Microsatellite comprising a propulsion module and an imaging device

Abstract

A microsatellite comprising a propulsion module for moving and/or pointing said microsatellite and an imaging device ( 100 ) mounted to said propulsion module. Furthermore there is a fuel supply ( 210 ) located within said imaging device ( 100 ).

1 - 38 . (canceled) 
     
     
         39 . A spacecraft comprising:
 a propulsion module for at least one of moving and pointing said spacecraft; and:   a chamber comprising:   an optical system for transmission of light from an image target to an optical sensor, the optical system comprising at least a window disposed at an end of the chamber, the window being for transmission therethrough of light from the image target; and   wherein the chamber is configured for storage of propellant.   
     
     
         40 . The spacecraft according to  claim 39  arranged for the chamber to contain liquid propellant, the chamber further comprising a bellow for containing the liquid propellant, the bellow being arranged to contract as the liquid propellant is consumed, wherein the bellow is terminated by a transparent window. 
     
     
         41 . The spacecraft according to  claim 39  wherein the chamber is of selectively variable volume such that on depletion of said propellant, the chamber is correspondingly reduced in volume. 
     
     
         42 . The spacecraft according to  claim 41  wherein the chamber comprises a piston for reducing the volume within the chamber. 
     
     
         43 . The spacecraft according to  claim 39  wherein the chamber comprises an extendable structure to move a first group of components of an optical system so as to modify an optical length of the optical system. 
     
     
         44 . The spacecraft according to  claim 43  wherein the chamber includes at least two concentric portions in sliding engagement and an actuator to cause relative movement between said at least two portions between a retracted position and an extended position. 
     
     
         45 . The spacecraft according to  claim 39 , wherein said chamber includes a deformable supporting structure such that variation of propellant refractive index due to changes in pressure and temperature are compensated for by deforming to a shape to cancel optical effects due to the propellant. 
     
     
         46 . A spacecraft comprising:
 a propulsion module for at least one of moving and pointing said spacecraft; and:   a chamber comprising:   an optical system for transmission of light from an image target to an optical sensor, the optical system comprising at least a window disposed at an end of the chamber, the window being for transmission therethrough of light from the image target; and   wherein the chamber is configured for storage of pressurised fluid.