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Physical Design
 
 
 
 
 

 
 
Physical Design
 
 
Considerations were taken into account when decided the physical design of the satellite. Its dimensions are 3m x 4m x 4m to account for the size of the large gain antenna and to house its various systems. Together, all of the components weigh 978kg. Since the 3m high gain antenna must point back to Earth when the satellites are orbiting Mars, it makes sense to orient the satellite with the antenna pointing away from the surface. Opposite of the high gain antenna should be the sensors for looking at the surface as well as the conical antenna for inter-satellite communication and MPS signal broadcasting. The four sets of thrusters should be equally spaced on the sides of the satellite and each should have their own tank of hydrazine. Based on the amount of hydrazine required and its density, each spherical container should have a radius of 28.8cm.
 
 
Weight Distribution
 
 

Item

Weight (kg)

RTG

107.5

Dish Antenna

100

Conical Antenna

0.5

Electronics

20

Housing

125

Attitude Control System

75

Propulsion System

150

Propellant

400

Total

978

 
     
 
Figure 2: MPS Satellite
Figure 2: MPS Satellite
 
 

Figure 3: MPS Satellite cutaway
Figure 3: MPS Satellite cutaway
 
     
   
     
 

References

[1] T. Pratt, C. Bostian, and J. Allnutt, Satellite Communications, Edition 2, New York: John Wiley & Sons, 2003.

[2] G.L. Bennet, “Space Nuclear Power: Opening the Final Frontier,” 4th International Energy Conversion Engineering Conference and Exhibition (IECEC), 2006. [Online]. Available: http://www.fas.org/nuke/space/bennett0706.pdf. [Accessed: December 6, 2008].

[3] G. Maral and M. Bousquet, Satellite Communication Systems: Systems, Techniques, and Technology, Edition 4, New York: John Wiley & Sons, 2002.

[4] T.B.H. Kuiper and G.M. Resch, “Deep Space Telecommunications,” Jet Propulsion Laboratory: California Institute of Technology, 1999. [Online]. Available:http://www.astron.nl/documents/conf/technology/tech08w.pdf. [Accessed: December 6, 2008].