Mars Reconnaisance Orbiter (MRO)

USA


International Sat. n°:

USA satellite n°:


Launch data:

Designation  28788 / 05029A
Launch date  12 Aug 2005 - 11:43 UT
Launch site CC, SLC-41
Launch vehicle  Atlas-5(401) (s/n AV-007)
Mission  Mars orbiter
Heliocentric orbit
Perihelion / Aphelion  
Incl. to ecliptic  °
Period   min
To Aerocentric orbit

Artist's concept of the Mars Reconnaissance Orbiter. Credit: NASA/JPL-Caltech



Spacecraft data:

Prime contractor  Lockheed Martin Space Systems, Denver
Operator Jet Propulsion Laboratory, Pasadena, Calif., for NASA's Science Mission Directorate, Washington
Platform  
Mass at launch  2180 kg
Dry Mass  kg
Basic shape  
Dimension  
Solar array  
Equipment HiRISE, CTX, MARCI, CRISM, MCS, SHARAD, Electra
Propulsion six 170 N MR-107N monopropellant engines
Orbit Heliocentric, then Mars orbit

Description:

The Mars Reconnaissance Orbiter (MRO) will make high-resolution measurements of the surface from orbit. It will be equipped with a visible stereo imaging camera (HiRISE) with resolution much better than one meter and a visible/near-infrared spectrometer (CRISM) to study the surface composition. Also on board will be an infrared radiometer, an accelerometer, and a shallow subsurface sounding radar (SHARAD)  to search for underground water.

Cameras:

Spectrometer:

Radiometer:

Radar:

The orbiter will also be used as a telecommunications link for future missions (Electra UHF radio).

MRO has 1196 kg of hydrazine propellant, with six 170-Newton MR-107E Aerojet thrusters and six smaller 22-Newton MR-160E thrusters. The mutiple engines provide propulsion for course correction and Mars orbit insertion.


Mission details:

External links:


Ref.: #3,,#7(JR552-562,570,621), #12, #81 - update: 30.01.22 Home