 Radar system with reduced distance error |
| The present invention is directed to a radar system of the above mentioned kind in which the ... |
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| Radar altimeter systems |
| It is an object of the present invention to provide a radar altimeter system that can be used, at ... |
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| Signal processing system |
| OF INVENTION The radar system of FIG. 1, which includes the balanced signal processor, can be used ... |
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| Radar channel including an orthogonal MTI filter pair |
| A radar operates in a moving target indication (MTI) mode with frequency diversity by transmitting N... |
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| Operator station for telephone exchange |
| The object of the present invention is to provide an operator station for telephone exchanges, ... |
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| Arrangement for processing a delta modulation signal, in particular for decoding these signals |
| What is claimed is: 1. A processing device for decoding a digital signal formed from binary ... |
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| Sound masking system for open plan office |
| What is claimed is: 1. An acoustic masking system for obtaining conversational privacy in an open ... |
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| Video signal processing apparatus for separating an image of a moving object from video signals |
| OF THE INVENTION Referring now to FIGS. 1 through 3, a preferred embodiment will be explained. A ... |
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| Dynamic image transmission system |
| Accordingly, it is a general object of the present invention to provide a novel and useful dynamic ... |
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| Telephone anti-theft device |
| OF A PREFERRED EMBODIMENT Referring initially to FIG. 1, pay telephone 10 is of conventional ... |
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Satellite system configuration
| Details |
Inventors: Preukschat, A. Werner;
Assignee:
Primary Examiner: Frankfort; Charles E.
Assistant Examiner:
Attorney, Agent or Firm: McCormick, Paulding & Huber
A new satellite system configuration is comprised of a power module with rigidly attached solar arrays and a control module including a sun pointing unit, an earth pointing unit and a rotary interface. The power module is attached to one face of the sun pointing unit and an opposite face of the sun pointing unit is attached to the earth pointing unit through the rotary interface to allow the earth pointing unit to remain pointing to the earth while the sun pointing unit rotates relative to it to keep the rigidly attached solar arrays of the power module pointing toward the sun. The earth pointing unit has a docking area for subsequent orbital docking of one or more earth pointing payload satellites to be serviced and controlled by the power and control modules. |
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DETAILED DESCRIPTION What is claimed is: 1.
Satellite system configuration comprising a service satellite (10) including at least one power module (11) having solar arrays rigidly attached thereto, and a control module (12) comprised of a sun pointing unit (1) attached at a first face thereof to one side of the power module, and an earth pointing unit (2) attached at one side to a second face of the sun pointing unit through rotary interface means (3) arranged to allow said earth pointing unit to remain pointing to the earth while said power module and solar arrays are kept pointing to the sun, said earth pointing unit having at least a second side (5) provided with docking means (7) for subsequent docking in orbit of at least one earth pointing payload satellite (20) for being serviced and controlled from said service satellite (10).
2.
A satellite system configuration according to claim 1, comprising three string legs having a common point, the first leg (100) including the service satellite (10) with said earth pointing unit (2) thereof providing the common point, the other two legs (200, 300) each including at least one earth pointing payload satellite (20,50) docked to said earth pointing module (2).
3.
A satellite system configuration according to claim 2, wherein at least one of said other two legs includes a plurality of earth pointing payload satellites (20,30,40;50,60) docked to each other.
Description:
BACKGROUND OF THE INVENTION The present invention relates to a new Satellite Configuration for geostationary missions.
Conventional satellite configurations consist of self contained units which include all service function elements that are required by the specific mission payload as well as the payload itself.
In view of satellite reliability and service availability considerations sufficient on-board redundancy needs to be achieved to meet the life time mission requirements.
Due to the mass limitation of some launch vehicles, the redundancy requirement leads to the adoption of satellite systems that require, for example for a 10 year service life, the procurement a number of individual flight satellites and their launch with a primary and a spare operational satellite always in orbit, and at least one spare satellite on the ground
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Telecommunications 
