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Space Seed is an ideological experimentation of a digital afterlife management system for future planetary inhabitants. It's using speculative design to investigate and reverse engineer the Panspermia theory.

This sophisticated apparatus will engineer our digital life data into special bacteria or extremophiles in which our digital afterlife, our wishes for the next life and our biological identity are encoded.

A capsule will protect these bacteria and follow its deep space journey towards a target planet.

Space Seed conserves the memory of each individual of our technological civilization and provides a record for any future inhabitants or visitors to understand the Planet Earth and its ancient civilizations. It is just like a message in a bottle thrown into the ocean: Space Seed is an open message for the visitor of the future.

The new circle of Panspermia has finished its reverse engineering process and is patiently waiting for our future planetary descendants to discover its origin.

This project is intended to immerse the audience into the world of speculative questioning and to challenge the definition of life, its origin, its present, and future.

Research & Making process short Documentary

(watch on computer for better resolution)


Spacecraft design software/hardware : 

 Check these tomorrow:


  • Ref :   

NASA 3D model :


Simulating spacecraft system


Similar project:

Version 3 :   Components:  


How to build an sustainable Mini biosphere 

1, Mini biosphere protection for extraterrestrial environment.

(a device with dried bacteria or tardigrade will no need cosmic ray protection?) ( Pseudomonas aeruginosa andStaphylococcus aureus.)


Make the Maple seed, someone did that before.




1, Energy   

  •    Principle energy source 1 :  Radioisotope

  •  Advanced Stirling Radioisotope Generator

A.  Multi-Mission Radioisotope Thermoelectric Generator 



CNC Machine&other

selective deposition lamination/



 Get the video resource here (



 Radioisotope thermoelectric generator (+) --hydrogen energy (Deep space mission )- Nuclear power plants

  •  The MMRTG design is capable of operating both in the vacuum of space and in planetary atmospheres, such as on the surface of Mars. Design goals for the MMRTG included ensuring a high degree of safety, optimizing power levels over a minimum lifetime of 14 years, and minimizing weight.[2]




Construction :  


Insulation maybe be used to thermally isolate the radiator panel from the spacecraft.


Material Choices:

+ Material of this Radiator fins: stiffened aluminum plate (source:


+ Carbon fiber (insides of the cube made from this to provide strength). Surrounded by thin titanium/aluminium layer.. and finally a coating of heat resistant material. 

Strong materials that can handle and distribute the temperature and pressure of  space and other planets. Spacecraft shielding is defined as the outer layer of a satellite or spacecraft that protects it against micrometeorite and orbital debris (MMOD), radiation damage, and re-entry temperatures. 

aluminium shielding, hydrogen-rich plastics and rare-earth-doped rubber are effective in attenuating cosmic rays to make Electromagnetic interference (EMI) shielding and thermal management.

The tensile strength of carbon nanotubes greatly exceeds that of other high-strength materials.








   Extra energy source 2: 

   B. Solar Cells   (on the wing) and  Open mechanism

Solar panel deployment engineeringreference: 


Origami to expanding surface :

Great deployment and explanation:

This solar Array is massive!!! how beautiful it is!  ( 

EUTELSAT is a French satellite provider,


Carbon Fiber :

Apply colours on alumminum Anodizing. 



A folding solar panel that could adapt the Spindle-shaped space craft, while landing on the surface of the planet, the solar panel deployed and open, it also function as a deceleration device to slow down the speed of space craft. With the add of an parashute system, this design could possibly success to landing on the surface avoid crash caused damage of the space craft. An umbrella form solar panel is an possible solution for such a space craft. 


Solar panel deplooyment patent





Other interesting projects:

Parts CAD drawing



  • The most common material in current designs is aluminized 2 µm Kapton film. It resists the heat of a pass close to the Sun and still remains reasonably strong. The aluminium reflecting film is on the Sun side. The sails of Cosmos 1 were made of aluminized PET film (Mylar).

