Mars Society International Student Design Competition Team Russia

2014

1 Contents

1 Introduction 2

2 Onboard systems 3 2.1 Construction and composition of the spacecraft ...... 3 2.2 Motion and navigation control system ...... 4 2.3 Communication ...... 8 2.4 Life support system ...... 9 2.5 Thermal regulation system ...... 13 2.6 Onboard computer system ...... 16 2.7 The power system ...... 18 2.8 Protection against radiation ...... 19 2.9 Medical training and medical brieﬁng ...... 20 2.10 Materials for the crew ...... 24

3 Mass analysis 25

4 Leading out process and Ballistics 26 4.1 Leading out process ...... 26 4.2 Ballistics and ﬂight path ...... 32

5 Scientiﬁc experiments 35 5.1 Medical and biological experiments ...... 35 5.2 Other experiments ...... 39

6 Quick start guide 41

7 Mission control center 42

8 The cost of the mission 44

9 Conclusion 45

10 Sources: 46

11 Team 47

2 1 Introduction

The beginning of 2013 was marked with a bright event. First space tourist and multimillion- aire Dennis Tito established Inspiration Mars Foundation to send a spaceship to Mars with a crew of two people in 2018. Despite the fact that only a flyby mission without landing on surface of The Red Planet is planned, such a brave initiative could not have passed by unnoticed. Pioneers of cosmonautics in Russia, (USSR back then), such as Friedrich Zander and Sergei Korolev, used to dream of flights to Mars. Works on engineering an interplanetary Martian spaceship were already held in 60’s of the last century. Forseeing the problems awaiting humans on their way to Mars, Korolev initiated development of closed ecosystems (which later turned into a successful experiment BIOS-3), and researches in long-time isolation of people in a confined space in the Institute of Biomedical Problems (IBMP).

In today’s Russia there is no project of manned mission to Mars. Unfortunately, since end of 80’s Russia didn’t even have any successful automatic missions to The Red Planet. Still some standalone experiments are carried out, primarily associated with accommodation and work of a crew of future expeditions. So in 2011-2012 in IBMP an experiment Mars-500 was held, modelling a 520-day expedition to Mars with crew of 6 people. Experiments on testing cosmonauts operability after a long flight in weightlessness were held in Gagarin Research & Test Cosmonaut Training Centre, in cooperation with Korolev Rocket & Space Corporation ”Energia”. Cosmonauts who returned after a half-year flight to ISS simulated both working in space suite on a surface of a planet and operating a descending space ship in a centrifuge right after flight from Kazakhstan to Moscow. These experiments proved thatcosmonauts are capable of working during the landing and after it in spite of a long stay in weightlessness.

Nowadays Russian enthusiasts of cosmonautics are looking forward to some serious research on behalf of future expedition to Mars. That is why Dennis Tito’s initiative attracts everyone’s keen attention. What seems to be of even greater interest is the opportunity to participate in initial design of flyby mission provided by Mars Society International Student Design Competition. A significant number of Russian students decided to take part in the competition, me and my teammates among them. It took quite a time to gather our team as we have students and graduates from six Russian universities and three different cities - Moscow, St-Petersburg and Voronezh - as well as one Russian student from Austrian university. The one thing that unites us is the space dream of humans flying further than a low-earth orbit, and we believe firmly that a manned mission planned by Tito will play a big part in future humanity’s space expansion.

The flight to Mars will help us to overcome the fear of perils that await us on the way of long-distance expeditions between planets. It will demonstrate us effectiveness of existing and developing ways of preventing harmful effect of weightlessness and space radiation. And above all, as a result of such a flyby, the humanity will obtain almost all technologies that are necessary for a full Martian mission with landing on the planet. A heavy-lift launch system, living module and atmospheric entry from an interplanetary trajectory will be developed during the project.

3 Our goal in this work is to show what existing Russian sources could be used for a full ﬂight. It is useful to keep in mind that since 2011 Russian Federation is the only country executing regular delivery of international crews to the ISS. The results of our workare represented in this report.

2 Onboard systems

2.1 Construction and composition of the spacecraft Interplanetary manned spacecraft that we suggest to use for the ﬂyby mission Mars 2018 may be created on the basis of previously proved and worked-out solutions.

We take modified European cargo spaceship ATV as the main living and working module. The engineers of ATV have left the groundwork for modifications considering the possibility of using it for manned missions. There are control, power and life support systems etc. inside ATV while heat exchangers and coolers of thermal regulation system are outside. Also we have chosen Russian descent capsule used with Soyuz -TMA for crew delivery to Earth. Surely, we couldn’t choose the descent capsule which is now in use for crew delivery from ISS because it demands set of modifications. The possibility of modification of descent capsule we choose for the tourist flyby Moon mission was worked-out in ”RSC Energia” before. Also there was suggested to use a modified heat shield for the passing through the atmosphere on the escape velocity on the way back that will allow reducing the speed safely. Besides spacecraft Soyuz has been already used in XX century for the Moon flyby missions in unmanned mode and with living beings onboard.

During our mission the descent capsule will be also used as the radiation hideout. For this reason it is surrounded with the ﬂue and water tanks. This construction is equipped with pyrotechnic devices for undocking before the entrance to the atmosphere. There are solar panels outside the toroidal protection with tanks. The propulsion system (used on ATV in standard mode) is situated on the butt of the descent capsule. The docking and observe compartment with active and passive docking adapters and observe dome with an opening lid is used for delivery the crew onboard, docking with space tugs and for the Space and Mars visual observation during the mission.

The general construction and composition of the IMS is shown on the picture below.

4 1. Inhabited compartment 2. Descent capsule 3. Docking and observe compartment 4. External ﬂue and water tanks 5. The propulsion system 6. Solar panels 7. Heat shield 8. Active docking adapter 9. Passive docking adapter 10. Observe dome

Continuation of the text in Annex 2.2 Motion and navigation control system Motion and navigation control system (MNCS) of the ship interacts with the system of the equipment control onboard (SECO) which receives information from the sensor equipment and transmits commands to the executive members. In addition, MNCS communicates with the onboard computer system (OCS) to make decisions on the motion of the ship. OCS also receives signals from themissioncontrol center (MCC). MNCS, OCS and SECOall together form the control system onboard (CSO). OCS is a computer with real-time operating system (OS), coupled witha terminal by the bus, in which the crew can input commands. Job of OS is based on ”modal” approach: the

5 ship during the flight goes from one mode to another, thus changing algorithms of OCS and a controlled equipment set. Each mode provides a set of functions. Each function exists to manage certain set of parameters that need to take prescribed values within the margin of error. In all modes, the first priority is to maintain the function of the required parameters of LSS. Furthermore, each mode has its own specific function.

Basic modes: 1. Standard mode - passive ﬂight and maintenance of orientation. Key features: - Determination of the direction of the Sun (solar cells) and the Earth (for antenna connection) and maintain triaxial orientation; - If necessary - gyrodines unloading; - Conducting scientiﬁc experiments; - Conducting the test instruments and systems checks.

2. Acceleration and orbit correction - giving impulse in the right direction. Key features: - The orientation of the ship in the right direction; - Issuing corrective impulse desired value; - A return to the standard orientation to the Sun and the Earth.

3. Docking, undocking, redocking. Key features: - Docking with boosters; - Docking with the transport ship ”Union”; - Decoupling the return module.

4. Rescue the crew. Key features: - Go to the quickest path back to Earth; - Decoupling the recovery module.

In stage of the leading out process switching between the modes goes by applying signals from the MCC in real time. In later stages, modes 2 and 3 are included in the certain moments of time specified program of MCC or manually from the terminal. The rest ofthe time the ship is in Mode 1. Mode 4 is turned on automatically when it is impossible to perform critical functions, or manually from the terminal. When you manually switch to another mode orat the command of the team from MCC,OCS checks readiness to transition in different mode, and in case all of the systems are ready, asks for confirmation. If the confirmation comes in one minute, theregime changes.

System condition monitoringis carried out on three levels: 1. Instrument level. 2. Functional level. 3. Modes level.

On the instrument level it retrieves information from devices and control equipment. If a device fails, it isreplaced with a duplicate. If all duplicate devices fail, an error message

6 istransmitted to the functional level. At the functional level, the OCSmust execute the functions to be performed in this mode. If the function cannot be executed, an error message is transmitted to the modes level where this function either is replaced to perform other functions, or the ship enters the rescue the crew mode.

While calculating coordinates and orientation the following coordinate system is used: 1. Associated with the vehicle coordinate system. 2. Reference coordinate system associated with the celestial bodies: - Geocentric equatorial coordinate system: the origin - in the center of the Earth axis directed to the vernal equinox and the north pole of the Earth; - Geocentric ecliptic coordinate system: the origin - in the center of the Earth axis directed to the vernal equinox and the north pole of the ecliptic; - Heliocentric ecliptic coordinate system: the origin - in the center of the Sun, axes are oriented the same way; - Areocentric ecliptic coordinate system: the origin - in the center of Mars, the axes are oriented the same way.

The transition from one coordinate system to another is performed by rotating and shift- ing. Rotation can be described in several ways: - With an orthogonal rotation matrix (9 component coordinate transformation - linear); - Using normalized quaternion (4 components, coordinate transformation - square); - Using Euler angles or Krylov corners (3 angles , coordinate transformation - for complex trigonometric formulas).

