Module-type spacecraft

FIELD: rocketry and space engineering; designing artificial satellites.

SUBSTANCE: proposed spacecraft has modules where service equipment is arranged and modules where target equipment and command and measuring devices are located. Optical devices of target equipment of infra-red range with cooled elements are mounted in central module. Radio equipment of on-board repeater is arranged in side modules whose position is changeable relative to position of central module. Optical and command and measuring devices are mounted on one frame at reduced coefficient of linear thermal expansion; they are combined with central module through three articulated supports. Cooled elements of optical devices are connected with radiators located beyond zone of thermal effect; service equipment module is provided with solar batteries having low dynamic effect on accuracy of spacecraft stabilization. Besides that, this module is provided with plasma engine whose working medium excludes contamination of said optical devices.

EFFECT: enhanced accuracy of spacecraft stabilization; electromagnetic compatibility of systems.

3 dwg

 

The invention relates to rocket and space technology and, in particular, to the designs of spacecraft (satellites).

From the patent literature known spacecraft, consisting of separate modules with standard systems and aggregates (see, for example, U.S. Pat. U.S. No. 6206327, CL 244/I58R, B 64 G 1/00, from. 27.03.2001 year).

Of the same patent literature known to the modular design of the spacecraft (artificial satellite), contains modules on-Board equipment, with the possibility of changing the mutual position of the modules during insertion in the composition of the booster and Autonomous functioning spacecraft in orbit (see, for example, U.S. Pat. U.S. No. 6220548, CL 244/I58R, B 64 G 1/50, from. 24.04.2001,).

However, in these constructions does not provide ways and means to improve the accuracy of stabilization of the spacecraft, to prevent contamination of the cold optics, for solving the problem of electromagnetic compatibility, the differential approach to the conditions of operation of various equipment, to achieve the specified accuracy of the orientation of the sighting axes of the optical devices.

The objective of this invention is to provide a modular construction of the spacecraft, which would have provided the means to achieve technical results, such as improving the accuracy of stabilization of the space and the parathas, the exception to the pollution of the cold optics, electromagnetic compatibility, a differential approach to the conditions of operation of various equipment, ensure the specified accuracy of the orientation of the sighting axes of the optical devices.

This task is solved in that the modular design of the spacecraft, containing modules on-Board equipment with the ability to change the relative position of the modules during insertion in the composition of the booster and Autonomous functioning spacecraft in orbit, in accordance with the invention, one of the modules contains utility equipment, and the rest of the target equipment and command-measuring devices of the control system, such as a gyroscopic measuring the angular velocity vector (HIVOS) and astropathic, target equipment installed in three modules: optical target equipment infrared range with a cooled elements in the Central module and the target radio equipment on-Board relay in the side modules having the ability to change its position relative to the Central module, optical devices target equipment and command-measuring devices of the control system of the spacecraft is installed on a single razorscale frame made of structural materials with more or is Kim level of coefficient of linear thermal expansion in comparison with the materials of the rest of the structure of the Central module, and combined with the frame of the Central module via three pivot bearing, a cooled optical elements of the target apparatus connected to the radiators, for example, low-temperature, level 190 To rendered outside the zone of thermal influence of the spacecraft with the Autonomous functioning of the spacecraft in orbit, on the module containing the service equipment, installed solar panels, reducing harmful dynamic impact on the accuracy of stabilization of the spacecraft due to the rigidity of their design and use drive solar device with dynamic unloading or gentle law of increase of the steering torque, to perform all necessary dynamic operations of the spacecraft, installed only plasma engines with a working body, precluding contamination of the optical target equipment infrared range with a cooled elements.

Hereinafter the invention is explained in more detail with the use of graphic materials, in which figure 1 shows a General view of the modular design of the SPACECRAFT (SC) at the Autonomous flight of a SPACECRAFT into orbit; figure 2 is similar to the modular design of the SPACECRAFT, but in parsed form; figure 3 - the modular design of the SPACECRAFT's position excretion in space head part (SHS) rockets-wear what I (PH).

The modular design of the spacecraft (see figure 1) contains the module 1 with the service equipment 2 (2) and prefabricated module target equipment, made in the form of three compartments or modules: the Central module 3 optical target equipment 4 infrared range with a cooled elements and command-measuring instruments of service systems, two side modules with 5 radio 6 target equipment on-Board relay, having the ability to change its position relative to the Central module. I.e. the side modules of the target apparatus connected to the Central module of the target apparatus is movable, for example, through the hinge, otkidyvayutsya or sliding connection.