2, Navigation 

  • a, Navigation and Guidance system --- Option 1 


Galactic Positioning System----


  • Many reasonable distance (untold billions of stars) are known and mapped and you can imagine using this data to fix your position. You can imagine a spaceship having a database of positions and brightnesses (magnitudes) which could be used to triangulate



  • EXTRA: solution 2 have detail information and could find relative materials that we searching before.  You could learn all the component from a cubesate and accordingly add and create new component needed. These component is also easily find on electronic market and even make a prototype. An modified and advanced design is required since what you are looking is pretty old version. 

    1. Navigation and Guidance system ---- Option 2  Link1,

        • Star tracker : 

                A Star tracker is like this

 Some similar startracker design

Star tracker on ESA instrument.



  • Minature star tracker

    • Sun sensor





  • --------

  • (Just for the story: I'm beginning to understand how the "crasy pulsar" came around and how important all this can be for you Yu)




3, Ion Thrusters

To make this : 



  • Alexey : he told me if we use a wing structure to release the heat, so basically could also use copper and some pipes for the wing structure design, and then print it all black

Nassikas Superconductor thruster :




Distance Measurement :

This Damn website is for Nuclear weaspon archives :



4, Seed Propeller & Wing  

General form

References :


Interior structure and making:




Air Chamber 

(Bacteria could store inside the tube, After landing, while installed sensors detected the suitable exterieur environment condition, the Valve of this device open up automatically and spreading the bacteria.​


3, Docking system Model 

     (Low impact docking mechanism)



    rocket stage separation mechanism(


4, Interferometers  

  • (Different interferometers exist, which one? is it useful?)


        • green laser diode

        • single surface mirror

        •  A beam-splitter



 5, Reaction wheels (4 of them) / Gyroscopes



 An electrically-powered wheel aboard a spacecraft. Typically, three reaction wheels are mounted with their axes pointing in mutually perpendicular directions. To rotate the spacecraft in one direction, the appropriate reaction wheel is spun in the opposite direction. To rotate the vehicle back, the wheel is slowed down. Excess momentum that builds up in the system due to external torques must be occasionally removed via propulsive maneuvers. 


One of Kepler’s reaction wheels, manufactured by Goodrich Corporation.  The reaction wheels are gyroscopes that keep the Kepler spacecraft pointing in a fixed direction.  The telescope, which has four reaction wheels, requires three to be operational at a given time to maintain its stable pointing. (Source:


Video examples:






5, Parachute system(? necessary?) 

Parachute system placement research reference:

Structure example :


Orion project parashute:



Parashute examples:


6, Temperature sensor

( to place in different location )




(cubesate communication system)

Open source network /connection system :

Sigfox, reseaux bas debit!/about


      (Cubesate use small chips for ground communcation)

  • Communication system could consider to use the Swisscube , it's small and efficient.


        • Design decisions:

          1. A signal transmission/relay system that communicates to these seeds and transmits back info to earth via satellite. This would ensure the size of the seeds remains minimal, as well as we are kept informed about the current status of the seed and if it has been planted.

          2. The seed itself is sent to the planet through a slingshot mechanism, to a pre-decided location, say on Mars (decided on bases of high resolution pictures taken), ensuring  the size of the seed remains minimal, and no motor-mechanism is need for it to be 'planted' in a specific location. It then would communicate back using an idea like Project Loon (from Google). Every now and then, these floating balloons would  communicate with the seeds when in range, and then would relay their status. The floating balloons/drones (flying actually, since there's no constant wind source on Mars as on Earth), would transmit the status to satellites with short radio bursts, ensuring energy efficient communication.

          3. They are planted by the people going to colonize Mars :)

          4. ?



8, Landing and instrument deployment :

Amazing animation with a lots of details  (Mars Curiosity)

Landing details :


9, complete composition :


10, Material Choices:

  1. Carbon fiber (insides of the cube made from this to provide strength). Surrounded by thin titanium/aluminium layer.. and finally a coating of heat resistant material. 