Representation turns with the aid of a quaternion is quite simple and computationally stable, so they are usually used to describe the rotation in an arbitrary coordinate system. Two successive rotation quaternions are describedby the productof them,a turn in the op- posite direction -by the inverse quaternion. Coordinates of the Sun, Earth and Mars and quaternions linking reference coordinate systems are calculated by the model DE405/LE405 for epoch J2000. Thus, to determine coordinates and orientation of the ship in any coordinate system is suf- ficient to determine the position and orientation of the ship in one of the systems, and then perform the rotation and shift of the coordinates. To impart a predetermined orientationL to the ship in a predetermined coordinate system, one need to define the ship’sorientation L0 0 in the system and define the quaternion of transition to the required of orientation W = L0 - 1L. Quaternion W defines the axis around which it is necessary to turn the ship, and the rotation angle. Knowing the axis, the rotation angle and the approximate ship inertia tensor (the exact inertia tensor cannot be determined because the objects and the crew can move inside the ship) ,OCS counts the pulses for theorientationengines, direction and speed of rotationofgyrodines correcting calculations as the orientation changes. If the known ship position is x0, its speed is v0 and the rotation quaternion L0 at time t0, it is possible, knowing the acceleration a(t) and the angular velocity w(t) at each time point, to determine the coordinates x(t), velocity v(t ) and a quaternion rotation L(t) at any time. Acceleration and angular velocity determines the inertial navigation system, consisting of

7 accelerometers and angular rate sensors respectively. To determine the x(t) and v(t)it is necessary to integrate a simple linear system of differential equations. This system is stable, so an uncertaintyofthe position, velocity and rotation is proportional to the measurement inaccuracy of the initial parameters x0, v0,L0. But at the same time, it increases with the error caused by inaccurate determination of a(t) and w(t). For velocity and rotation this error is proportional to elapsed time (t - t0), coordinates - the square of the time (t – t0)2. So you need to periodically adjust readings of inertial navigation system using other means of navigation. Orientation can beidentified by the stars quite accurate. If the star sensor is out of action, one can use a solar sensor to determine at least the direction toward the Sun for the correct orientation of the solar panels. To determine the coordinates of the ship in the geocentric system onecan use radionavigation or an optical sensor of Earth’s horizon, but their accuracy decreases in sync with the distance from the Earth, so that they are unsuitablefor correction near Mars. To determine the coordinates in areocentric systemone can use the optical sensorof horizon of Mars. Finally, for sufficiently rough positioning in a heliocentric system, onecan use the same stellar sensor, determining the direction toward the planets - 2 planets are enough to determine the coordinates. Thus, MNCSis required to have:

1. Board control: - Central computer OCS - bus-modular system, similar to those used on the ISS: 5.85 kg weight, power consumption 40W, standard bus-modular system (4U) has dimensions of ap- proximately 50x30x20 cm. For reliability you need 3 identical computer: ”the main” - working; backup - backup, in the ”hot” reserve, and replacement - in the ”cold” provision, i.e. oﬀ. Possible to improve the reliability and eﬃciency need to add the computers that control subsystems: Coolant, Ships , etc. - MIL 1553B bus standard for connecting peripherals with the UA; - OCS interfaces with hardware, one coupling device has a mass of 6.45 kg and consumes 24 watts, the ISS has 23 interfaces , but we probably need less. - Terminal - the usual Laptop (notebook) with the operating system Linux. Dimensions - approx 30x20x5 cm, weight - about 3 kg.

2. Strapdown inertial system (SINS), consisting of: - Accelerometers: developed devices to within 0.000001g, the size of about 5 cm and weighing not more than 200 g - Gyro meter angular velocity ( GIVUS ) Accuracy 3.6”/h, power 75 W, diameter 30 cm, weight 12 kg.

3. Automatic optical sensors: - Solar sensor (SD) 251K2: Accuracy 3 ’, 6.5 W power consumption, weight 3 kg; - Block positioning stars (BOKZ) for AMC ”Phobos-Grunt ”designed device with an accuracy of 0.5”, 2 kg, power consumption 8 W; BOKZ dimensions - about 20x10x20 cm - Optical horizonSensors: AMC for ”Phobos-Grunt” developed wide television camera (TCS) with a ﬁeld of view of 23 degrees, weighing 1.6 kg, power consumption 8W and narrow-angle television camera (UTC) with a ﬁeld of view of 0.85 degrees, up 3” weight 2.8 kg. Thus,

8 the ﬁrst TCS ﬁnds the sky Mars or Earth, then UGC directed to that part of the sky and determines the direction of the planet and its angular size more accurately. Resolution of UGC allows to ”aim” at Mars accurate to 8 km from a distance of 500 km away (radius of the sphere of action of Mars) and to ”aim” at the Earth accurate to 13 km from a distance of 900 km away (radius of the sphere of action of the Earth).

4. Onboard equipment for navigation. To determine the position and velocity, knowing the orientation, a single antenna is enough: the distance from the Earth is determined by the delay of the signal, relative velocity -bythe Doppler Eﬀect. For backup we use 2 antennas. It is possible to use the same antennas whichare used for communication. If they take their signals from the Deep Space Network, it can be navigation signals. Thedistance from Earth was ensured accurate within about 3 km speed and within about 2 m/s for the Mars Science Laboratory mission in the same way.

5. Engines orientation (DO) - 24 pieces (3 axes of rotation, 2 pairs of engines on each axle, each engine is duplicated).

6. Gyrodine - 4 pieces (3 support orientation 3 perpendicular axes, one in reserve). Their size and weight can be determined on the basis of similarity to the ISS. Martian ship is similar to the ISS in terms of the requirements for orientation and change of orientation (it also makes one revolution around the Sun per year). At the same time the ISS weighs 400 tons, and the ship - 16 tons, that is 25 times smaller. 4 gyrodine ISS weigh about 1 ton, then 4 gyrodine the ship should weigh about 40 kg. Each gyrodine ISS takes 95x74x71 cm and consumes a maximum of 470 W, thenevery gyrodine will take about 32x25x25 cm on the ship and consume about 20 watts. In the absence of gyrodines ISS orientation spends 12 kg of fuel per day. It means, a ship without gyrodines in 500 days will spend 240 kg of fuel on the orientation ﬂight. Consequently, gyrodines can save 200 kg.

7. Automatic docking system “Course MM”: measures the relative motion in the conical sector with an angle of 15 degrees at a distance of 1 km before docking. Power consumption is 30W, weight 14.8 kg.

2.3 Communication A communication system need for exchanging information between spaceship and terrestrial points of communication.

The system provides: - transmission of telemetric information about the status of all spaceships’s systems - receive commands to control onboard systems from Earth - receive/transmission telephone information - receive/transmission photo/video - information

The communication system operates in the following modes:

9 - standby (receive work) - session - mode (work on to receiver/transmitter of information)

The structure of the communication system includes: - Antenna-feeder device - transmitter’s module - receiver’s module - decoders - information exchanging device - onboard cable network.

Antenna-feeder device includes two antennas: a) 2 omnidirectional antennas as like as antennas Service Module of the ISS. 1 kg weight. These antenna will operate when the spaceship will be on Earth’s orbit and on near with Earth zone of passage track b) high gain antenna with a diameter of 2 m. Data will be transmitted with a speed of 550 kbit/s. Antenna weight 20 kg. Selected from the foreign analogue AFS used on interplanetary spacecraft MAVEN.

This antenna will operate at the far part of the orbit ﬂight. To improve the accuracy and reliability of information transmitting, t must be directed so that the major axis was oriented determinably on Earth induring a session mode. If the antenna will be included in the work on near the Earth, there will be considerable waste of fuel for constant orientation of the complex. In case of failure of the main sets of transmitters and receivers, the second and third set of transmitters and receivers always will be in cold mode reserve.

Continuation of the text in Annex 2.4 Life support system Manned Mars circling flight is unthinkable without life support systems (LSS), which is one of the most important systems onboard the spaceship, as it affects the lives of the crew. To date we have accumulated a rich experience in the creation of the Earth environment in a confined space suitable for human life. Including the time exceeding the years of continuous flight, for example, as on the International Space Station (ISS) and the orbital station ”Mir”. As the basis of our mission to circle overflight Mars we decided to take the basic system used on the Russian segment of the ISS. These advantages include: the use of long-term manned stations, maintainability and low price with respect to the existing analogue. Selected LSS must meet the requirements to maintain minimum conditions, without which life is not conceivable for the astronauts aboard: provide oxygen, water and nutrients, remove carbon dioxide and other products and slag separation of a person in liquid, solid or gaseous form, as well as to maintain the temperature in the environment habitat. Life support systems are designed on the basis of balance of nutrients and energy consumption of a healthy person. Space missions have produced a range of necessary data on the dynamics

10 of human metabolic processes and its adaptation to the ﬂight spacecraft and working in outer space. To calculate the LSS we use the following averages for the needs of one person (Table 1)

Table 1: The means of mass-energy components ﬂows for 1 person per day Mass-energy components ﬂows Unit Value Products of metabolism: Heat generation W 95-100 kJ 8160-13000 Water generation(respiratory and skin surface)1. kg 1.2-2.5 Diuresis kg 1.3-1.5 Carbon dioxide gas kg 1.0-1.5 Excrement kg 0.16-0.20

Consumed waste products: Food kg 0.6-1.7 Water(driking) kg 1.7-3.6 Water(hygienic) kg 2.2-5.5 Oxygen kg 0.9-1.2

Selected life support complex solves a wide range of tasks to establish, maintain and control comfortable conditions of human existence and technical equipment operability.

Depending on the task, LSS equipment is combined in groups: 1. means to ensure the gas composition; 2. water supply facilities; 3. means of providing nutrition; 4. sanitary facilities; 5. means of fire detection and firefighting.