Optical devices target equipment and command-measuring devices 7 of the control system installed on a single razorscale frame 8 (2), made of structural material with a lower coefficient of linear thermal expansion in comparison with the materials of the rest of the structure of the Central module and combined with the frame 9 of the Central module via three pivot bearing.

The cooled optical elements of the target apparatus connected to the radiators 10, for example, low-temperature, level 190 To rendered outside the zone of thermal influence of the design space and the parathas with Autonomous functioning SPACECRAFT in orbit.

To reduce the dynamic influence of the solar battery 11 on the accuracy of SPACECRAFT stabilization uses a special design of the SAT increased stiffness and actuator 12 rotate with the device dynamic unloading or gentle law of increase of the steering torque.

On the module containing the service equipment to perform all necessary dynamic operations KA set of stationary plasma engines 13 with a working body, precluding contamination of the optical target equipment infrared range with a cooled elements.

Described modular construction KA is used and operates as follows:

Before the start of a rocket designed for launching into orbit of SPACECRAFT or satellites, in the SHS (SHS) set out the proposed structure assembled in compact form (see figure 3). After the withdrawal of the corresponding orbit the modular design of the SPACECRAFT is provided in the position and status of Autonomous functioning SPACECRAFT in orbit (see figure 1): unfolding solar panels, the side modules with equipment relay recline, are deployed or removed from the Central module of target equipment included in the work of the onboard equipment of the service module, SPACECRAFT oriented in a given direction and begins to function telematically, radio and other target hardware.

The proposed design of the SPACECRAFT provides a number of advantages and positive technical results. So, for example, installation of equipment in three Autonomous compartments-modules and the use of functional and structural autonomy of the compartments of the module target hardware can work on the design, fabrication and testing of compartments performed in parallel, the modernization of relay complex and the optical target equipment from product to product can be performed independently, you receive the possibility of gradually increasing functionality KA (the first spacecraft only with optical equipment, subsequent donamaria brtc), a differential approach to the conditions of operation of various equipment.

Device dynamic unloading is performed, for example, in the form of a flywheel mounted in the drive solar battery. The flywheel rotates in the direction opposite to the rotation of the solar battery, and is designed so that the total kinetic moment of the rotation of the solar panels and the flywheel is equal to zero. This can significantly reduce disturbances on the SPACECRAFT from solar rotation and to achieve high accuracy of stabilization of the SPACECRAFT.

Installing the optical devices target equipment, astrobingo horoscopical of measuring the angular velocity vector of the integrated management system space platform on a single isolated from the chassis KA razorscale design allows you to provide the specified accuracy the orientation of the sighting axes of optical devices due to the exclusion of mutual misalignments seats target equipment, and command devices traffic control system. The use of drive rotation of the solar devices dynamic unloading or with gentle law of increase of the steering torque to achieve the specified accuracy of the SPACECRAFT stabilization and also used for orbit correction plasma engines with low thrust, their placement and high purity streams, prevent pollution of the cold optics, can significantly improve the technical and operational characteristics. To ensure the specified accuracy of the SPACECRAFT stabilization promotes and application design solar high rigidity.

To ensure thermal equipment when operating a SPACECRAFT in geostationary orbit also promotes and priority placement of devices into "Northern" and "southern" panels KA

The modular design of the spacecraft, containing modules on-Board equipment that has the ability to change their relative position during insertion in the composition of the booster and Autonomous functioning spacecraft in orbit, characterized in that one of the modules contains the service equipment of the spacecraft, and the OST is further modules target equipment and command-measuring devices of the control system of the spacecraft, the target apparatus is installed in three modules: optical devices target equipment infrared range with a cooled elements in the Central module and the target radio equipment on-Board repeater in the side modules having the ability to change its position relative to the Central module, and these optical devices target equipment and command-measuring devices of the control system of the spacecraft is installed on a single razorscale frame made of structural material with a lower coefficient of linear thermal expansion than the material the rest of the structure of the Central module, and integrated with the Central frame module three pivot bearing, and these cooling elements, optical devices target equipment infrared range connected with radiators made outside the zone of thermal influence of the spacecraft with the Autonomous functioning of the spacecraft in orbit, on the module containing the specified office equipment, solar panels are installed with reduced harmful dynamic effect on the stabilization of the spacecraft C is the account of the hardness of their design and use drive solar device with dynamic unloading or gentle law of increase of the steering torque, with this module, in addition to these solar panels are installed plasma engines with a working body, eliminating contamination of the optical devices of the specified target equipment infrared range with a cooled elements.



 

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