  2. Strong materials that can handle and distribute the temperature and pressure of  space and other planets

  3. Spacecraft shielding is defined as the outer layer of a satellite or spacecraft that protects it against micrometeorite and orbital debris (MMOD), radiation damage, and re-entry temperatures. 

  4. aluminium shielding, hydrogen-rich plastics and rare-earth-doped rubber are effective in attenuating cosmic rays to make Electromagnetic interference (EMI) shielding and thermal management.

  5. The tensile strength of carbon nanotubes greatly exceeds that of other high-strength materials.




References :  





Space craft components references:



DIY Satellite

Solar tracker:

DIY Space program

Spy satellite:


Related references that been discovered during the research 

  • The DIY Arduino Telescope GOTO control project




NASA Open data:,%20et%20al.pdf



3D printing stuff

1, 3D printing : shapeway :


Le monde 3D :!frimpression-3d/c8nv



Version 2 : 

Steps, functions & Parameters

Mini biosphere need to protect 

  1. temperature

  2. humidity 

  3. light

  4. radiation levels

Traveling into deep space

  1. Propulsion 

  • Variable Specific Impulse Magnetoplasma Rocket

  • Electrically_powered_spacecraft_propulsion?

  • Ion Beam propulsion ( particals accelerated using an electrical field ) this means low acceleration but high final velocity. 

  • Chemical propulsion in order to leave earth orbit(actual)

  • Laser-driven light sails

  • Radioisotope thermoelectric generator (+) --hydrogen energy (Deep space mission )




  1. Sustainable Energy system/ Batteries

    • Radioisotope Thermoelectric Generator(far from the sunlight).

    • Photovoltaic cells

    • Nuclear Reactor with different power conversion principles then RTGs ( not sustainable but has a long lifetime )

  2. high temperature resistant / Low temperature protection external shell internal shell 

High temperature --

3, High radiation protection exterior shell and interior shell(for dry bacterias).

Landing in low planetary orbit

  • Parashut system

  • Altimeter ? A device that measures altitude above the surface of a planet or moon. Spacecraft altimeters work by timing the round trip of radio signals bounced off the surface.)

Penetration to the surface

  • Drilling system

detect the environment (temperature, light, air, water/humidity)

-------Check all the sensor working with Arduino

  • Sensors

    • Sun/light sensor/optical sensors  ( With arduino) 

      • Polarimeter: An optical instrument that measures the direction and extent of the polarization of light reflected from its targets.

      • Photometer: An optical instrument that measures the intensity of light from a source.

    • Water/humidity sensor

    • Temperature

    • Soil composition/Soil moisture sensor 

    • Gas composition sensor  (atmospheric composition and air quality)

    • Radiation sensor

    • Plasma detector: A device for measuring the density, composition, temperature, velocity and three-dimensional distribution of plasmas that exist in interplanetary regions and within planetary magnetospheres.

    • Radiation sensors 

    • Cosmic ray detection? 




Different parameters








This file include some files of 2 spacecrafts from Copenhagen Suborbitals and NASA.


1. Steps & Function Requirement: 




Mars Rover landing steps:


Reference :

Example Mars Rover----- 

Suppose landing step from 

Step Fourteen: Bridle is cut and first impact occurs


  • ------Insert step of Seeds spreading------

At about the height of a four-story building and three seconds before landing, the bridle is cut and the vehicle freefalls to the surface. The mass of Spirit and its lander is about 544 kilograms (1,200 pounds).

  • ------

Final Landing Stage

Step Fifteen: Lander rolls to complete stop



The rover, protected by its lander structure and airbags, could bounce up to four or five stories high and roll as far as 1 kilometer (0.6 miles) across the martian surface before it comes to a complete stop around 8:45 pm PST.





  • Enter the soil


 (Spacecraft Parameters 

  • Telemetry, Tracking, and Command, Communication,Power,Thermal,Propulsion)


Target planet : Mars Environment data +Mars Envionment condition 


2. Parameters and content 

Source 1 , Source 2


  • Astronautics and Space Environment 

How those elements will influence the device:

Solar system, two-body problem, orbits, Hohmann transfer, rocket equation, space environment and its effects on space systems, sun, solar wind, geomagnetic field, atmosphere, ionosphere, magnetosphere. 