In normal human activity can take place in a fairly narrow range of environmental parameters. Therefore, designing an integrated system of life, we must form a ship microclimatic conditions close to perfect, including: pressure - 660...860mm Hg, temperature - 20...25C, relative humidity - 40 ... 70%, air velocity - 0.1...0.4 m/s, the partial pressure of oxygen - 140...200mm Hg, partial pressure of carbon dioxide - not more than 10mm Hg. Due to the limited scope of our spaceship, we cannot use the most reliable LSS on stocks when all necessary means are taken along for all the 500 days of the planned flight. Unfortunately, the use of biological closed system is also impossible today. The first experiments in this area during the experiment BIOS-3 in Krasnoyarsk (Russia) showed quite impressive results. Three people lived inside at almost 100% closure of the water and air and 50% on the food circuit for 6 months. BIOS-3 was the first and, to date, the only system in the world where all the human needs for water, air and plant foods were completely covered by maintaining a closed ecological cycle of matter in the system.

11 But the disadvantages of this system include its operation only in terrestrial conditions. In orbit weightless conditions only small greenhouses (root modules) were fulﬁlled. Currently the use of actual physical and chemical methods of regeneration and air conditioning is on the cards. Collection and treatment of water allow an almost complete circuit of oxygen and water. Unfortunately, limitations in terms of power supply for our spaceship did not allow us to use the full range of systems for the complete isolation of gas and water inside. For example, we had to abandon the thought of Sabatier Reactor, which would allow the crew to use the allocated carbon dioxide and hydrogen released by the ”electronic”. Now, let’s consider all the life support systems for our ship. (Picture 1)

Picture 1. Life support systems onboard.

1. Means of gas composition Means of gas composition are intended for: • oxygen for the crew from the average daily consumption of one person to 25 l/h; • removal of carbon dioxide from the atmosphere at the rate of average daily discharge one person to 20 l/h; • removal of atmospheric trace gases; • control of the gas composition in the parameters of microclimate Robsch, PO2, PCO2, RN2O, RSO, PH2; • alarm on exceeding PCO2, RSO, PH2 above normal and below normal PO2 decreases; • signaling leakage module;

12 • signaling Robsch fall below the set value adjustment;

To solve these problems is to ensure that the gas composition would be further divided into subgroups: 1.1 Funds of oxygen support system; 1.2 Cleaning and atmosphere; 1.3 Means of gas analysis; 1.4 Controls ship watertight compartments; 1.5 Means of control tightness of joints.

1.1 Funds of oxygen support system Oxygen support system of our ship includse the installation of ”Electron”, one solid oxygen generator (THC) and oxygen fuel module ATV.

1.1.1 System of oxygen support ”Elektron-VM” Installment ”Electron” works on the principle of electrochemical decomposition of water. Installment ”Electron” includes: liquid circuit with a 30% solution of potassium hydroxide (KOH), gas pipelines with a pressure regulator, solenoid valves (TBE). Liquid circuit is located (enclosed) in a sealed enclosure which charges with nitrogen (to enhance security). From the outside the ﬂuid circuit is connected to periodically replace a water tank (EDV). Oxygen is generated in the electrolysis unit by electrolysis of water contained in the solution of potassium hydroxide. Water contains 89% of oxygen. By the reaction water is decomposed into oxygen and hydrogen. Oxygen is supplied directly to the atmosphere of the ship, and the hydrogen is discharged at a vacuum. Electrolysis unit consists of 12 electrolysis cells, prisoners of a ﬂameproof enclosure. Elements cool trailers (CTP). The decomposition of 1 kg of water at a rate of 25 l release of oxygen per hour at a pressure of 760 mm Hg is enough to provide one person breathing during the day. To ensure the daily oxygen requirements of the crew of 2 persons, there must be expanded 2 kg of water per day. Power consumption in this case is 0.5 kW. Thus, to provide oxygen for crew mission (500 days) spending one ton of water is required. Installment ”Elektron” is a controlled onboard computer system. In the operation of control: status valves, the pressure of oxygen and hydrogen in the presence of hydrogen and oxygen backbone presence of oxygen in the hydrogen lin. In case of deviation from the norm setting parameters ”Electron” is automatically disabled. Guaranteed lifetime of ”Electron” is a year, so on the ship it will go through the full spare set. In the experience of the International Space Station operating time units for water (BZ) of the ”Elektron” reached more than 600 days.

1.1.2 Solid oxygen generator SOG consists of replaceable cartridge (cassette) with an igniting device impactor, filter, Dust filter and fan placed in the same housing. It is intended for the thermal decomposition of oxygen-containing substance pressed into a cylindrical casing. The effluent from the oxygen

13 generator is cooled by the air ﬂow. Generator is operated by turning the handle (handwheel) until it clicks. This means that the hammer broke the capsule and chemical reaction started. The amount of oxygen released by a single cassette is 600 L, the decomposition of the cassette product takes 5 - 20 minutes with the reaction temperature of 450 - 500 ◦ C. Surface temperature is SOG can reach 50 ◦C. Generator cooling process continues for about 3 hours while the fan is running. Solid oxygen generator serves as a reserve in case of failure of the primary system ”Electron” while it’s being repaired. Two crew members oxygen recycling should go 2 rounds per day. If we used only SOD for the oxygen support system it would require 2x500 = 1000 rounds. To save storage capacity, we take 40 rounds, providing 20 days of reserve for the possible repairs of ”Electron”.

1.1.3 Compressed gas cylinders ATV As an additional reserve of oxygen onboard stands compressed gas cylinders ATV. In considering oxygen support system it is important to remember about the toxicity of oxygen.

Therefore, if the oxygen concentration in the compartment for any reason would be set above 24,1%, we will face: 1. stop of the ﬂow of oxygen; 2. possible performing of a partial collapse.

It should be taken in knowledge that the toxic eﬀect of oxygen is proportional to the partial pressure and not the percentage of gas. Therefore, inhalation of gas with high oxygen content (including 100% oxygen in individual masks PBA) is necessary to alternate breathing air or pressure reduction.

1.2 Cleaning and atmosphere Cleaning tools designed to remove atmospheric carbon dioxide and gaseous harmful trace from the atmosphere onboard. The composition of the atmosphere of cleaning agents include: • system of cleaning carbon dioxide from the atmosphere ”Vozduh”; • chemical absorbers of carbon dioxide; • puriﬁcation unit from harmful atmospheric trace (BMP);

Continuation of the text in Annex 2.5 Thermal regulation system Thermal control system (TCS) MPK based on similar system has been used and spent on Soviet and Russian space stations (”Mir”, the RS ISS) and is designed to perform the following functions: - provide comfortable atmosphere parameters habitable compartments Interplanetary manned

14 spacecraft (IPC ) for 2 people manning; - ensure temperature conditions for the functioning of the structural elements, onboard systems and equipment located both outside and inside the sealed compartment of the IPC; - provide the desired humidity of the gas medium sealed compartment of the IPC; - ensure uniform gas composition in the joint IPC Containment; - provide the required air velocity in the habitable zone of the instrument and the IPC;

Providing thermal regime External heat sources are: * Direct sunlight

Internal heat sources are: * Operating units and equipment; * Regenerative substance of a system to ensure the gas composition; * Crew members (metabolic heat).

TCS MPK was established in accordance with the following principles: * Maximum insulation from the external surfaces of the IPC has to minimize unregulated external heat transfer and heat transfer from the heated blocks and structural elements to cold; * Radiation way to reset into the environment of excess heat generated in the atmosphere of the IPC; * Maximum utilization of heat generated crew and equipment; * Temperature control enclosures MPK sections and blocks using a liquid coolant; * Construct the multi-loop temperature control system as a system with a hydraulic discon- nection of circuits;

To reﬂect solar radiation outside the MPK screen-vacuum thermal insulation is used. MLI is a multi-layered set of metallized polyethylene terephthalate ﬁlm and glass haze having high vacuum high thermal resistance. MLI is performed in the form of panels, the outer surface of which is closed with glass. TCS consists of two closed not hydraulically intercon- nected circuits: the heating circuit (HCI) and the cooling circuit (CCI). Thermal connection circuits by means of liquid-liquid heat exchanger. Contours are duplicated when the primary circuit (KOB1; KOH1) backup circuit (KOB2; KOH2) is in a ”cold” standby. During operation, the MPK is constantly used one set of circuits: KOB1/KOH1 or KOB2/KOH2.

Heating circuit (HCI) is located within the MPK and serves to collect heat from the working units (LSS etc.) and its distribution throughout the volume of the ship, providing a temperature of 20...25◦C. Circulation of the working ﬂuid (coolant ”Triol”) is provided in the line via electric pump units (ENA). The composition ”Triolet” includes 70% of water, glycerol and 30% special additives. This liquid is safe for the crew in case of leakage. Surplus heat from the HCI using the liquid-liquid heat exchanger transfers the cooling circuit. CCI provides its radiation using radiation heat exchanger cooling - EVA.

15 Coolant circuit CCI is toxic, so the pipes are only on the outside of the ship. The main mode of operation of TCS is automatic.

Moisture control TCS provides relative humidity – 30% to 70%. To maintain the desired humidity on the IPC the air conditioning system, which consists of two redundant systems and SKV1 SKV2, is used. Air cooling in SKV is carried out in two stages. In the ﬁrst stage of cooling air is due to convective heat transfer between the air and coolant heating circuit in the gas-liquid heat exchanger. Cooling air to the second stage and its drainage is accomplished by convective heat transfer in the evaporator - condenser between the air and halocarbon (freon). Power is provided by CFC board network voltage DC 28.5 V and the power supply unit (PSU SLE) alternating three-phase current with line voltage 115 V 50 Hz (for power micro compressor) To condensate of atmospheric moisture from water traps air conditioning system and SKV1 SKV2 in water recovery from atmospheric moisture SRV-K is designed as magistral condensate drain (IOC).

Ventilation Ventilation system (VS) is designed to create a purposeful air circulation in the habitable zone of pressurized compartment and instrument IPC to address the following objectives: * Providing the required atmospheric composition in all zones sealed compartment; * Providing a predetermined thermal balance (temperature gradient) over the entire volume sealed compartment; * Clean atmosphere sealed compartment of household dust.

