Lower Torso Assembly: this assembly has hard
material seal closure which can be attached to
the upper body torso. This assembly covers the
pants, boots and joints. Within this assembly
one can take turns either way. D ring is very
important which has the tethers which won’t
let​ ​the​ ​astronaut​ ​to​ ​float​ ​away​ ​in​ ​space.
Helmet: this assembly has vent pad which will
control the flow of the oxygen from the
primary life support system to hard upper torso
and front of the helmet. The clear plastic
bubble is the main part of the helmet which is
covered by the visor assembly. The visor
assembly will protect the spacewalker from the
extreme temperature and harmful rays coming
from the sun. TV camera and additional lights
can​ ​be​ ​attached​ ​to​ ​the​ ​suit.
Communications Carrier Assembly: this
assembly made up of plastic cap which has
microphone and earphones. Using which the
astronauts can talk to others peers and also hear
the​ ​warnings/cautions.
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10. Liquid Cooling and Ventilation Garment: The
underwear garment made up of stretchy
spandex material. Which used almost 91.5
meters, or 300 feet, of narrow tubes
throughout. Water is pumped through the tubes
near the spacewalker's skin. The chilled water
removes extra heat as it circulates around the
entire body. The vents in the garment draw
sweat away from the astronaut's body. Sweat is
recycled in the water-cooling system. Oxygen
is pulled in at the wrists and ankles to help with
circulation​ ​within​ ​the​ ​spacesuit.
11. Maximum Absorption Garment: one spacewalk
can last long for five-six hours so specially
made garments can be used to absorb the sweat
under​ ​the​ ​spacesuit.
12. Wrist Mirror: this mirror will help astronauts to
see the control module readings. The reading is
written in backward so mirror can revert it
back.
13. Layers: spacesuit has total 15 layers. First three
layers covered by liquid cooling and
ventilation garment. The next layer is bladder
layer which will control the pressure of the
suit. It also holds the oxygen underneath for
breathing. The next layer will hold the bladder
layer to make it flexible per astronaut’s
movement and it is made up of same materials
as camping tents. The next seven layers will
make the suit act as a thermos so temperature
can​ ​remain​ ​same​ ​without​ ​changing.
14. Cuff​ ​Checklist:​ ​holds​ ​the​ ​checklists​ ​of​ ​tasks.
15. Safety Tethers: one end is attached to the
spacecraft and another one attached to the
spacewalker’s​ ​body.
IAC-17-A5.IP.8
Fig.​ ​2.​ ​Main​ ​parts​ ​of​ ​the​ ​EVA.
4.2.​ ​Flexibility
The spacesuit is highly gas pressurized. It means
that human has to perform additional actions to deform
the suit and as a result they experience discomfort, skin
irritations, hot spots and over time injuries. Hands, feet
and shoulders are the most affected areas [10]. Although
proper suit fit is very important to prevent these injuries,
it is very difficult to achieve this (figure 3) [11]. Rising
the​ ​flexibility​ ​is​ ​a​ ​very​ ​important​ ​issue.
Fig.​ ​3.​ ​Location​ ​of​ ​injures.
When the space suit becomes inflated it’s very
difficult for the astronaut to maneuver. It is important to
note that manual depressurization is not safe and not
recommended. Although the space suit is only
pressurized to required level, astronauts will struggle to
move inside the spacesuit as it’s unnatural. Also in the
space, wrinkles in the suit changes its volume and when
the volume is changed the pressure also begins to vary.
So it’s very important to monitor the pressure inside the
spacesuit​ ​and​ ​electronically​ ​control​ ​it.
Spacesuit needs to be flexible and allow astronauts
to​ ​move​ ​freely​ ​and​ ​perform​ ​following​ ​operations:
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1. Carrying things, holding things, and grabbing a
tight​ ​grip​ ​of​ ​vehicle​ ​or​ ​astronaut;
2. Bending​ ​and​ ​stretching;
3. Moving​ ​upper​ ​torso​ ​to​ ​have​ ​things​ ​handy;
4. Moving​ ​shoulders​ ​very​ ​frequently;
5. Moving​ ​waist;
6. Donning​ ​and​ ​doffing;
7. Micrometeorite hitting the spacesuit and making
the​ ​astronaut​ ​out​ ​of​ ​luck.