  • Thermal and Statistical Systems

Thermodynamics and statistical mechanics; kinetics of atoms, molecules, and photons; compressible fluid dynamics.  

  •  Astronautics and Space Environment II 

spacecraft dynamics, Euler's equation, space plasma physics, spacecraft in plasma, radiation effects on space systems, space instrumentation: detectors, analyzers, spectrometers.

  • Space Mission Design 

  • Molecular Gas Dynamics 

Physical description of kinetic nature of gas flows; distribution function; introduction to the Boltzmann equation; free-molecular flow; surface and molecular reflection properties; Monte Carlo flow calculations. 

  •  Spacecraft Propulsion 

rocket engineering. Space missions and thrust requirements. Compressible gas dynamics. Propellant chemistry and thermodynamics. Liquid- and solid-fueled rockets. Nuclear and electric propulsion. 

  • Spacecraft Dynamics 

Two-body motion, rigid-body motion, attitude dynamics and maneuvers, spacecraft stabilization: gravity gradient, reaction wheels, magnetic torques, thruster attitude control.  

  • Physical Gas Dynamics

a: Molecular structure; radiative processes; microscopic description of gas phenomena; translational, rotational, vibrational, and electronic freedom degrees; particle energy distributions; microscopic representation of thermodynamic functions. 

b: Kinetic concepts in gas physics; thermal non-equilibrium; intermolecular potentials; transport of radiation and particles in high-temperature gas; dissociation and ionization equilibrium; energy relaxation. 

  • Spacecraft System Design 

System components; vehicle structure, propulsion systems, flight dynamics, thermal control, power systems, telecommunication. Interfaces and tradeoffs between these components. Testing, system reliability, and integration.  

  • Design of Low Cost Space Missions 

check all aspects of space mission design for practical approaches to reducing cost. Examines "LightSat" mission experience and potential applicability to large-scale missions.

  • Space Studio Architecting

Programmatic/conceptual design synthesis/choice creation methods for complex space missions. Aerospace system engineering/Architecture tools to create innovative projects. Evaluated by faculty/industry/NASA experts.  

  • Space Environments and Spacecraft Interactions

Space environments and interactions with space systems. Vacuum, neutral and ionized species, plasma, radiation, micrometeoroids. Phenomena important for spacecraft operations.

  • Partially Ionized Plasmas

Check microscopic processes involving particles and radiation, and their impact on properties of high-temperature gases and plasmas in local thermal equilibrium and non-equilibrium.

  • Computational Techniques in Rarefied Gas Dynamics

Particle-based computational simulation methods for rarefied, high-speed flows. Molecular collision kinetics. Monte Carlo direct simulation and related techniques.  

  • Spacecraft Thermal Control 

Spacecraft and orbit thermal environments; design, analysis, testing of spacecraft thermal control system and components; active and passive thermal control, spacecraft and launch vehicle interfaces. 

  • Systems for Remote Sensing from Space 

The operation, accuracy, resolution, figures of merit, and application of instruments which either produce images of ground scenes or probe the atmosphere as viewed primarily from space. 

  • Spacecraft Sensors 

Spacecraft sensors from concept and design to building, testing, interfacing, integrating, and operations. Optical and infrared sensors, radiometers, radars, phased arrays, signal processing, noise reduction. 

  • Spacecraft Structural Dynamics

Applied analytical methods (vibrations of single and multi degree of freedom systems, finite element modeling, spacecraft applications); requirements definition process; analytical cycles; and design verification. 

  • Spacecraft Structural Strength and Materials

Spacecraft structural strength analysis and design concepts overview; spacecraft material selection; analysis of composite materials; finite element method; spacecraft configuration; structural testing; bolted joint design.  