Experimentally established that the premises (including the ones in sealed compartments) for air velocity less than 0.073 m/s have formed stagnant zones. By reason of insufficient ventilation and as a consequence - increase of concentration of carbon dioxide - a person has a feeling stuffiness while at speeds exceeding 0.3 m/s , there is a draft, which may cause the common cold. Comfortable for the person considered the flow rates of air between 0.12 - 0.18 m/s. Quite suitable air velocity in the range 0.1 - 0.25 m/s. A person feels uncomfortable in those cases when the temperature gradient (temperature difference between separate areas of the room) is greater than 4◦C. In IPC establish a suffi- cient number of fans, which should provide comfort to the crew.

Fans are located: - In CA - 2 pcs.; - The working volume of the IPC 4 pcs.; - The panels working volume of 4 pcs.; - In the transition compartment Pho and overview dome - 4 pcs.

16 Also, the crew can use portable ventilators installed in case of need, such as during physical exercise. There are 4 such fans. Experience in the use of fans on station ”Mir” and the ISS RS showed that their working hours usually exceed the warranty period of work, but we will post onboard 5 spare fans. In CA and PhO stretch soft ducts to deliver by force the air enriched with oxygen from the system ”Electron” in there, air is returned back through the openings of manhole covers. In case of activation of smoke detectors and ﬁre suppression algorithm, all the fans TCS will be disabled to stop the stirring air.

2.6 Onboard computer system Onboard computer system (OCS) is the set of computing facilities intercommunicating through some interfaces. By means of some data transmission unit adapters, or interfaces, the onboard computer system joins the other onboard systems into an integrated structure which is designed for execution of informational and control tasks.

The onboard computer system interacts with a motion and navigation control system (MNCS) during onboard decision making of the ship’s motion. OCS communicates with the Mission control center (MCC) and performs the preliminary processing of telemetric data. MNCS, OCS and equipment control onboard (SECO) form all together the control system onboard (CSO). OCS itself is applied on the bus-modular principle with a hierarchy structure. The modules of the system are connected by some exchange transit lines, which are corresponded by multiplex exchange channels (MEC), such as MIL STD 1553B. The functions of OCS are divided between diﬀerent modules. Such a structure of the system allows perform a scaling without any critical changes in software.

OCS consists of the following buses: • control bus; • MNCS bus; • telemetry bus.

Apart from the OCS there is an embedded computer (EC) in the descent module (DM).

Hardware OCS structure is represented two interchanging contours with diﬀerent functionalities. The ﬁrst contour is formed by computing facilities of the OCS which serve for motion control of the ship and control the onboard systems in real time and connecting busses.

The hardware environment of this contour: • central computer (CS); • control post’s computer (CPC);

17 • interleavers and controllers.

The second contour is formed by LAN which controls the onboard systems, payload and applied processes. Interaction between the crew and the network is carried out by the central control post and additional one (laptop).

The hardware environment of this contour: • control post’s computer (CPC); • personal computer (laptop)

The ﬁrst contour is built for the solving of the following problems: • the providing the onboard systems with required compute capacity for performing the functions of ship control; • control of the onboard systems; • data exchange between the OCS and the onboard systems; • the receiving control commands from Earth and control boards, the processing and the subsequent sending to the onboard systems; • automatic execution of the diagnostic routines for the onboard systems; • collection and the processing of telemetric data; • delegation of the computational tasks and data ﬂow control.

The second contour is built for the solving of the following problems: • provision of the control and monitoring functions of the diﬀerent objects for an operator in the dialogue mode; • control of a technological and science equipment of the station in the real-time mode; • ship control by the ﬁrst contour; • the handling of big data in the LAN; • management of computations for the central post.

Taking into account the fact that a suﬃcient part of the mission will take place far from Earth, a proper data storage system is set on the ship. Solid-state drive (SSD) is planned as a physical drive.

Software The software of the CS is meant for execution of the following tasks: • automatic and automated ship control during all the life-cycle stages; • ensure proper opportunities of ship control and its status monitoring from the direction of the crew or the MCC; • provision of data exchange with MCC; • navigation and motion control of the ship; • provision of data exchange with MNCS; • control of the interfaces; • control of the input commands;

18 • control of the commands for the SECO; • pre-processing of telemetry data and the subsequent sending it to the MCC; • onboard systems management; • data recording on the data bank.

The software of the CPC is meant for execution of the following tasks: • support of ship and onboard systems control; • data exchange with the CC; • warning in case of any emergency; • the data bank management.

Continuation of the text in Annex 2.7 The power system The power system is designed for: - providing onboard equipment and systems of spaceship by energy during the ﬂight - charging batteries from solar panels

The power system includes: - 4 solar panel - 4 backup batteries - 2 buﬀer batteries - bus power - current regulator - sensor unit’s

The total power of all devices and systems which include spaceship with a safety factor of 1.3: - 6 kW.

In moments, when spaceship ﬂyby the Mars, the spaceship will be in the shadow. So it will use the power from buﬀer battery. And it is planning, that consumption of devices and systems will be lower. The total power of all devices and systems which include spaceship with a safety factor of 1.3 in the shadow of Mars: - 4 KW.

ATV’s solar panels, which area is 33.6 sq.m. give the power of 4.8 kW. But if we use in the same area on factory ”KVANT”, where we will get from the 1 sq.m 295 W, the resulting power from solar panels - 9.9 kW. Power which generated by solar cells decreases with distance from the Sun. Near the Mars , solar panels will get 50% of that power, which was prepared at about the Earth, The power -5 kW. The buﬀer battery (chemical current source which based on a silver- zinc battery) will be

19 constantly connected to the output buses and the Solar battery will provide power the con- sumer board, when the solar cell current will equal to 0 (in shadow). If the current SB more than current regulator, the buﬀer battery accumulates electrical energy. Also in spaceship there will be the backup battery designed to maintain on-board network and to provide electricity in the case of complete consumption of energy backup batteries.

2.8 Protection against radiation Total contribution to the background radiation in interplanetary flight Earth-Mars-Earth will consist of solar cosmic rays (SCR), Galactic cosmic rays (GCR), as well as the Earth’s radiation belts (ERB). Let’s think, according to equipment of radiation rover Curiosity received during the flight Earth-Mars is 380 mSv. It gives meaning to believe that the total background radiation obtained for the entire flight crew did not exceed 1 Siever, with appropriate radiation protection. This is the maximum permissible dose for human health. Lethal single dose of radiation for humans is 3-5 Sievert value.

Large amount of information on the radiation environment and the eﬀects of radiation on the human body were obtained in Earth orbital station. It should be noted that in low Earth orbit crew protected powerful Earth’s magnetosphere. On average astronaut on the International Space Station for Radiation Protection 10-15 g/cm2 per day gets dose of 0.6- 0.9 mSv. Summary background radiation obtained in 3 space ﬂights lasting 747 days by cosmonaut Sergei Avdeev was 380 mSv. While the 9-day mission to the moon, the crew ”Apollo 14” has received an average radiation dose of 11.4 mSv with the protection of not more than 7.5 g/cm2.

Ship design provides the most secure shelter from radiation. This lander with fixed on the outer surface of the torus-shaped tank with fuel and industrial water. Total protection in this part of the ship will be variable with changes in the amount of liquid in the tank and will be 10-15 g/cm2. This will allow the importance of protecting the crew protect themselves even from the powerful solar flares. In the descent vehicle exactly crew spends maximum time during the flight. Going into the main module of the ship is associated with physical exercise and other needs. Protection of the basic module consists of the module housing and laid inside the payload. Importance of protecting and variable (3-5 g/cm2) and will decrease in sync with decreasing of stocks payloads. Radiation protective layer. Figure 1. Special contribution to the value of background radiation in interplanetary missions have flares on the sun. Upon detection of such outbreaks, threatening the spaceship, the crew takes place in the descent module to the end of the threat. Selection should consider the date of the flight time of minimum solar activity of 11-year cycle. 2018 is suitable for committing such interplanetary flight. Space weather prediction center allows you to monitor the activity of the sun (Fig.2) Schedule solar cycle progression. Figure 2.

20 Subject to the conditions set out above, and in this spaceship design crew should receive a dose of radiation not exceeding critical to human health. During the flight, the crew will use dosimeters and follow the maximum permissible radiation level for the day, which should not exceed 2 mSv. Beyond the project remained radiation dose calculations from various sources and accurate figures on the thickness of the protective layer structure. In this project, we relied on the figures given in the various reliable sources on the flight experience of orbital space stations, manned flights to the moon (like program “Apollo”) and flying machine Mars Curiosity.

2.9 Medical training and medical briefing All crew members (including both of the backup crews) must pass the same medical training and medical briefing before the flight. Since the requirements for selection of the crew indicated that one of the crew members must be a doctor and have the appropriate skills, crew members will receive various medical instructions. Nevertheless, they should be trained the same.

21 Medical training of the crew includes: - Prevention of adverse eﬀects of weightlessness - Standard physical training - Psychological training

Crew members will be trained at one of the centers for training of astronauts on the standard requirements for medical training. Medical instruction (briefing) will mostly include instructing crew members with no medical training for situations requiring emergency medical care. Also, both crew members require to be trained in using the code to enable emergency protocols in case of emergency, requiring emergency medical care. Due to signal delay, communication with the Centre provides op- tions to include emergency protocols in case of emergencies. The astronauts will be equipped with the recorded video and text files, while entering activating the emergency protocol code. In addition, a crew member without a medical education will have to be trained in first aid (with the mandatory training and passing the exam). Measures of medical accounting and control in the appropriate section application will also require further clarification and training on the part of both the crew members for further application of such positive measures on board during the mission.