There are researches dedicated to the spacesuits
designed for micro-gravity experiments in space. Z-2
spacesuit (figures 4, 5) is designed for maximum
productivity on Mars. The space-suit has adjustable
shoulders and solid upper torso. Z-2 has very advanced
level
composites
to
achieve
light-weight,
high-durability, and to withstand harsh environment
conditions for a longer time [12]. The spacesuit must be
flexible enough to don and doff with the help of couple
of​ ​astronauts​ ​or​ ​even​ ​unassisted​ ​[13].
Having 50 years of experience of sending human up
in the space, NASA is building a new generation
spacesuit called Z-3, that will be tested on International
Space Station (ISS) around 2020-21 [12, 14]. Future
spacesuits need “shape memory”. For example, if
astronaut needs to bend his back, stretching the upper
torso, and bending on knees. The spacesuit must also
contain smart sensors to feel astronauts inside what they
are touching on other planets. Integrating tiny cameras
would help astronauts to look things around 360 degree
[14].
Fig.​ ​4.​ ​Z-2​ ​design​ ​of​ ​Z-2​ ​spacesuit,​ ​NASA,​ ​front​ ​view
IAC-17-A5.IP.8
Fig.​ ​5.​ ​Z-2​ ​design​ ​of​ ​Z-2​ ​spacesuit,​ ​NASA,​ ​back​ ​view
4.2.1.​ ​Gloves
Gloves are the most important part of all
hand-operations. Moving the fingers is strenuous so
astronauts try to avoid finger movements as much as
possible, preferring to push and touch objects rather
than hold them. Power tools, for example, are cradled
between the gloves rather than gripped in the usual
fashion. New gloves design has become a NASA
priority. While new materials have offered little increase
in glove flexibility, the most recent efforts to try and
improve the dexterity of these gloves involves the
placement of an electromechanical actuator on the
dorsum of the glove that provides power-assistance to
the major metacarpophalangeal joint. Gloves assembly
protects the hands and wrists of astronauts and it can be
connected and disconnected to the arm assembly. The
assembly has rotary bearing to allow the hands to rotate
freely, a wrist joints to give extension fabric joints for
thumbs and fingers and provides protection against very
hot and cold extravehicular conditions. The gloves have
fingertip​ ​heaters​ ​which​ ​are​ ​controlled​ ​by​ ​astronauts.
Honeywell in collaboration with Dr. Paul Webb, has
developed a prototype of a Mechanical Counter
Pressure (MCP) glove. The glove was chosen as the
first section to be designed due to the immediate need to
improve current EMU gloves, but also because of the
ease of chamber testing and the defining challenge of
applying MCP to the most complex jointed geometry of
the body. At the moment some compression studies
have been performed as well as physiological tests in a
vacuum chamber (table 2, figures 6, 7). The results were
showing that fingers can stay close to each other and
less irritation found inside the hand [15, 16, 17]. But the
thinner material of the glove helps to make the
movements, to do finger movements, and allow the
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hand to stay in natural condition. Although, donning the
glove was the notable and consistent problem as it takes
several​ ​minutes.
Table​ ​2:​ ​Results​ ​of​ ​testing
Test
Mobility
Finger
Thumb
Wrist
Dexterity
Hand/wrist
Tactility
2​ ​mm​ ​dots
4​ ​mm​ ​dots
Naked​ ​hand
Apollo​ ​A7L-B
MCP
100
100
100
30
30
51
92
94
84
100
31
73
100
100
30
75
90
100
The overall viability of the glove was tested at a
NASA JSC vacuum chamber. The subject wore the
glove at pressures below 0.006 atm for 60 minutes, and
found it effectively protected the hand with only a very
small​ ​amount​ ​of​ ​swelling​ ​at​ ​the​ ​base​ ​of​ ​the​ ​little​ ​finger.
Fig.​ ​6.​ ​Comparison​ ​of​ ​fatigue​ ​with​ ​MCP​ ​skinsuit​ ​and
Apollo​ ​A/L/B​ ​gloves
Fig.​ ​7.​ ​Gloves​ ​testing​ ​in​ ​vacuum​ ​chamber​ ​(NASA)
5.​ ​Biomedical​ ​issues​
Biomedical telemetry is aimed to collect various
physiological parameters. Depending on a mission,
biomedical
monitoring
included
[4,
5]:
electrocardiogram (ECG), blood pressure measurement,
IAC-17-A5.IP.8
respiratory rate, galvanic skin response and resistance,
rectal and core body temperatures, passive-dosimeter
for radiation exposure measurement, cardio tachometer
for measuring heart rate, impedance pneumogram,
electroencephalogram,​ ​electromyography.
