Modular satellites in satellite formation

The invention relates to a modular satellite concept, after the a satellite in the conventional sense is realized by at least two satellite modules, the only common Functions of a satellite in the conventional sense provide.

For satellites in the traditional sense is to be Missiles, the number of coordinated and mutually have a unit associated components to which, for example, the power, the position, position and Temperature control, the TT & C subsystem (Telemetry, Tracking and Command) and the transponder with the Antenna subsystem as payload belong. The transponder comprises regularly receiving section, a processing section (on-board processor) and a transmitting part, each with the associated Antenna. These individual components, which vary depending Application can further be added, to become a Missiles, the satellite united in the traditional sense.

The performance requirements for telecommunication satellites, for example, with respect to the transmission power, the number of Transponder / spare transponder and the frequency bands in the lead Result to the fact that very large satellite in the conventional sense and be very difficult. These satellites can only with the most powerful and most expensive launch vehicles (eg Ariane 5, Proton, etc. are started). The effort, the size and the weight of the satellite with respect to the start as far as possible to reduce, through the ever-increasing Requirements against which regularly with an enlargement the structure and an increase in the weight of the satellite in traditional sense are connected.

Against this background, the basis of the invention lying problem is to provide a satellite that the ever-increasing performance demands while is a significant reduction of the starting weight requirements.

This problem is solved consisting a modular satellite of at least two module satellites, Communication means for exchanging data and / or the transmission of signals and having each of which a Payload component comprises, holding in a the Communication devices attained the interaction determine functionality of modular satellites.

According to the invention of the modular satellite from at least a first module satellite which the means Power, to control the position, the position and the Temperature and the path control of the module satellite, as well as a first payload component and a first Communication means for transferring data and / or Signals to another module comprises satellite, and a second module satellite which the means Power, to control the position, the position and the Temperature and the path control of the module satellite, as well as a second payload component and a second Kommunkationseinrichtung for transmitting data and / or Includes signals to another module satellite.

According to one described in more detail below Embodiment includes the modular satellite nor a third module satellite which the means Power, to control the position, the position and the Temperature and the path control of the module satellite, as well as a third payload component and a third Kommunkationseinrichtung for transmitting data and / or Includes signals to another module satellite.

Through the realization of the different payloads in each Module satellite is achieved that the individual module satellite a significantly lower starting weight than one satellite in the conventional sense, in which the present invention to multiple Modules distributed payload components in one unit are summarized. Considering the total weight of all Module satellites together the functionality of a deploy satellites in the normal sense, is this certainly higher than the weight of the conventional satellite. The significantly reduced weight in the individual Satellite module but brings with respect to the Start required launcher so many advantages that the increase of the total weight neither technically nor economically a represents real disadvantage. Moreover, requirements are also conceivable, which corresponds to a conventional satellite only one size, which can no longer be started.

The modular Satellite invention is also a connected Another advantage of modern life with Telecommunications satellites accompanied. Modern Telecommunications satellites have a life of up to 15 years. but very much shorter are certain Key technologies, such as the signal processing on board of the satellite (on-board processing). While in conventional Satellites obsolescence of on-board processing immediately means that this satellite for modern tasks not or can be used is limited, provides the inventive modular satellite the ability to Satellite module on which the on-board processing is realized, to withdraw from the market and with a new module satellite replace, which takes over the signal processing.

In a particular embodiment, the build Communication devices using laser beams a Link to between the module satellites. The Kommunkationseinrichtungen include to a Lasersende- and a laser receiver.

Alternatively or additionally build communication facilities using microwaves a transmission link between the Module satellite (1, 2, 3) build. The Kommunkationseinrichtungen include to a microwave transmitting and a microwave receiver.

In an advantageous embodiment, the payload component a first module satellite receiving means with at least one Emfangsantenne for the reception of signals and / or data. The first module satellite can then required control commands from a ground station on the received receiving antenna of the receiving device.

The payload component of a second module satellite can Signal processing means for Verbarbeitung of its signals and / or data.

The payload component of a third module satellite is then a transmitting device having at least one transmitting antenna for Sending is of signals and / or data. The third module satellite , the required control commands from a ground station (4) received via the transmitting antenna of the transmitting device (11).

The three payload components, ie, the receiving means Signal processing means and the transmitting means of the three inventively designed module satellites are only in their Interaction useful. The receiving device of the first Satellite module receives a signal transmitted from a ground station Signal and transmits the signal to the Signal processing means of the second module satellite, of of the processed signal to the transmitting device of the third Module satellite is transmitted.