Prevention of adverse effects of weightlessness Each of the crew members during a standard physical training will have to take training cycle to prepare for further exposed weightlessness: vestibular apparatus training and another one to prevent the musculoskeletal and cardiovascular system overload. Also, members of the crew will be equipped with special antigravity suit to prevent the adverse effects of weightlessness on board. We should also mention that two crews passing the mission on Earth will not be equipped with an environment of weightlessness, so for them these measures may be subject to modifications (perhaps they will be left for a complete psychological immersion in the atmosphere of being on a spaceship).

Standard physical training Each crew member is required to pass a standard physical training norms and regulations at the astronaut training center. Physical training includes endurance and speed training, training of the vestibular apparatus and the preventive measures of basic body systems overload and subsequent work in zero gravity.

Psychological training Considering the long-term stay in a confined space during the mission, the future crew members will be required to undergo a profound psychological training. The goal of training is identifying potential weaknesses in the psychological profile of the astronaut, their ability of teamwork (focusing on the team rather than personal goals) and temper compatibility with each other. It is assumed that both of the crew members are from one culture field,

22 so that intercultural problems may ﬂatten, however, other problems may arise. Professional psychologists and psychiatrists will be working with members of the crew during training mission and throughout its course.

Engineering briefing and engineering training All crew members (including both of the backup crews) must pass the same engineering training and engineering briefing before the flight. Since the requirements for selection of the crew indicated that one of the crew members must be an engineer and have the appropriate skills, crew members will receive various engineering instructions. However, training should be the same to avoid possible misunderstanding of vehicle systems onboard. Crew members will be trained at one of the centers for training of astronauts on a mission to the specialized requirements of Inspiration Mars: all crews will be required to pass the exam on the knowledge and understanding of vehicle systems, incorporating emergency protocols and Earth connection to be able, if necessary, to make the required repairs inside and outside the ship. Engineering instruction will mostly include instructing a crew member without engineering education for situations requiring emergency engineering intervention and inability to produce the interference with the help of the second crew-member.

Briefing for emergencies All crew members (including both of the backup crews) must listen to the same instructions for emergencies. Instruction must include a set of theoretical rules of behavior in case of emergency as well as practical training. It’s worth noting that the first backup crew emergencies would be modeled on basis of scientifical experiment Mars-500, the second backup crew will face false emergencies same to the ones on board the ship.

2.9.2 Onboard training schedule In ﬂight is used the training system provided with four day microcycle, which includes three days of training and 1 day of rest. At diﬀerent days of the cycle exercise aimed at maintaining speed, speed-strength and overall endurance. The total load from the 1st to 3rd day increases microcycle completed a day of rest. Duration of training - 1 hour.

1st day. Training aimed at maintaining speed- endurance and strength training include walking, running at a pace of 120-140 steps per minute sessions and high-speed running at a pace of 240 steps per minute and more. 2nd day. Training is aimed at maintaining the power of endurance. 3rd day. Basis training - monotonous running relatively low and medium speed for a relatively long time intervals (4-6 minutes) and pedaling on a bicycle ergometer in the same mode. 4th day. Available optional training.

23 On request can be selected the astronaut training on a bicycle ergometer, including pedaling, alternating with work with expanders. The studies confirmed the high efficiency of interval training on the track with a large number of shifts short intervals of intense jogging intervals of walking and training with a share of the passive mode of the web path not less than 30% of the total. Astronauts begin to perform physical exercise 6-7 days of flight , with a gradual increase in load and reaching its highest level in 2 month flight. Further training is planned in a serpentine pattern: a slight decrease in intensity to the 3 month flight, an increase of 4 months to a second month, 5 month again reducing the intensity, etc. Astronauts are recommended to wear a suit ”Penguin” for 8-12 hours a day, allowing the load size, reaching up to 30% ”Earth weight” astronaut. Pinch cuff “Bracelet” is used in the acute period of adaptation to weightlessness on the 7th day of the flight 10s. Is recommended wearing products 10-12 hours a day. At the final stage of the flight ODNT workout (negative pressure on the lower part of the body) will be conducted starting 26 days until the end of the flight. Electromyostimulation is used in the acute period of adaptation to weightlessness and the final phase of flight.

2.9.3 Diet Regular diet for the spaceship crew is designed as a 3-day menu with 4 meals a day, and includes the products of heat sterilization, freeze drying, intermediate moisture and natural form suitable for human consumption without the need of prior preparation and heating, having weight daily set of products Net 1360 and the energy value of 2600 kcal ( Dobrovolsky VF, Theoretical and practical aspects of improving the technology of production of canned foods and diets for the crews of space ships and stations . Dis.d.t.n. - Moscow NII PP and SPT , 2000, p.9-10).

Continuation of the text in Annex 2.9.4 Radiation monitoring. Means of individual monitoring One of the main components of the SORB (System of Radiation Safety) is a CPM (radiation monitoring system). The objectives of this system are monitoring and forecating the radiation environment on the path of the ﬂight and within the plant and determine the radiation dose of the crew. This system consists of active radiation monitoring equipment and the means of individual monitoring. Further funds will be considered individual monitoring. Individual monitoring is carried out by means of active and passive dosimeters. Active personal dosimeter IAP -2. Used for operative dosimeter. Dimensions dosimeter 87h62h21 mm, weight - 0.2 kg. Polling frequency depends on the radiation situation and is 1 time a week.

24 Passive monitoring Individual dosimeters integrated ID- 3M are designed for continuous wearing for each crew member during the ﬂight. These dosimeters shall record the total absorbed dose. Dimensions dosimeter 42h40h11 mm, weight - 0,025 kg. Way to get information - processing in the laboratory after returning to Earth.

Radiation protection Inside the ship astronauts will use personal radiation protection. Chemical protection involves the use of radioprotective short and prolonged action. For briefly radioprotectors including medications protective effect will manifest itself during 0.5- 4 hours after administration. They can be used in solar flares and while passing through the radiation belts. By means of long-term protection drugs with radioprotection are used from one day to several weeks. In pulsed ionizing radiation, they usually show a smaller effect than the funds short-term protection. In the experiment, ”Matryoshka-R” along the outer walls of the cabins will be installed ”Safety Shutters” which presents a screen with pockets that hold napkins and wet towels. Expected dose reduction due to ”Styling - blind” - 15%. Clothing astronauts will also provide protection from ionizing radiation.

Continuation of the text in Annex 2.10 Materials for the crew Accessories for hygiene

Equipment

25 Clothing

3 Mass analysis

3.1. Space tugs 3.1.1. Space tug 1, Space tug 2, Space tug 3

3.1.2. Space tug 4

3.2. Interplanetary Manned Spacecraft

26 4 Leading out process and Ballistics

4.1 Leading out process 1. Fitting complex The ﬁrst launch of Proton-M displays the support circular orbit of 175 km and an inclination of 51.6 spaceship (OK), mass 23.000 kg. It is further shifted into waiting orbit altitude of 220 km, which is starting next to Proton-M.

The second launch Proton-M displays the support circular orbit 175 km booster WP1. OK enters support orbit for the waiting orbit WP1, which is joined with it, after the complex shifts into the waiting orbit.

27 Third launch Proton-M displays the support circular orbit 175 km RB2. OK enterssup- port orbit for the waiting orbit RB2, which is joined with it, after the complex shifts into waiting orbit.

Fourth launch of Proton-M displays the reference circular orbit 175 km RB3. OK enters support orbit for the waiting orbit RB3, which is joined with it, after the complex shifts into waiting orbit.

Fifth launch Proton-M outputs to support a circular orbit 175 km RB4 Dwell . OK enters support orbit for the waiting orbit RB4, which isjoined with it. Ship complex assembly is completed.

28 Spacecraft ”Soyuz-MS” with future crew of the OK is launched on the “Soyuz”. ”Soyuz- MS” goes to the support orbitof OK whereit ﬁts in with it, thenthe crew of two people goes with it on OK. Commander of spacecraft ”Soyuz-MS” undocks from the ship complex and is returned to Earth. Crew OK after ﬁnished verifying the complex systems on reaching the starting period proceeds to launch the departure trajectories to Mars.

29 The change in mass of the complex and the cost of fuel assembly are shown in Table1

Table 1.

2. Leading out on departure trajectories First ignition is made in support orbit perigee and shifts complex intermediate orbit with an apogee of 561.6 km.

Second ignition is made in an intermediate orbit perigee and apogee altitude brings it up to 992.9 km.

30 Third ignition is made to an intermediate orbit perigee and apogee altitude brings it up to 1477.3 km.

Fourth ignition is made in the intermediate orbit perigee and apogee altitude brings it up to 2025.2 km. Resets DTB RB4.

Fifth ignition is made in an intermediate orbit perigee and apogee altitude brings it up to 2963.7 km. CB resets RB4.

Sixth ignition is made in support orbit perigee and shifts complex intermediate orbit with an apogee of 561.6 km.

Seventh ignition is made in intermediate orbit perigee and apogee altitude brings it up to 992.9 km.

Eighth ignition is made in intermediate orbit perigee and apogee altitude brings it up to 1477.3 km.

Ninth ignition is made in intermediate orbit perigee and apogee altitude brings it up to 2025.2 km. Resets DTB RB3.

Tenth ignition is made in intermediate orbit perigee and apogee altitude brings it up to 2963.7 km. CB resets RB3.

Eleventh ignition is made in support orbit perigee and shifts complex intermediate orbit with an apogee of 561.6 km.

31 Twelfth ignition is made in intermediate orbit perigee and apogee altitude brings it up to 992.9 km.

Thirteenth ignition is made in intermediate orbit perigee and apogee altitude brings it up to 1477.3 km.

Fourteenth ignition is made in intermediate orbit perigee and apogee altitude brings it up to 2025.2 km. Resets DTB RB2.