Simulation missions [18, 19] (e.g. operation with
AoudaX spacesuit) showed that additional weight
burden and thermal stress of the suit can severely strain
the crewmember, leading to adverse health events that
can impact the overall mission. A stable core body
temperature is required to ensure optimal functioning of
the human body; therefore, astronaut core temperature
should be a measured value. Helmet humidity and
temperature measurements would provide insight into
the actual interior temperature of the spacesuit. It is
evident that EVA exposes crewmembers to substantial
physical stress through intense activity involving
increasing​ ​workloads​ ​and​ ​stress​ ​levels.
The medical personnel in the Mission Control
Center should be provided the ECG as the ECG can
provide insight into the cardiac health status of the
astronaut during the mission. In combination with other
physiological parameters (i.e., heart rate, respiratory
rate, and arterial oxygen saturation), the ECG can assist
in evaluating the workload capability and fatigue level
of the astronaut. To monitor thermal stress levels of the
astronaut during the mission it would be best to have
measurements of core body temperature and in-suit
temperature​ ​and​ ​humidity.
The Polipo low-pressure sensing system (figure 8) is
placed on the subject’s left arm and is designed for
anticipated pressure hotspots and for even distribution
over the sleeve. Sensors 1 and 2 are located on the
wrist; Sensor 3 and on the forearm; Sensors 5 and 6 on
the elbow; Sensors 7 and 9 on the upper arm; and
Sensors​ ​10​ ​to​ ​11​ ​near​ ​the​ ​shoulder.
Fig.​ ​8.​ ​Polipo​ ​sensor​ ​locations.
Previous software models to monitor physiological
responses during EVAs could measure heart rate,
respiratory rate, O​2 volume consumption, CO​2 volume
generation, and mean core body temperature. Design of
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new monitors should allow wider range of
measurements to have a full information on a condition
of human during EVA. As an example, a metabolic rate
could now be estimated during EVAs by measuring the
inlet and outlet temperatures of the liquid cooling and
ventilation garment (LCVG) as well as heart rate and
oxygen​ ​consumption​ ​measurements​ ​[20,​ ​21,​ ​22].
5.1. Spacesuit​ ​Data​ ​Systems​ ​and​ ​Sensors
The On-Board Data Handling (OBDH) system is a
key component of the spacesuit as it provides the suit’s
power supply and data acquisition, processing, and
communication. The various sensors with the spacesuit
facilitate physiological and environmental monitoring of
the astronaut. Helmet temperature is measured using an
absolute air pressure sensor and helmet humidity is
measured using a sensor module. Dew point and
potential condensation within the helmet can be
surmised from helmet temperature and humidity data.
With regards to suit gas concentrations, CO​2 is
measured using a module located at the apex of the
helmet’s inner surface. Thus, the measurement is an air
mix between inhalation and exhalation CO​2 levels. In
contrast, O​2 is measured using an oxygen sensor located
in the left side of the helmet. Biomedical telemetry is
collected through an ECG device consisting of a
1-channel ECG amplifier and a 3-channel accelerometer
that transmits signals to either a PC via Bluetooth or
stored locally on a SD card for later analysis.
Additionally, the ECG raw data is used to calculate
heart​ ​rate​ ​variability.
Astronauts should have an access to all the data to
analyze their conditions. That is why the system
requirements should include indication of heart rate
parameters, helmet CO​2 level, helmet O​2 pressure, core
body temperature, body skin temperatures (3
minimum), inner and outer suit temperatures (4
minimum), suit outlet dew point, suit outlet gas
temperature, liquid cooled garment inlet and outlet
temperature, and liquid cooled garment flow rate.
Requirements should include warnings and alerts for
any of the following instances: low suit pressure, high
heart rates (> 175 bpm), high core body temperature,
high partial pressure CO​2 (> 15 mmHg), or excessive
sweat rate (suit outlet dew point > 27​o​C). Also warnings
should be calculated taking into account environmental
and physiological responses to thermal stress, workload,
and​ ​fatigue.
As an example, values for the core body temperature
algorithm are provided in below table 3 and the core
body temperature algorithm is presented in figure 9.
IAC-17-A5.IP.8
There are four different terminal states present in this
algorithm:​ ​Nominal,​ ​Advisory,​ ​Caution,​ ​and​ ​Warning.
