Indonesian Space Technology Innovation Research & Development

Indonesia Space Technology Innovation Research & Development

Add & Edited By:

Arip Nurahman
Department of Physics
Faculty of Sciences and Mathematics, Indonesia University of Education

and

Follower Open Course Ware at Massachusetts Institute of Technology
Cambridge, USA
Department of Physics
http://web.mit.edu/physics/
http://ocw.mit.edu/OcwWeb/Physics/index.htm
&
Aeronautics and Astronautics Engineering
http://web.mit.edu/aeroastro/www/
http://ocw.mit.edu/OcwWeb/Aeronautics-and-Astronautics/index.htm

Space technology is technology that is related to entering space, maintaining and using systems during spaceflight and returning people and things from space.

"Every day" technologies such as weather forecasting, remote sensing, GPS systems, satellite television, and some long distance communications systems critically rely on space infrastructure. Of sciences astronomy and Earth sciences (via remote sensing) most notably benefit from space technology.

Computers and telemetry were once leading edge technologies that might have been considered "space technology" because of their criticality to boosters and spacecraft. They existed prior to the Space Race of the Cold War but their development was vastly accelerated to meet the needs of the two major superpowers' space programs.

While still used today in spacecraft and missiles, the more prosaic applications such as remote monitoring (via telemetry) of patients, water plants, highway conditions, etc. and the widespread use of computers far surpasses their space applications in quantity and variety of application.

Space is such an alien environment that attempting to work in it requires new techniques and knowledge. New technologies originating with or accelerated by space-related endeavors are often subsequently exploited in other economic activities.

This has been widely pointed to as beneficial by space advocates and enthusiasts favoring the investment of public funds in space activities and programs. Political opponents counter that it would be far cheaper to develop specific technologies directly if they are beneficial and scoff at this justification for public expenditures on space-related research.

Contents 1 Specific space technologies 2 Future space technologies 3 See also 4 External links

Specific space technologies

• Ablative heat shield
• Aerobot (Planetary probe suspended in atmosphere.)
• Atmospheric braking
• Booster See also ICBM
• Centrifuge
• Gantry
• Human staffed missions
• Interplanetary Internet
• Isolation chamber
• Lander
• Launch pad
• Reentry
• Real time
• Rocket
• Rocket sled
• Rover
  
  
  • Lunar Rover
  • Mars Rover
• Satellite
  
  
  • Communication satellite
  • Earth observation satellite
  • Navigation satellite
  • Space observatory
  • Satellite television
  • Telecommunications satellite
  • Weather satellite
• Spacecraft
• Spacecraft propulsion
• Space probe
  
  
  • Aerobot (Planetary probe suspended in atmosphere.)
• Space shuttle
• Space station
• Space suit
• Space capsule
• Splashdown
• Telemetry
• Thruster

Future space technologies

• Asteroid mining
• Single stage to orbit
• Solar power satellite
• Non-rocket spacelaunch
• Space manufacturing
• Suitport

See also

• Acid leaching
• Asteroid mining
• Self-replication
• Space-based industry
• Space colonization
• Space elevator
• Spacelab
• In-Situ Resource Utilization

External links

• PERMANENT — near-term space resource utilization
• Space Studies Institute
• Manufacturing in space
• SKYLAB: A Guidebook (see Chapter 5, section 4)
• Space-age welding
• Spacehab
• Wake Shield Facility program
• Lunar Boom Town A role playing study group at Wikiversity where participants plan and study future space ventures.

Oscilloscope

A physics lab demo of the oscilloscope.

Space Exploration Nuclear Engine

Design of a Sodium-cooled Epithermal Long-term Exploration Nuclear Engine

Author:
P. Yarsky, A.C. Kadak, and M.J. Drisco

Edited and Add By:



Arip Nurahman
Department of Physics
Faculty of Sciences and Mathematics, Indonesia University of Education

and

Follower Open Course Ware at Massachusetts Institute of Technology
Cambridge, USA
Department of Physics
http://web.mit.edu/physics/
http://ocw.mit.edu/OcwWeb/Physics/index.htm
&
Aeronautics and Astronautics Engineering
http://web.mit.edu/aeroastro/www/
http://ocw.mit.edu/OcwWeb/Aeronautics-and-Astronautics/index.htm














 

Abstract

To facilitate the mission to Mars initiative, the current work has focused on conceptual designs for transformational and enabling space nuclear reactor technologies. A matrix of design alternatives for both the reactor core and the power conversion unit were considered. Based on a preliminary screening of technologies using simplified analyses, a conceptual design was established for more detailed design work.

The boiling sodium Rankine cycle was selected for the power conversion unit, and the reactor core is an ultra high power density core with highly enriched uranium fuel. The sodium Rankine cycle has many advantages, lending to a highly efficient radiator and compact reactor core. The sodium-cooled, epithermal long-term exploration nuclear engine (SELENE) is designed to be scalable to meet many differing mission requirements.

The SELENE core is a comprised of Nb-1Zr clad, lead bonded, UC plates in a honeycomb pattern. The fuel plates are arranged into a rectangular grid, roughly 25cm on each end. The fuel is in two zones, one is 97 a/o enriched in 235U and the other is 70 a/o enriched in 235U. The core is a fast spectrum reactor, BeO reflected, and ex-core controlled. Three designs are proposed, the first is for a 10 MWth /1.0 MWe Low Temperature (1300 K) system (SELENE-10-LT) and the second for a 10 MWth /1.2 MWe High Temperature (1500 K) system (SELENE-10-HT) and the third for a 27 MWth 12.6 MWe system (SELENE-30).

All of these designs utilize essentially the same system architecture. Three designs are proposed so that low power variants can be used to verify the technology and develop experience. The reactor systems may then by uprated to a higher power level. The system lifetime is 9 effective full power months, corresponding roughly to a single trip from Earth to Mars and back