In the following, the invention is based on a Exemplary embodiment with reference to the drawings explained, in which:<dl tsize="7"><dt>Fig. 1</dt><dd>a first embodiment of a modular Satellite module consisting of two satellites and</dd><dt>FIG. 2</dt><dd>A second embodiment of a modular Satellite consisting of three module satellites.</dd></dl>

In Fig. 1 is a first embodiment of a shown modular satellites according to the invention, in which two Module satellites 1, 2 are provided. The first module satellite 1 of the exemplary embodiment is provided as a receiver for a Ground station 4 transmitted signals (uplink) designed. It includes a receiving device 5, for the representative in Fig. 1, Receiving antenna 5a and an input amplifier 5b are. In addition, the first satellite module 1 with all other components provided that are required to get out to make it a stand-alone missile from a Ground station, for example, the ground station 4 from is controllable.

For these components, the above-mentioned examples were, 1 the sun sail 6 is shown in FIG. representative shown. In particular, it involves the Power supply, the position, position and temperature control and the TT &amp; C subsystem (Telemetry, Tracking and Command).

According to the invention comprises the first module satellite 1, a first Communication means 7, with which a communication channel to can be built a second Modulsatellliten. 2 Of the second module satellite 2 comprises to a second Communication device 8, on the first to the Module satellite 1 via the first communication device 7 data can be exchanged and / or transmit signals. The first and made the second communication devices from a first transmission means 7a and a first Receiver 7b and a second transmission means 8a and a second receiving device 8b.

The second satellite module 2 includes in the first Embodiment of a transmitting device 9, which in FIG. 1 primarily represented by the transmission antenna 9a to but also inter alia a transmitter amplifier 9b, mostly with a TWT (TWGT) belongs. The second module satellite 2 is as well as the first module satellite 1 with all the necessary Components equipped, consisting of the second module satellite 2 make an independent missile example of the Ground station 4 from is controllable. As with the Satellite module 1 in FIG. 1 for these components of the second module satellite 2 representative, only the Awning 10 shown, the previously mentioned for the Components is.

According to first form the two module satellites 1, 2 sharable a view from the ground station 4 Satellite receiver with 5 and transmitter 10th A signal sent from the base station 4 of the signal is received receiving device 5 of the first module satellite 1 and over the first communication device 7 to the Communication means 8 of the second module satellite 2 transmitted. The transmitting device 10 of the second module satellite 2 sends the signal to the earth.

If a problem occurs on the modular satellite which at this embodiment according to the invention of the Module satellites 1 and 2 exists, the affected are module satellite maneuvered from the composite, since it with you two module satellites invention to independently controlled missile concerns, and by a new Module Satellite replaced with corresponding payload component will. it is according to the inventive concept only necessary to replace the module satellites to maneuver the composite and with a new module satellite to replace.

Due to the nowadays available technology in the TT &amp; C region it is readily possible two or more Module satellites close to each other or in a to position the desired distance from each other in orbit.

In FIG. 2 is a second embodiment of a shown modular satellites according to the invention, in which three Satellite module 1, 2, 3 are provided. The first module satellite 1 of this embodiment is provided as a receiver for the of a ground station signals transmitted 4 (uplink) designed. He comprises a receiving device 5, for the representative in Fig. 1, the receiving antenna is shown. In addition, the first module satellite 1 with all other components provided that are required to select one of him independent missile to do that, from a ground station eg the ground station 4 from is controllable. For this Components which have been already mentioned by way of example, the awning 6 representatively shown in Fig. 2. In particular, it involves the power supply, Position, position and temperature control and the TT &amp; C subsystem (Telemetry, Tracking and Command).