Table 3: Threshold Values for core body temperature
algorithms
Terminal​ ​State
Core​ ​Body​ ​Temperature​ ​(0​​ C)
Nominal
36.5​ ​≤​ ​T​C ≤​ ​ ​37.75
Advisory
36​ ​<​ ​T​C​ <​
​ ​36.5
37.75​ ​<​ ​T​C <​ ​38
Caution
35​ ​<​ ​T​C​ <​
​ ​36
38​ ​≤​ ​T​C ≤​ ​38.9
Warning
T​C​ <​
​ ​35
T​C >​ ​38.9
During activities such as spacewalks, astronauts may
perform strenuous activity that causes a rapid rise in
body temperature. A space suit is insulated against
external temperature extremes because the side facing
the sun can heat to 250​0​F, and he side facing deep space
can plunge to -250​0​F. The danger of overheating comes
from within as astronauts release body heat and
humidity inside the suits, potentially causing heat
illnesses. To monitor astronaut body temperature during
space flight, NASA teamed with Johns Hopkins
University in the late 1980s to develop a thermometer
pill called the Ingestible Thermal Monitoring System.
The result was a ¾ inch, silicone-coated capsule
containing sensors, a microbattery, and a quartz crystal
temperature sensor. Once the pill is swallowed, the
quartz sensor vibrates at a frequency relative to the
body’s temperature, transmitting a harmless,
low-frequency signal through the body. Recorder
outside of the body can read this signal and display a
core body temperature and other vital statistics. After 18
to 30 hours, the pill passes safety from the digestive
system​ ​(figure​ ​10).
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Fig.​ ​9.​ ​Example​ ​of​ ​alerting​ ​algorithm.
Fig.​ ​10.​ ​Thermometer​ ​Pill​ ​introduced​ ​by​ ​NASA
5.2. Spacesuit​ ​Sensors
A major spacesuit systems requirement is the ability
to measure all critical data. Critical data, with respect to
health monitoring, the systems requirement document as
the following parameters: heart rate, helmet CO​2 level,
core body temperature, body skin temperatures
(minimum 3), suit internal and external surface
temperatures (minimum 4), suit outlet dew point, and
suit​ ​outlet​ ​gas​ ​temperature.
The top priority sensor should be integrated into the
spacesuit should be core body temperature because the
majority of thermal stress research utilizes this
measurement. It is important for human temperature
regulation and can influence human performance.
Sensors for measuring core body temperature have
become more common in recent years. For example, an
ingestible telemetric sensor has been used successfully
in sport and occupational applications such as diving,
military training, and long-duration exercise. Body
temperature measurement should be taken with a
minimum of 3 skin locations. It would facilitate
monitoring of thermal stress exposure and provide
insight to the body’s thermoregulation practices in the
spacesuit. Body skin temperature has traditionally been
measured using hardwired devices such as thermistors,
but new iButton® wireless sensors do not require
receivers for data collection and are not subject to
IAC-17-A5.IP.8
cross-talk interference found that the wireless iButton®
sensors can effectively measure body skin temperature
during laboratory and field investigations where other
methods for body skin temperature measurement were
problematic.
Body-worn monitors for measuring physiological
health have been developing by space agencies such as
NASA for use in extreme environments. Life Guard is a
physiological monitoring system designed for astronauts
that provides measurements for the following
parameters: ECG, respiration, skin temperature, 2-axis
acceleration, pulse oximetry, pulse rate, and blood
pressure​ ​[20,​ ​21,​ ​22].
6​.​ ​Life​ ​support​ ​system
The life support system of the spacesuit controls the
atmosphere inside the suit, providing CO​2 removal,
oxygen supply, and backup oxygen to restore pressure
in case of leak. The correct function of the life support
system is critical to the suit, since its usual failures
mode can lead to quick death of the astronaut (due to
CO​2 buildup or suffocation for example [1]). Also
included in the life support system can be water
provision for consumption, although this is usually done
by a simple bag attached to the astronaut’s body. For the
Martian spacesuit design, there are five high-level risks
to be addressed: fire, humidity within the suit, maxing
out CO​2 canisters, oxygen depletion, and decompression
sickness. Having identified numerous hazards, the
following solutions were suggested [3]: usage of
non-flammable/fire retardant suit layers as in the current
EVA suits such as the outer Kevlar layer on NASA’s
EMU suit is the solution; usage of rapid amine cycling
(RAC) beds that use proprietary amine sorbents that
temporarily capture CO​2 and water and then regenerate
by venting the excess to the vacuum of space; usage of
alarms and redundant systems as sensors for low O​2 or
high CO​2 suit levels; having an O​2 backup systems such
as the one on NASA’s EMU should be increased in
capacity to account for unexpected delays due to
Martian terrain; usage of a metal layer to reduce
permeation loss of the contents, but due to the carbon
fiber overwrap, the tank can be much thinner and lighter
than a conventional metal-only tank. Within the issue of
decompression sickness some solution could be
implemented: pre-breathing and staged decompression
before EVA, increasing suit pressure, lowering habitat
pressure,​ ​using​ ​other​ ​buffer​ ​gas.