  • Liquid Rocket Propulsion

Liquid-propelled rocket propulsion systems. Capillary devices for gas-free liquid acquisition in zero gravity. Ground and in-orbit operations. Propellant life predictions and spacecraft end-of-life de-orbiting strategies. 

  • Advanced Spacecraft Propulsion

Nuclear, electric, sails, and far-term propulsion systems. Overviews of nozzles, heat transfer, electromagnetics, rarefied gases, and plasma physics. Analysis of electrothermal, electrostatic and electromagnetic thrusters.  

  • Orbital Mechanics I 

Physical principles; two-body and central force motion; trajectory correction maneuvers; position and velocity in conic orbits; Lambert's problem; celestial mechanics; orbital perturbations.

  • Orbital Mechanics II 

Theory of perturbations of orbits; numerical methods in orbital mechanics; satellite dynamics; averaging methods; resonance; mission analysis.  

  • Space Navigation: Principles and Practice 

Statistical orbit determination: (weighted) least squares, batch and sequential (Kalman) processing, illustrative examples; online ephemeris generation: potentially hazardous asteroids, comets, satellites; launch: vehicles, payloads, staging.  

  • Spacecraft Power Systems

Introduction to solar arrays, batteries, nuclear power sources, mechanical energy storage. Application theory of operation, practical considerations. Subsystem topologies and performance. Design optimization techniques.  

  • Spacecraft Attitude Control

Review of attitude dynamics, gravity gradient stabilization, attitude stabilization with a spin, attitude maneuvers, control using momentum exchange devices, momentum-biased stabilization, reaction thruster control. 

  • Spacecraft Attitude Dynamics 

Dynamics of systems of particles and rigid bodies; spacecraft attitude systems; attitude maneuvers (spin, precession, nutation, etc.); attitude stabilization and attitude determination; simulation methods.



3. Component examples

Examples One 

Capsule testing priorities

  • Re-entry dynamics testing (the capsule will perform atmospheric re-entry like the full scale capsule if having the same ballistic coefficient – requiring the small 2x-capsule to have a mass of app 80 kg.)

  • Ballute testing (the capsule is stabilized during supersonic re-entry when having a ballute deployed).

  • Thermo-data (the capsule will be fitted with thermo-couplers on the inside to measure energy impact of the capsule from top to bottom during the entire mission).

  • Heat shield (We will conduct heat shield testing on top of the capsule, for the ascent-phase, and bottom, for the descent phase. As always we are using cork for this).

Capsule construction

  • General construction made from aluminum for better calculation energy impact and distribution (final capsule is being from aluminum as well).

  • Open fitting architecture. (The large amount of electronics and avionics such as GPS-antenna, comm-antenna, cameras, batteries, sequencers etc. are still not totally known. We have created a main structure which provides an easy way to install this later.)

  • All cover plates created for easy change and removal.

  • Unpressurized

  • Main diameter 630 mm and 80 kg total mass.

Capsule subsystems list

  • Ballute (supersonic re-entry drogue for stability)

  • Drogue (deployed in lower part of the atmosphere until splashdown at app 11 m/s)

  • Float-bladders x 4 (making the capsule float post splashdown)

  • Cameras x 2 (recording the event and providing life coverage during flight. Installed in top part of capsule to avoid aerodynamic heating)

  • Com-antennas x 4 (for up- and downlink of data, video and commands) (

  • Avionics main box x 4 (for all internal electronic controls of capsule systems)

  • Sustainable energy providing system---------?Battery NiMH x 2 (2 main pack of batteries for all systems installed in the bottom)

    • Solar energy

    • Bioenergy

    • Photovoltaics

    • Artificial_photosynthesis?

    • Quantum Zero Point Energy?

    • Nuclear energy

    • Laser beam energy

  • GPS-antennas (for general positioning)

  • Chute-gas (gas-tank and inlet for inflating chute-chamber in order to deploy ballute)

  • 3-ring-system (classic 3-ring system to release ballute and deploy drogue)

  • Launch vehicle interface (3 lower structures for holding the capsule to the launch vehicle)

  • Thermocouples (for internal point temp measurement)


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