Fifteenth ignition is made in intermediate orbit perigee and apogee altitude brings it up to 2963.7 km. CB resets RB2.

Sixteenth ignition is made in support orbit perigee and shifts complex intermediate orbit with an apogee of 561.6 km.

Seventeenth ignition is made in intermediate orbit perigee and outputs complex hyperbolic trajectory. Resets DTB WP1.

Eighteenth reset ignition is made after DTB WP1 and shifts to a predetermined set of escape trajectories. CB resets WP1.

Changes in the mass and its complex with excretion rate shown in Table 2, the elimination sequence diagram in Figure 1.

32 Table 2.

Continuation of the text in Annex 4.2 Ballistics and ﬂight path The ﬂight can be divided into following stages:

1. The acceleration from the low-earth orbit (height h = 220km up to the V velocity and coasting in the Earth’s scope of activity. In the process:

V = V0 + ∆V (1) where V0 = 7777m/s is the vehicle’s orbital speed and ∆V is a velocity increment. Due to the vehicle’s weight and the amount of fuel during the launching stage, ∆V cannot exceed 4900m/s, from which V cannot exceed 12677m/s. As a ﬁrst approximation it is possible to calculate the vehicle’s pathway in geocentric coordinate system, taking into account only the

33 Earth gravity. At this case the velocity of leaving the Earth’s scope of activity approximates the asymptotic velocity Va1, calculated via the following formula

2 2 Va1 = V2–V2 /(1 + h/R) (2)

where V2 = 11186m/s is the Earth parabolic velocity and R = 6400km is the Earth’s radius. Therefore Va1 cannot exceed 6304m/s.

2. Elliptic heliocentric path ﬂight between Earth’s and Mars’ activity scopes. At the beginning of the stage the correction should be done to enter the Mars’ activity scope. About the end of the stage another correction might be necessary to enter the Mars’ activity scope at the desired position. This position is set with the parameters of the gravitational slingshot of the next stage.

3. Mars’ activity scope coasting, in which the vehicle does the gravitational slingshot: orbits the Mars hyperbolically, changing the course. Like the ﬁrst stage, it is possible to calculate the vehicle’s pathway in the areocentric system of coordinates, taking into account only the Mars’ gravity. While the vehicle is “following” the Mars (and “leaves oﬀ” the Earth, which orbits faster than Mars), its heliocentric velocity should be put together with the Mars’ orbital velocity.

The Mars’ activity sphere entry point determines the angle of maneuver, and the height hM, at which the flight would go on the Mars. The height should be restricted: hM cannot exceed 100 km, so that the vehicle would not get into the planet’s atmosphere (in that case it would be difficult to predict its further pathway). The angle and height are determined so that the vehicle could reach the Earth’s activity sphere at the next stage. Due to the favorable position of the Mars in 2018 it is close to the ecliptic. In the process the vehicle flies around the Mars from the counter-solar side and, accelerating, “catches” the Earth.

4. Elliptic heliocentric path ﬂight between Earth’s and Mars’ activity scopes. At the beginning of the stage the correction should be done to enter the Earth’s activity scopes. About the end of the stage another correction might be necessary to enter the Earth’s activity scope at the desired position.

34 5. Hyperbolic path coasting in the Earth’s sphere activity. Once again, at the calculation of the approximate pathway in the heliocentric coordinate system only the Earth’s gravity could be taken into account. The entry point should be determined to enter the atmosphere at the angle, providing the safe descent.

6. The separation of the descent vehicle (DV), its atmosphere reentry at a given angle and its descent at a sliding pathway. The descent would be managed only by its lift-drag ratio: turning DV (changing its rolling angle) one could manage the course of lifting force.

At the ﬁrst stage of descent DV goes down, moving along the lower borderline of the acceptable reentry corridor. Gravity load increases due to the air resistance. The lifting force should be thus upwards directed, so that the vehicle would not go into the dense atmosphere too fast. At the second stage, after the maximum gravity load DV goes to the upper borderline of the acceptable corridor, while the Earth is round, and the DV pathway is about the bee-line. In that case the lifting force should be directed downwards, so that the DV, going through the light air, would not leave it for the Earth low orbit. Even if it goes to the orbit, it would get into the atmosphere once again at the next loop. But the descent would last too long time and DV would also mean to pass the radiation belts several times, which is harmful for the cosmonauts’ health.

At the third stage DV descends once again, and the lifting force is directed upwards, but the highest gravity load is lower, than at the ﬁrst stage. At the fourth stage DV starts the freefall in the lower atmosphere, which is slowed by the parachutes and the rest of the fuel. It is advisable to land on water to provide the soft landing. As 75% of the Earth surface is covered by the oceans, it is easy to achieve at the stage of the correction before the entry to the Earth’s activity scope.

35 It is considered that the atmosphere starts at the height of 100km. Let us take the gravity load 9g as maximum allowed. Then the vehicle with the lift-drag ratio 0.3, as DV of ”Sojuz”, would have the reentry velocity not more than Vmax = 17300m/s. The width of the reentry corridor with the veclocity a bit lower than Vmax would be 6km and it reduces promptly to null as the velocity reaches Vmax . But taking into account that we can ”aim” at the Earth with precision about 13km, the width of the reentry corridor must be equal 13km. The appropriate reentry velocity is 14200m/s.

Therefore, the speed Va2 of the Earth’s activity scope entry can be estimated with the formula (2) – it cannot exceed 8857m/s.

The restrictions for the speeds Va1 and Va2 determine the time slot, which allows the start: from 2017 to 6th January 2018. Hence, the vehicle would need the fuel stock for 3-4 corrections. To calculate the amount of fuel for one correction, one could use the analog approach. Similar ballistics analogue is unmanned interplanetary probe “Vega”, which has the total characteristic velocity of the corrections 160m/s. Therefore, there should be enough fuel stocked to reach 5060m/s.

5 Scientiﬁc experiments

5.1 Medical and biological experiments The main directions of research programs in the period of Inspiration Mars missions are research and experimental work on the eﬀect on the human factors of a ﬂight to Mars.

36 The expedition members will be exposed to complex simultaneously or sequentially acting factors inherent in the dynamics of interplanetary flight, space environment and conditions of life in a confined space. Main groups of factors: the general conditions of the expedition, physical factors of interplanetary space, dynamic factors of interplanetary flight, closed habitat factors, psychosocial factors. A considerable part of the factors in these groups will be different from the factors affecting the astronauts during orbital flights at the Earth, even at comparable long flight crews. Most of the experiments are aimed at studying the adaptation of the cardiorespiratory system and at metabolism studies in microgravity.

Experiment ”Pnevmokard” Study of the influence of space flight factors on the autonomic regulation of blood flow and contractile function of the heart in long-term space flight.

Goal: Preparation of new scientiﬁc information to deepen the understanding of the mechanisms of adaptation of the cardiorespiratory system and the whole organism to space ﬂight.

Goals: • comprehensive study of the cardiovascular system of astronauts in different stages of prolonged space flight in order to clarify the mechanisms and stages of adaptation and to identify diagnostic criteria for individual assessment of adaptation to weightlessness; • synchronization of indicators of cardiac activity and respiration, as well as the study of the cardiorespiratory system control processes in terms of variability of physiological parameters; • study of the relationship between the functional state of the cardiorespiratory system during a long flight and orthostatic tolerance and physical activity in the initial period of rehabilitation in order to predict the possible reactions of crew members while returning to Earth.

The study will be conducted using the hardware-software complex ”Ecosan- 2007”, which includes the device ”Pnevmokard”. With the onboard device ”Pnevmokard” ISS obtained a number of new scientific evidence on the high individuality of adaptive reactions to long-term effect of weightlessness. It has also confirmed the high efficiency and practical importance of the probabilistic approach to assessing the risk of disease based on the analysis of heart rate variability.

Experiment ”Kosmokard” Study of the inﬂuence of space ﬂight factors on the electrophysiological characteristics of the myocardium and on their relationship with the processes of the autonomic regulation of circulation at long-term weightlessness.

Research goals: 1) research and evaluation of the electrophysiological characteristics of the myocardium under long-term weightlessness;

37 2) study the possibility of early detection of probable prenosological (prepathological) abnormalities that cannot be detected by conventional electrocardiography; 3) examine the relationship between changes in the electrophysiological characteristics of the myocardium and the vegetative regulation of heart rate during the prolonged space ﬂight; 4) investigate the relationship between changes in the electrophysiological characteristics of myocardium in ﬂight and orthostatic tolerance and physical activity in the initial period of rehabilitation with a view to forecasting the possible reactions of crew members while returning to Earth.

Scientiﬁc appartura: Device ”Ecosan-2007” Laying KOSMOKARD- DEVICE, dimensions: 140h100h80 mm, weight 0.30 kg; Laying KOSMOKARD – ASO, dimensions: 300h270h80 mm, weight 0.60 kg; Media KOSMOKARD – DATA, dimensions: 23h23h85 mm, weight 0.04 kg In the course of the experiment will be studied Kosmokard energy-metabolic processes to ensure the myocardium under conditions of prolonged weightlessness that will give new insights into the mechanisms of adaptation of the body of astronaut in space ﬂight.

Experiment ”Sonokard” A comprehensive study of physiological functions by contactless method during sleep during long-duration spaceﬂight. The aim of the experiment is to develop proposals to improve the system of medical super- vision of astronauts using the method of non-contact removal of physiological data during sleep. During sleep the astronauts will be going through the contactless removal of physiological data using the device ”Sonokard” located in a breast pocket of T-shirts.

On the basis of contactless registration indicators of cardiorespiratory system during the nighttime days can develop efficient criteria for evaluating and predicting adaptive capa- bilities of the organism in the long-term space flight. It has not only scientific but also of practical importance for the further development of operational health monitoring of the health of astronauts. Such a system will be an important element in ensuring the safety of manned space flights since it will go to the continuous monitoring of the functional state of the astronauts’ organism. Moreover, long recording complex of physiological indicators will provide new information on the status of the different management levels of physiological functions, their coordination and communication with the degree of adaptation of the body during weightlessness.