The first concept for a “Super Spacesuit” that could
be used on Mars has been unveiled by Mars One (figure
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11). The Dutch Company plans to send people on the
red planet by 2026, and claims its spacesuit will allow
them to survive in Mars’ harsh conditions. The
pressurized suit will include an impact resistant helmet
with a see-through bubble as well as interchangeable
parts that can be created using a 3D printer. It can also
withstand extreme temperatures from -128 to 77 degrees
centigrade​ ​(-198​ ​to​ ​170​ ​degrees​ ​Fahrenheit)​ ​[23].
Fig.​ ​11.​ ​Mars​ ​One​ ​concept​ ​spacesuit
Developing technologies are being considered for
application in future PLSSs. Some of the solutions are
analyzed​ ​below.
6.1.​ ​CO​2​​ ​Removal​ ​System
Pressure Swing Adsorption (PSA), a process by
which CO​2 can be separated from gas more efficiently,
and through a repeatable process, as opposed to the
current LiOH canisters, which become saturated with
each use, and are limited to around 8 hours. By
regenerating the sorbent during EVA, the size and
weight of the sorbent canister can be greatly reduced.
PSA accomplishes this by venting CO​2 and water vapor
into​ ​space​ ​[24].
Since current PLSS designs utilize lithium
hydroxide to scrub carbon dioxide metabolic waste from
the EMU air supply. About 2kg of LiOH are consumed
per 8-hour EVA. While this is the most EMU
mass-efficient option, it is also a large mass impact on
the overall mission: A mission staying 600 days, with a
2-man EVA every day, would thus consume about 2400
kg of lithium hydroxide (plus packaging factor) during
its ground stay. Lithium Hydroxide can be regenerated
with a complex process, but it is energy intensive and
complex. Lithium Hydroxide regeneration was ruled as
impractical for initial missions. Alternatives to Lithium
Hydroxide are available. Magnesium Hydroxide,
IAC-17-A5.IP.8
Mg(OH)​2​, will work nearly as well as LiOH and
requires only about 50% more mass, or about an
additional kilo, in the PLSS. It can be regenerated by
heating to 500 K in a vacuum or near-vacuum for 20 or
more use cycles. Another option is to use KO​2 as both
the oxygen gas supply and CO​2 scrub chemical. It
appears to be viable, based on initial information,
though further work is needed. Other alternatives
including Ag​2​O, molecular sieves, and membrane
diffusion all appear to be overly massive for Mars
surface applications, requiring at least five times as
much​ ​mass​ ​[8].
6.2.​ ​Oxygen​ ​Supply/​ ​Production
Current space suits carry oxygen bottles for oxygen
and some sort of non-regenerative CO​2 scrubbers for
removing CO​2​. Many constructions were developped
from rescue equipment, so this obviously means that a
space suit is only able to provide life support for a very
limited time. Around 30 liters of algae and water is able
to provide enough oxygen for a human to breathe and
remove the equivalent amount of CO​2​. This has been
experimentally verified in some experiments there algae
was spread over 8m​2​. It’s being said that it is possible to
build a suit that would use algae as regenerative life
support. The one critical problem to this is heat
dissipation. 8m​2 utilizing sunlight is far too unwieldy to
carry around. This needs to be far more compact. The
spacesuit will be an oven that would require simply
huge radiators - something far too unwieldy to use as a
portable​ ​unit​ ​[25].
In another sense, spacesuits use rebreather
technology. Exhaled air is passed through CO​2
scrubbers, then measured for oxygen content. Oxygen
from a 100% oxygen source is added to the air stream to
bring it back up to normal. Exhaled air still has oxygen
in it, so the air stream only needs to be 'topped up'. The
air handling system also removes excess humidity,
odors, and other possible contaminants. Water
condensed from the humidity goes into a storage pocket
that the astronaut can draw from. There's a secondary O​2
system in case the main life support system fails. It's
good for at least 30 minutes, depending on the design
and that's barely enough time to get someone back.
