nro3_200206

nro3_200206 - Electromagnetic Formation Flight...

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Electromagnetic Formation Flight NRO-000-02-C0387-CLIN0001 MIT Space Systems Laboratory 1 Electromagnetic Formation Flight Progress Report Submitted to: Lt. Col. John Comtois Technical Scientific Officer National Reconnaissance Office Contract Number: NRO-000-02-C0387-CLIN0001 MIT WBS Element: 6893087 Submitted by: Prof. David W. Miller Space Systems Laboratory Massachusetts Institute of Technology
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Electromagnetic Formation Flight NRO-000-02-C0387-CLIN0001 MIT Space Systems Laboratory 2 D ESCRIPTION OF THE E FFORT The Massachusetts Institute of Technology Space Systems Lab (SSL) and the Lockheed Martin Advanced Technology Center (ATC) are collaborating to explore the potential for a Electro-Magnetic Formation Flight (EMFF) system applicable to Earth-orbiting satellites flying in close formation. P ROGRESS O VERVIEW Work at the MIT SSL is continuing on two fronts: the CDIO class, and the MIT SSL graduate research group. The CDIO class is currently in the process of designing an electromagnetic test bed called EMFFORCE. One requirement of this testbed is the ability to determine each satellites relative position to one another. This month’s report will discuss the analysis and trades used to determine the preliminary design of the EMFFORCE test bed metrology subsystem. Metrology 1. Subsystem Overview Fig. 1: Metrology Block Diagram Extracted from the requirements of the overall project, the goal of the metrology system is to accurately calculate relative distance and attitude. Per the requirements document, accurately is defined as 1/10 of the control tolerance for both distance and angular readings. In addition, the metrology system needs to have a field of view of 360º in a 2-D plane. Finally, the system needs a detection range compatible with test facilities. These test facilities include the test facility at MIT and the Lockheed flat floor facility in Denver, CO. Interface Board Rate Gyro 2-axis accelerometer TT 8 Processor A/D Converter IR Receiver x3 Ultrasonic Receiver x3 Ultrasonic Transmitter IR Transmitter x2
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Electromagnetic Formation Flight NRO-000-02-C0387-CLIN0001 MIT Space Systems Laboratory 3 2. System Trade Analysis The initial trade analysis for the metrology subsystem was to compare sonic ranging systems, indoor GPS, and inertial navigation. Sonic ranging may be implemented in many ways. In the current incarnation, the sonic system uses time differences between transmitted sonic signals to triangulate the position of a vehicle (this is explained in much greater detail in the design section below). Inertial navigation uses velocity and acceleration information from rate gyros and accelerometers to calculate the position of a vehicle. The second derivative of acceleration gives linear position and the first derivative of angular rate gives angular orientation. The indoor GPS system is very similar to the current design for the sonic system except that it uses radio frequency. Indoor GPS relies on several radio frequency antennas.
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This note was uploaded on 11/08/2011 for the course AERO 16.810 taught by Professor Olivierdeweck during the Winter '07 term at MIT.

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nro3_200206 - Electromagnetic Formation Flight...

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