The second module 2 comprises, in the second satellite Embodiment of a transmitting device 9, which in in FIG. 2 primarily represented by the transmit antenna, to the but also inter alia a transmitter amplifier, usually with a TWT (TWGT) belongs. The second module satellite 2 is as well as the first module satellite 1 with all the necessary Components equipped, the one from the module satellites make independent missile for example from the ground station 4 is made controllable. Just as the module satellite 1 in Fig. 2 for these components of the second module satellite 2 representatively shown only the awning 10, the for the previously mentioned components is.

gem in the embodiment. Fig. 2 is a third Module satellite 3 is provided, for example, a payload as Signal processing device 11 (on-board processor), of the of a third communication device 12 of the third Satellite module 3 received signals are fed. The third communication device 12 receives signals / data from the first communication device 7 of the first Module satellite. The signal processing device 11 processes the signals and transmits the processed Signals via the third communication device 12 of the third Module satellite 3 to the second module satellite 2 via its Communication device 8. The third module satellite 3 as well as the first module satellite 1 with all the necessary Components equipped, the one from the module satellites make independent missile for example from the ground station 4 is made controllable. Just as the module satellite 1 in Fig. 2 for these components of the third module satellite 3 representatively shown only the awning 13, for the previously mentioned components is.

According to the invention only are the three satellite module 1, 2, 3 this embodiment together a summary of the Ground station 4 usable with satellite receiver, Signal processing means and transmitting means. One of the Ground station transmitted signal 4 is of the received receiving device 5 of the first module satellite 1 and via the communication device 7 and the Communication device 12 of the third module satellite 3 transmitted. From there the signal to the Signal processing means 11, then by the signal from the via the communication device 12 to the Communication means 8 of the second module satellite 2 is transmitted. The transmitting device 9 of the second Module 2 satellite sends the signal to Earth.

If the requirements on the signal processing in the course of the life of the modular satellite, which in this Embodiment according to the invention of the module satellites 1, 2 and 3, should change, the second module satellite 2 be maneuvered from the composite, since it is at the Module satellite 2 according to the invention independently a controllable missile concerns, and by a new Module Satellite replaced with signal processing means will. The same is true for the first satellite module 1 and the third module satellite 3, as well as the second Module satellite 2 even with the life disturbances or expiration can be replaced. The inventive concept accordingly, it is only necessary to replace the to maneuver module satellite of the composite and by a replace new module satellite.

The inventive modular satellite a realized effective redundancy concept, as not only defective Satellite module can be exchanged, but individual Module Satellite preventively also in an economical way can be repaired. The inventive concept offers a higher flexibility than the prior art conventional Satellite concepts. So functionality can be added at any time or be taken away. Technologically outdated modules be supplemented or replaced. The satellite life and technological progress can therefore coordinated will. It is also essential that complex, and thereby today not to be realized by satellite in the conventional sense the inventive concept is modular and in Orbit are assembled into a functioning unit. Modules can co-positioned at the same orbital position placed to or at different orbital positions will. The inventive concept are also on simple way spot beam satellite module realized that illuminate certain regions on the earth, and which on the respectively provided communication device, the corresponding Signals are fed.

The communication devices 7, 8 and 9 of the satellite module 1, 2 and 3 of the embodiments shown in FIGS. 1 and 2 can be realized in different ways. For example can a rating based on laser beams or microwaves Transmission link to be established. In view of the very short distances for these additional transmitting and Receptions little more benefits provide.

Deviating from the embodiments described herein , a modular satellite according to the invention with more than two or three module satellites are realized. Which Payload carrying module satellite, this can optionally after assesses technical and economic criteria and be determined. The point is that from the perspective of Ground station of the inventive modular satellite only through the interaction of the module the desired satellite Provides functionality.

In an advantageous variation of the second embodiment , the receiving means (5), the second in the Embodiment in the first Modulsatelltien (1) is arranged, and the transmission means (9) responsive to the second module satellite (2) is arranged, also on a (First) module satellites are summarized. the the Signal processing wide alternate end module satellite (3) is then a Another (second) module satellite of the modular invention Satellite. When the requirements for the change signal processing (on-board processing), can and must only this module satellite can be exchanged while the durable transmitting and receiving devices continue to be used will.

To that shown in FIG. 2, the third module of the second satellite Embodiment is preferably a receiving antenna for provide the TT &amp; C signals to the ground station Control of the module satellites are sent. The two Embodiments gem. Fig. 1 and 2, first and second module satellites 1 and 2, the control signals from the ground station through the receiving antenna of the Receiving device 5 and the transmitting antenna of the transmitting device 9 received. Usually, however, possess the invention Module satellites known from conventional satellites Antennas for receiving / sending TT &amp; C signals / data. These antennas are often referred to as omnidirectional antennas because they have an all-round characteristics. Because after the Uncoupling from the launcher is not ensured that the Main transmitting and receiving antenna is aligned so that the can be controlled by the satellite ground station. After positioning in orbit, the main antenna for TT &amp; C purposes be used.