While using an algae system separately to generate the
oxygen used in the space suits might be feasible, at the
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very least it would highly increase the complexity of the
air handling system in a space suit, making it much
more​ ​prone​ ​to​ ​disastrous​ ​failure​ ​[25].
6.3.​ ​Passive​ ​EMU​ ​Cooling
Around 14 kg of the Apollo EMU's mass is in its
thermal control systems. This is a particularly attractive
area for reduction of mass because the Mars atmosphere
provides a cool sink which can be used to passively cool
an EMU. The general concept behind passive cooling is
to design a suit such that the thermal balance of heat
generated metabolically and absorbed from sunlight is
balanced by convective and radiative losses to the Mars
atmosphere, maintaining a stable and comfortable
temperature for the user. Current suits seek to insulate
the user from the environment as much as possible,
removing metabolic heat via a liquid-cooled garment
and heat rejection systems. These systems, and the
required insulation in the suit itself, are quite massive.
To determine the initial feasibility of passive suits, a
simple suit thermal model was integrated with Mars
surface conditions data and various metabolic loads. It
was determined that a suit approximately 8 times as
thermally conductive as the Apollo suits is well
balanced for passive thermal control. At this insulation
level and a 250 watt metabolic rate, the user will remain
comfortable over nearly the whole yearly cycle of day
EVA operations on Mars. A suit with variable layers of
insulation from 60% more to 75% less of this value (an
overcoat and no insulation except tear/dust and pressure
restraint layers, respectively) can maintain comfort over
the whole spectrum of operations. In some hotter cases,
the optimal solution is for the user to sweat to remove
some metabolic heat, but this was accomplished with
earth-normal​ ​amounts​ ​of​ ​sweating.
Basic thermal modeling established that it is
possible to manufacture a passively cooled EMU. In
addition to variable insulation suits (removable suit
layers to tailor insulation level to climate and time of
day, similar to earth outdoors clothing today), several
technologies to enable actually building passive suits
were investigated: dense membranes, to enable
"sweating suits"; insulating properties of materials in
Mars conditions; chemical and isotope heaters for
extreme cold conditions; and phase change materials to
IAC-17-A5.IP.8
stabilize temperature shifts. The following sections
address​ ​these​ ​areas​ ​[8].
6.4. Waste​ ​Management​ ​System
Astronauts spend hours in the space suit during
EVA. The suit must be capable to provide food and
drink and as well there should be a proper waste
disposal system. Waste management system should
collect and dispose human waste without degrading the
astronaut’s performance. Body waste management
system​ ​must​ ​include:
• Body wastes to be accommodated - urine for
men​ ​and​ ​women,​ ​and​ ​menses​ ​for​ ​women;
• Protection from contamination - prevention of
odor,​ ​particles,​ ​biotic​ ​containers,​ ​toxicants;
• Accommodation duration - accommodation of
body​ ​wastes​ ​for​ ​maximum​ ​suited​ ​duration;
• Oral/Nasal Breathing Environment - Space suit
systems in combination with EVA procedures
shall provide for an in-helmet environment that
provides protection from defecation in the suit,
vomiting in the suit, loose food or waste particles
and​ ​Free-floating​ ​liquids.
The liquid wastes from the body can be collected in
a disposable urethane-coated nylon bag, UCD-urine
collection device and that is worn by male astronauts
(figure​ ​12)​ ​[26].
Fig.​ ​12.​ ​Urine​ ​Collection​ ​Device​ ​(UCD)
Female astronauts wear a disposable containment
trunk and that collects liquid wastes in a super absorbent
material​ ​(figure​ ​13).
Fig. 13. The Disposable Absorption Containment
Trunk​ ​(DACT)​
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6.5. Additional​ ​dust​ ​protection
In addition to the space radiation one of the major
hazards the astronauts will face is dust. Micro sized
particles will enter the habitat through instruments,
space suit, and through any gap or opening. And with
the dust from Mars there can be toxic particles that can
eventually lead to cancer or lung injuries. The abrasive
and reactive chemical nature of regolith in the form of
micro sized angular silica oxide particles can also create
problems to the space suit after one EVA [27].