Investigation of autonomic regulation of circulation. The purpose of this experiment is to determine the eﬀectiveness of a new method of evaluation of the functional state of the organism, which is to study the risk of abnormalities based on the analysis of heart rate variability (HRV).

38 A hardware-software complex ”Ecosan-2007” is used for the experiment. Vegetative regulation of blood circulation is studied using the method of HRV analysis. Studies carried out in conditions of prolonged isolation in modeling ”Mars mission” showed that in general there is no signiﬁcant change in the functional status and in most cases, the adaptive response of the crew members are adequate.

Experiment ”Diuresis” Study of water-salt metabolism and hormonal regulation in spaceﬂight. The purpose of the experiment - to obtain new data on the state of water-salt metabolism and hormonal regulation of volemy in weightlessness and re-adaptational period after spaceﬂight.

The goals of the experiment are to study: - The state of water-salt metabolism and hormonal regulation of volemy at different stages of space flight and early re-adaptational period; - The relationship between renal excretory activities and its hormonal regulation on the background of water-salt loads during adaptation to weightlessness and the after-flight term period; - Fluid balance and key electrolytes in microgravity.

The equipment used: - Complex for processing, freezing and impact gates biomaterial samples to Earth; - Hematocrit kit for determining the hematocrit in the peripheral blood, - Complex-4 Reﬂotron for determining hemoglobin creatinine and urea, - Laying M receivers for collecting urine (urine tanks with adapters for syringe (FRG), sy- ringes for sampling urine (FRG), clips) 180h120h50 mm, 0.50 kg

At the moment, after the experiment on ISS following results were obtained: During the flight, the amount of fluid intake in the morning significantly reduced with downward trend in daily water consumption and aldosterone concentration in the blood, which could be due to the peculiarities of work and rest, changing the composition of liquid media and circulating blood volume. While in microgravity, the concentration of potassium in the blood significantly increased, probably due to malnutrition of muscles in antigravity, as evidenced by significant negative correlation of this index with a BMI (body mass index). Data correlation analysis indicates that there is a close relationship of age and BMI with other studied parameters. These results should be considered in assessing the nutritional status and condition of the physiological activity of the crew members. The concentration of cortisol and aldosterone in the blood, urinary excretion of VLA (vanillylmandelic acid) in microgravity is not much different from the background that allows us to conclude the absence of activation of sympathetic nervous system and maintaining its functional connections in the final stage of prolonged space flight. In microgravity and after the flight there was a decrease in concentration of prolactin in the blood, which indirectly indicates the increased dopaminergic activity of the CNS (central nervous system), because the regulation of secretion of this hormone pituitary prolactotrophe essentially depends mainly on the activity of dopaminergic neurons tuberinfundibular brain

39 areas. Direct evidence of increasing dopaminergic activity is to increase the body’s excretion of HVA (homovanillic acid) in the urine in the air, while the ratio of ICH/HVA did not change. Increased CNS dopaminergic activity can lead to increased peripheral vascular resistance, systolic blood pressure and increase in cardiac output and cause symptoms of agitation and imbalance of crew members in the ﬁnal stages of ﬂight that must be considered in planning the level of physical and mental activity of crew members.

Continuation of the text in Annex 5.2 Other experiments One of the most important tasks onboard of the spacecraft making a long-term flight (as in mission Inspiration Mars) is to conduct scientific experiments using the forces of acting crew. Since the amount of space missions with high duration is limited, verification of already carried out experiments is required. It is also possible to conduct new experiments, the design of which will be specially made for mission Inspiration Mars.

Proposed concept of experiments may be divided into three groups: - Psychological and psychophysical studies - Sanitation and microbiological studies - Operational and technological research

Psychological/psychophysical studies We have three main areas of research during the ﬂight of a manned expedition to Mars:

1. Maintaining the psycho-emotional state, general and professional mental health during over than 520 days of the expedition;

2. Ensuring eﬀective intragroup interaction in a multicultural crew;

3. Crew interaction with the Control Center in the long-term autonomous flight with the increasing communication delay. On the basis of tasking programs of psychological experiment Mars-500 and current requirements and the needs of the mission crew Inspiration Mars, we can formulate the following tasks to be flown: - Assessment of mental and emotional state, mental performance and alertness level crew members; - Study of the features of the crew communications with the outside world with the limitations (communication delay) of the inherent flight to Mars; - Study of the processes of group and individual adaptation to the 501-day isolation (and checking the results of the experiment Mars-500 with 520-day isolation); - Study of personal values and relationships in pairs; - Study the professional skills of the operator’s activity under 501-day isolation (and checking the results of the experiment Mars-500 with 520-day isolation);

40 - Development of new tools psychological support developed based on virtual reality technology; - Study of the inﬂuence of diﬀerent means psychological prophylactics (including the presence on board of higher plants) to optimize the psychophysiological status of the crew members; - Study of the role of unconscious psychophysiological reactions in adaptation to prolonged isolation.

In psychological and psychophysiological studies regularly examines the state of higher mental functions, mechanisms of emotional stress, the eﬀectiveness of control methods of mental performance, especially intra- and interpersonal dynamics and crew communications with the outside world, the state and dynamics of professional management skills to the exact process benches and simulators.

We will investigate the state of operator functions, types of resistance responses to stres- sors activities. We are going to study the effectiveness of the influence of regular exercise on autologous classical techniques on the psychophysiological state of operators during the sessions of the test control at all stages of the experiment. During the Mars-500 experiment were observed the manifestations of ”problems of the way home”, compounded by mental asthenia on the background of sensory deprivation and monotony. We should expect the corresponding effects in the mission Inspiration Mars, perhaps exacerbated by the lack of physical possibility of withdrawing from the mission ahead.

Sanitation and microbiological studies In hygienic and microbiological studies will be examined the dynamics of changes in habitat conditions, cyclical changes in its toxicological and hygienic characteristics, prognostic signiﬁcance of changes and their causes.

Operational and technological research In operational and technological research conducted study of growth and plant life in a closed volume with given environmental conditions by installing and maintaining greenhouses with growing number of plants as elements of psychological support. Conducted development of methods and means of providing medical help in case of emergency, medical monitoring, telemedicine means of medical monitoring and diagnostics. We study a number of new funds for sanitary control environment.

Psychological support As psychological support of the crew we will use the same methods and tools that on ISS (books, movies, music, news and reviews, etc.). Means of psychological support will be established after taking into account the opinion of

41 each member of the crew and loaded prior to the mission. Surveys of news will be transmitted three times a week over a computer network.

6 Quick start guide

In accordance with the Regulations, the beginning of candidates selection for cosmonauts is the moment of placing online MVK solution to hold it. Relevant notice on the site should contain information on the timing and form of statements and documents participating in selection, amount of astronaut candidates, conditions and order of selection. According to the following terms, ”applicant for selection” is a citizen of Earth, whose application to participate in the selection of candidates for the astronauts is accepted by Commission of the competition. ”Candidate” is a person selected from among applicants for selection for training for manned flight at the approved program. Applicants for selection are persons whose applications for participation in the selection with a package of supporting documents were accepted by the Competition Commission before the deadline. Applicants are considered qualified in case MVK has chosen them the best in performing professional astronauts activities. The Regulations introduce some serious limitations for applicants: their age should not exceed 33 years. Applicant may be declared unfit for further selection for non-compliance of any of its specified requirements (criteria). In this case into the selection of candidates for the astronauts persons against whom criminal proceedings are pending are not allowed; having unexpunged (outstanding) conviction as well as violation the legislation of their country for the Protection of State Secrets are unfit too.

The document sets out the requirements to be met by applicants: • requirements for education, professional qualiﬁcations and experience of applicants • medical requirements • moral and psychological demands • requirements for physical ﬁtness • requirements for professional competence

Applicants are required to have higher education (”bachelor”, ”graduate” or ”master”) in engineering or medical specialty, with priority in the selection of persons with experience in the aviation and aerospace industry. Applicants must have work experience of at least 5 years, with at least 3 years of working in one place. Pilots and test pilots need to have higher education and proficiency flight not less than third class, and also not less than 3 years of experience in flight (service) in the organizations associated with the operation, use, testing or aviation and space technology.

Noteworthy is the Regulation’s requirement that military experts who have successfully passed the selection can be enrolled in the astronaut force only after leaving the military. Requirements for the medicine, determining the degree of life - be astronauts are set out in the Regulations on Medical Examination and monitoring the health of candidates for the

42 astronauts, astronauts and astronauts instructors.

During selecting applicants for compliance with the requirements of the psychological qualities of the candidates are evaluated in: • personality: individual psychological temperament, individually-typological, character traits, the type of higher nervous activity, abilities, needs, attitudes, motives, etc.; • professionally important psychological: memory, attention, thinking, perception; • moral: moral values, attitudes towards people, willingness to self-improvement, etc.; • socio-psychological: the ability to interact interpersonal positively, tolerance and proneness to conﬂict. • be evaluated intellectually creative potential applicants, including cognitive and creative activity, the willingness and ability to learn. • with the use of test methods are also investigated psychological immunity, ability to work under time pressure, cognitive behavior, etc. • in selecting applicants for compliance with the moral and ethical requirements evaluated are: • biographical data, including information about the identity of the candidate and his family; • training and employment, including data on the behavior, activities and relationships in the team; • motivation for choosing a new profession; • features and behavior in normal and emergency situations; • bad habits, etc.

Continuation of the text in Annex 7 Mission control center

1. Simulator spacecraft (SC) should be a testing and training mean for the Mission Control Center (MCC), and provide compliance testing , accuracy and completeness related to spacecraft operating procedures . The simulator must also provide an eﬀective means of testing the readiness of the ground control in terms of its basic functions for processing telemetry, telecommand preparation and delivery , and display data.

2. SC model should accurately represent the characteristics of the SC, as they are controlled by the Operator SC MCC in all phases of flight. For Interplanetary manned spacecraft (IMS) control must create a computer model, as well as ground-based analogue ship for flight simulation and possible emergency situations on board, as well as to find ways of countering them when they occur.

3. For the purpose of receiving and inspection of the simulator must be ensured that possible tracking to record all necessary data for oﬄine analysis. Suitable autonomous service analysis should also be provided.

4. The simulator must provide mode of operation in which it left with the duty not later

43 than 2 minutes after, as well as to respond to the simulation commands issued by the operator from the keyboard for 2 seconds. The simulator must respond to the request operation for 5 seconds.

5. Need to develop software for spacecraft control, including software simulator, put it in the DRM software and debug if the use of such software is required on the operational and technical documentation (OTD) on the management of SC.

6. To control the spacecraft can be used by MCC and other available funds of the Central Research Institute of Machine Building (CRIMB).

7. MCC should contain all the necessary equipment and software to perform the tests in orbit and normal operation. MCC should in particular contain a means for processing and display telemetry data check instruction before sending, validation program execution command, receiving telemetry data and management data for analysis of anomalous situations, the initiation of the measurement range and the angle of observation and motion control SC the orbit and its orientation, due to the management stations and receiving TMI and landﬁll run.

8. When operating the spacecraft must not have potential single failure points, ie during normal operation should not be the potential deterioration of the spacecraft or its satisfac- tory operation by unauthorized issuing any command.

9. There should be no potential to cause irreparable damage to the spacecraft by the erroneous granting aboard one telecommand.

10. Must be capable of continuously transmitting telemetry information about the current state of the spacecraft at the expense of the GCC for the duration of active existence.

11. It shall be possible to lock the team work with ground control (GC) all automatic devices. Any deviation from this requirement must be explained.

12. It shall be possible to lock the team with GC any equipment having a waiver of any automatic connections that may occur in the future, including in survivability mode.

13. It must be possible, as a means of overcoming unforeseen circumstances, any lock -board control mode using either the new regime loaded in the onboard computer with NFC, or by using the control mode by commands from the GCC, in which data is read from the respective sensors and control signals are generated for relevant executive bodies.

Due to the fact that the IGC ﬂight passes at a considerable distance from the Earth to communicate with the crew and obtain telemetric information from the board, as well as transfer of control commands to be used aboard Ground stations receiving suﬃcient power and covering all the space around the Earth. For this purpose, suitable antenna American Network Deep Space Network, which currently provide a link with a lot of automated vehi-

44 cles, studying objects in the solar system, including AMC ”Voyager 1” , which reached the borders of our system.

8 The cost of the mission

Analyzing this table, we concluded that Proton-M and Soyuz-FG are the most suitable carrier rockets for the mission. Our project includes five launches of Proton-M which will carry four booster blocks Breeze-M and IMS to the LEO as well as one launch of Soyuz FG to deliver the crew to the IMS. The choice of these rockets was made due to several aspects: 1) Proton-M and Soyuz FG are produced in Russia and have the Russian Baikonur Cosmod- rome as the launch site. This fact is reflected in their cost in best way for us. 2) Proton-M in its current modifications has been used since 2001 (10-12 launches per year) and currently has an excellent statistics of successful launches (91% successfull). 3) Today Soyuz-FG is the main mean of delivering astronauts to the ISS, as it has no more reliable (100% successful launches) and cheaper analogs.

45 According to our calculations, the approximate total cost of the mission is $ 1.3 billion, which is less than the initial evaluation of $3 billion given by Dennis Tito’s team by more than a half. Reaching the cost of only $1,3 billion became possible through the use of carrier rockets and equipment mainly produced in Russian and partly in Europe. These reduced the level of economic costs. The main expense items are the creation of the Interplanetary Manned Spacecraft and carrying it to the Mars ﬂyby trajectory.

9 Conclusion

Before summing up our work on the flyby mission within Mars Society International Student Design Competition, we would like to say few words about Inspiration Mars news. Due to the lack of financial support and delays in creating heavy and super-heavy-lift launch systems such as Falcon 9 Heavy and Space Launch System (SLS) it turns out that the flyby of Mars became almost impossible by the year of 2018. On the one hand, it is really disappointing as far as next such opportunity will only be available in 2031. Yet on the other hand, additional time for preparing the mission gives hope that NASA would possibly support a little longer flyby around Venus and Mars. We really look forward to such mission becoming real.

Returning to our work, we would like to say that we tried to fulﬁl the task laid upon us by the rules of the contest, that is to create a project of ﬂyby mission to Mars starting in 2018 using resources existing nowadays. The analysis done showed that among existing heavy-lift launch systems only Proton-M suits our mission. There is no surprise that exactly this system was chosen as basic for leading out modules of interplanetary space ship and accelerating blocks. Lack of super-heavy-lift launch systems led us to necessity of low-earth orbital joining with further leading out of a space ship on an interplanetary trajectory. Calculations proved that such approach can be brought to reality.

Unfortunately, accelerating block Briz-M, which we will be able to use, is not reliable enough. If we take exploitation reliability of accelerating block as 0.92, not taking in account any adaptations of the construction, and reliability of launch system as 0.975 then in case of five starts, not taking in account reliability of a space ship (if it does not break during the process of installation) we will have WHAT IS THAT (coefficient of reliability or what??) reliability coefficient equal (0.924) ∗ (0.9755) = 0.63. Still even such a low calculated reliability allows us to carry out the mission.

Of course, for real manned ﬂights the development of new space equipment will be es- sential, which follows from analysis of existing and developing means of leading out. As a base for our space ship we took a modiﬁed module of ATV ship, for in our opinion it mostly suits the demands of mass, capacity and reliability. Moreover, it’s main body is created by Italian company Alenia Spazio, which made major part of hermetically sealed modules for American segment of International Space Station.

46 We chose landing section from a manned ship Soyuz-TMA, however it requires further improvement of thermal shield to reach the second cosmic speed. Originally Soviet ships Soyuz were designed for the moon program. They flew around the moon and came back. The turtles aboard managed to return alive. Onboard systems, medical and scientific equipment are based on those made for space station Mir and ISS. These systems proved their reliability for more than a year long flights. The only complication our team faced is a lack of publicly available information about size, mass and cost of the systems. Thus we managed to make only approximate analysis and calculation of costs.

Anyhow, in first approximation the possibility of a flyby mission was shown by the work of our team. We are sure that the efforts spent are justified at least by the fact that young people all over the world would see what the humanity is capable of in moving further into far space and what difficulties will stand on our way there. Mars is an understandable goal for our civilization and we really hope that exactly our generation will make this important and meaningful step towards exploration of Solar system and further moving of humanity into space.

10 Sources:

1. Kosmicheskaya biology and medicine in 2 volumes. Volume 1. Medical support long- duration missions. State Scientific Center of the Russian Federation - Institute for Biomed- ical Problems of the Russian Academy of Sciences. 2. Baraboi LM - ”Ionizing radiation” - M.1991. 3. Budarkov SG - ”Radiobiological Handbook” - Moscow 1992 4. VM Petrov, VA Shurshakov Radiation Physics Research on the ISS during the period 2001 - 2008 were as follows: Experiment ”Matryoshka -R”. In the book. : Medical bio- logicheskpie research on the Russian segment of the ISS. 2011. T. 2. Pp. 389-426. 5. Shibanov GP Habitability and safety of space remaining in the man. M.: Engineering, 2007. - 544 p.: Il. 6. http://niichimmash.ru/projects/elektron-vm/ 7. http://papers.sae.org/2006-01-2092/ 8. http://niichimmash.ru/press/publications/regeneratsiya-vody-i-atmosfery-na-kosmicheskoy- stantsii-opyt-orbitalnykh-stantsiy-salyut-mir-i-mks-p/ 9. Space Biology and Medicine in 2 volumes. Volume 1. Medical support long-duration missions. State Scientific Center of the Russian Federation - Institute for Biomedical Problems of the Russian Academy of Sciences. 10. AV Vasin, E.A.Kobzev, Improving prevention of adverse effects of weightlessness during training astronauts. 11. http://www.nasa.gov/pdf/284273main Radiation HS Mod1.pdf 12. http://www.swpc.noaa.gov/SolarCycle/ 13. http://ligaspace.my1.ru/news/2013-02-24-434 14. Getselev IV Radiation situation on board the spacecraft Tsipko 2001. 15. Space Weather Effects on Humans: in Space and on Earth Proceedings of the Inter-

47 national Conference Space Research Institute, Moscow, Russia, June 4-8, 2012, Ed. A.I. Grigoriev, L.M. Zeleny

11 Team

Alexandr Khokhlov - Nikolay Shelakhaev - Nataliya Lakhvich - Saint Petersburg State The University of Applied Bauman Moscow State Polytechnical University; Sciences Wiener Neustadt; Technical University;

Olesia Dogonasheva - Saint-Petersburg National Anna Kuksa - Pirogov Anna Golovchenko - Research University Of Russian National Research Voronezh State University; Information Technologies, Medical University; Mechanics and Optics.

48 Alexander Farafonov Anna Pavlysh - State - Bauman Moscow State University of Saint- Ilya Ovchinnikov - Technical University; Petersburg; Moscow Aviation Institute;

Andrey Parfenov - Anton Matveev - Bau- State University of Saint- Daniil Prokopenko - man Moscow State Techni- Petersburg; Moscow Aviation Institute; cal University;

49 ANNEX