Protective covers can be used to mitigate the
contamination of dust. It provides a lightweight inherent
barrier protection against hazardous dry particles and
aerosols, and non hazardous light liquid splash and
excellent abrasion resistance. These covers are reusable
and materials are 20-30 mils thick with excellent barrier
properties.
battery for the space suits. So for the Mars space suit
Li-cell​ ​can​ ​be​ ​used.
7.​ ​Power​ ​supply
There should be enough power to continuously
power the sensors, the software needed to record the
data and maintaining the suit systems. The power
requirement of the full Mars space suit has broken down
as below by engineers at Hamilton Standard (table 4)
[28,​ ​29].
The power system of the Mars space suit should be
possible to supply maximum power demand. The design
needs to supply proximately 150 Watts for 8 hrs as a
goal with low mass. Power requirement for the space
suit can be fulfilled by following methods: charging
overnight, charging using solar cells in day time and
generating power as body moves forward through some
electrical​ ​equipment.
Rechargeable batteries can be used as the primary
source. They will provide the power requirements to
sensors and other equipment and will be charged by
solar cells during the day and charged at night. As the
sensors are integrated into the space suit they cannot be
taken out and charge separately. On the chest area
flexible solar cells can be integrated to the space suit
along with the computer board. This external system
will consists of the computer, the connections to the
sensors and suit and connection to anything need to be
charged. One large solar cell voltage will be 8.15V and
4 solar cells (2 on the front and 2 on back) can be
integrated into the chest vest. It will provide power from
32.5V as a secondary charging solution. A typical
Li-Ion cell will operate nominally at an average voltage
of 20 V and the lowest specific energy obtained from a
Li-ion cell is 130 Wh/kg [29]. It is the latest developed
IAC-17-A5.IP.8
Table​ ​4.​ ​Power​ ​requirements.
Subsystem
Power​ ​requirement
Communication
10W
Cooling​ ​fluid​ ​circulation
30W
Life​ ​support
5W
Active​ ​control​ ​valves
5W
Control​ ​/monitoring​ ​system
5W
Heaters
35W
Dynamic​ ​H2O​ ​separation
10W
Information​ ​Display
10W
Instrumentation
5W
Lightning/Ventilation
30W
Total
145W
8.​ ​Materials
An innovative design for spacesuits in Martian
missions would have to be comprised of materials that
would withstand the radiation that is received on the
planet, as well as a reduction of mass to the current suits
for greater mobility and comfort [30]. The suit would
consist of 15 layers which are composed of the
following​ ​materials​ ​(figure​ ​14):
1. Soft fabric tricot lining for astronaut’s skin (2 mm
–white).
2. Nylon with cotton, on which is laid a layer of
spandex with a plastic tubing for cooling and ventilation
of the astronaut (4mm-white, plastic tubes 1.5 cm
–blue).
3. Memory alloys (nickel-titanium). Memory alloys
such as nickel-titanium can in essence be “trained” to
return to an original shape in response to a certain
temperature. This material provides pressure to the suit,
so the energy is spent when adopting the position. This
layer is thin, therefore reduces the mass of the suit and
improves mobility on the Martian surface (7
mm-Golden).
4. Dacron with cotton: Cotton batting is very durable
when used as a dense padding layer. The dense mesh of
fibers prevents premature wear of other comfort layers
resulting in a product that brings value because of its
resiliency​ ​and​ ​consistency​ ​(5mm​ ​–white)​ ​[31].
5. Nylon coated with neoprene: It belongs to a
family of synthetic rubbers that are produced by
polymerization of chloroprene. Neoprene has good
chemical stability and maintains flexibility over a wide
range​ ​of​ ​temperatures.
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6. Nylon lined with urethane and Dacron: Reinforces
the internal pressure of the suit. The urethane is
characterized by its high resistance to changes in
temperature and humidity levels, as well as movement,
wind and dynamic loads [32]. The Dacron has the most
relevant​ ​features:
• High​ ​resistance​ ​to​ ​wear​ ​and​ ​corrosion.
• Very​ ​good​ ​slip​ ​coefficient.
• Very good barrier to CO​2​, acceptable barrier to
O​2​​ ​and​ ​humidity.
• High chemical resistance and good thermal
properties:​ ​it​ ​has​ ​a​ ​great​ ​non-formability​ ​to​ ​heat.
• High resistance to folding and low moisture
absorption, which makes it very suitable for the
manufacture​ ​of​ ​fibers​ ​(3​ ​mm-white).​ ​[33]
7. An aluminized layer of Mylar laminated with
Dacron formed in turn by six coating sub layers against
micrometeorites​ ​(0.38​ ​mm-Silvery).
8. Mixture of Gore-Tex, Kevlar and Nomex,
polymers highly resistant to radiation and also a coating
of blue maya, a known pigment due to its excellent
properties: not only has a strong blue color, but is
resistant to light, corrosion and heat Moderate, does not
fade with concentrated nitric acid, alkalis or organic
solvents, and the murals executed with it have tolerated
humidity for hundreds of years. Blue Maya is a complex
formed by Palygorskite and Indigo clay that provides
the blue color (1.5 cm –blue). In addition, the dust on
the surface of Mars is a problem so an electrodynamic
dust shield (EDS) would be added. The combination of
the EDS system of the carbon nanotube electrode
together with the Work Function Matching Coating
(WFM) coating is proposed for Provide an improved
dust-cleaning system for use in space suits. The WFM
coating works by altering the surface chemistry exposed
to dust and is specially designed to minimize
electrostatic bonding forces. EDS is an active
technology introduced by NASA that uses electrostatic
and dielectrophoretic forces to transport dust particles
from surfaces by generating a traveling electric field (2
mm-white).
The first four layers are handled as complete pieces
forming an overall. The rest are sewn and bonded with
epoxy adhesives as they are resistant to high
temperatures,​ ​chemicals​ ​and​ ​impacts.
Ideally, the electronic material should be between
layers 7 and 8 as the contact with the body is more
remote and the materials are thermally stable. In
addition to a cover of epoxy resins that avoid short
circuits,​ ​dust​ ​and​ ​humidity.
IAC-17-A5.IP.8
Fig.​ ​14.​ ​Layers​ ​of​ ​Spacesuit
8.1.​ ​Helmet
The helmet and visor are made up of a combination
of Kevlar, zylon carbon fiber, polycarbonate and carbon
nanotubes (figure 15). The visor will be mostly
transparent to increase the visibility of the astronaut. It
will have a flexible screen where messages can be
transmitted, as well as alerts or vital signs. In addition, a
layer of transparent epoxy paint and another layer of
polyester​ ​gel​ ​that​ ​protects​ ​from​ ​UV​ ​rays​ ​[33].
Fig.​ ​15.​ ​Helmet​ ​for​ ​Mars​ ​Space​ ​Suit
9.​ ​Conclusions
Previous studies were dedicated to specification of
major hazards associated with Martian mission as well
as in different areas of life support. This work was
focused on the spacesuit design, providing short review
of a general background of the spacesuits development
and typification, indicating differences and challenges
for the long-term mission suits. Even though there are
many studies and prototypes of Martian spacesuits as
well as analogue spacesuits, there is not yet an
optimized approach to the perspective spacesuit design.
Based on literature review, main design aspects were
identified and the given solutions were analysed.
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Correlating initial data and considering hazards with
offered solutions, the best practice was indicated and
given for the future discussion. This paper paid special
attention to general design of the spacesuit and to the
life support systems, including analysis of the human
condition with a help of telemetry sensors. The main
goal for the future of the project is focused on creation
of a detailed description of a spacesuit including
solutions​ ​for​ ​an​ ​optimized​ ​prototype.
https://www.space.com/16903-mars-atmosphere-climat
e-weather.html​​ ​(accessed:​ ​20.05.2017).
Acknowledgements
This​ ​work​ ​was​ ​supported​ ​by​ ​the​ ​Russian​ ​Science
Foundation​ ​(Agreement​ ​15-19-10028)​ ​ ​[Российский
Научный​ ​Фонд​ ​(Соглашение​ ​№​ ​15-19-10028)]​ ​and​ ​it
helped​ ​to​ ​co-operate​ ​efforts​ ​in​ ​human​ ​protection​ ​area
and​ ​in​ ​exploration​ ​of​ ​technologies​ ​used​ ​for​ ​future​ ​Mars
missions.
[10]​ ​Five​ ​things​ ​we​ ​would​ ​need​ ​for​ ​people​ ​to​ ​go​ ​to
Mars.
http://www.abc.net.au/news/science/2015-09-28/five-ke
y-technologies-needed-to-get-people-to-mars/6802314
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68​th​​ ​International​ ​Astronautical​ ​Congress​ ​(IAC),​ ​Adelaide,​ ​Australia,​ ​25-29​ ​September​ ​2017.
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