RU2247683C1 - Module-type spacecraft - Google Patents

Abstract

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.

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Description

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

Spacecraft consisting of separate modules with standard systems and assemblies are known from the patent literature (see, for example, US Pat. No. 6,206,327, CL 244 / I58R, B 64 G 1/00, dated March 27, 2001).

From the patent literature, the modular design of a spacecraft (for an artificial satellite) is known, which contains modules of on-board equipment, with the possibility of changing the relative position of the modules during launch as part of the launch vehicle and with the autonomous functioning of the spacecraft in orbit (see, for example, US Pat. No. 6220548, class 244 / I58R, B 64 G 1/50, dated April 24, 2001).

However, these designs do not provide ways and means to improve the accuracy of stabilization of the spacecraft, to eliminate contamination of “cold” optics, to solve the problem of electromagnetic compatibility, a differential approach to the operating conditions of various equipment, to ensure a given accuracy of orientation of the sighting axes of optical instruments.

The objective of this invention is to create a modular design of the spacecraft, which would provide means to achieve technical results, such as improving the accuracy of stabilization of the spacecraft, eliminating pollution of "cold" optics, ensuring electromagnetic compatibility, differential approach to operating conditions of various equipment, ensuring the given accuracy orientation of the sighting axes of optical instruments.

This problem is solved in that in the modular design of the spacecraft containing modules of the onboard equipment with the ability to change the relative position of the modules during the launch as part of the launch vehicle and with the autonomous functioning of the spacecraft in orbit, in accordance with the invention, one of the modules contains service equipment, and the rest - the target equipment and command and measuring instruments of the control system, for example, a gyroscopic angular velocity vector meter (GIVUS) and astro sensors, target app The equipment is installed in three modules: an infrared optical target equipment with cooled elements in the central module, and an onboard repeater radio target equipment in side modules that can change their position relative to the central module, optical instruments of the target equipment and command and measuring instruments of the spacecraft control system mounted on a single dimensionally stable frame made of structural materials with a lower coefficient level linear thermal expansion in comparison with the materials of the rest of the central module construction, and combined with the central module frame through three hinged supports, the cooled elements of the optical target equipment are connected to radiators, for example, low-temperature, level 190 K, carried outside the heat-affected zone of the space structure spacecraft with autonomous functioning of the spacecraft in orbit, solar cells are installed on a module containing service equipment to reduce harm The dynamic influence on the accuracy of stabilization of the spacecraft due to the rigidity of their design and the use of a solar battery drive with a dynamic unloading device or a gentle law of increasing control moment, to perform all the necessary dynamic operations of the spacecraft, only plasma engines with a working fluid eliminating optical target pollution are installed infrared instruments with cooled elements.

The invention is further explained in more detail using graphic materials, in which Fig. 1 shows a general view of the modular design of a spacecraft (SC) during autonomous flight of a spacecraft in orbit; figure 2 - the same modular design of the spacecraft, but in a "disassembled" form; figure 3 is a modular design of the spacecraft in the position of the launch as part of the space head part (KGCH) of the launch vehicle (LV).

The modular design of the spacecraft (see Fig. 1) contains module 1 with service equipment 2 (Fig. 2) and a prefabricated module of the target equipment, made in the form of three compartments or modules: a central module 3 with optical target equipment 4 of the infrared range with cooled elements and command and measuring instruments of service systems, two side modules 5 with radio engineering 6 target equipment of the onboard repeater, with the ability to change their position relative to the central module. Those. the side modules of the target equipment are connected to the central module of the target equipment movably, for example, through hinged, tilting or sliding connections.

Optical devices of the target equipment and command-measuring devices 7 of the control system are mounted on a single dimensionally stable frame 8 (Fig. 2) made of structural materials with a lower level of coefficient of linear thermal expansion in comparison with the materials of the rest of the central module construction and combined with the central frame 9 module through three hinged supports.

The cooled elements of the optical target equipment are connected to radiators 10, for example, low-temperature, level 190 K, carried outside the zone of thermal influence on them of the design of the spacecraft during the autonomous operation of the spacecraft in orbit.

To reduce the dynamic effect of solar cells 11 on the accuracy of stabilization of the spacecraft, a special SB design of increased rigidity and a rotary drive 12 with a dynamic unloading device or a gentle law of increase in control torque are used.

To carry out all the necessary dynamic operations of the spacecraft, only stationary plasma engines 13 with a working fluid eliminating contamination of the optical infrared target equipment with cooled elements are installed on the module containing the office equipment.

The described modular design of the spacecraft is used and operates as follows:

Before the launch of the launch vehicle, intended for launches into the orbits of the spacecraft or satellites, the proposed design is assembled in a compact form (see Fig. 3) in the space warhead (KCH). After launching into the appropriate orbit, the spacecraft’s modular design is brought into position and the state of the spacecraft’s autonomous functioning in orbit (see Fig. 1): solar batteries are deployed, side modules with relay equipment are tilted, deployed or retracted from the central module of the target equipment, the onboard vehicle service module equipment, the spacecraft is oriented in a given direction and the target optical, radio engineering, and other target equipment begins to function.

The proposed design of the spacecraft allows you to get a number of advantages and positive technical results. For example, the installation of target equipment in three autonomous module compartments and the use of the functional and constructive autonomy of the module modules of the target equipment allows the design, manufacture and testing of compartments to be carried out in parallel, the relay complex and optical target equipment can be upgraded from product to product, it becomes possible to gradually increase the functionality of the spacecraft (the first spacecraft with only optical equipment, the next Retrofit BRTK s), a differential approach to operating conditions of various apparatus.

The dynamic unloading device is, for example, in the form of a flywheel installed in the solar drive. The flywheel rotates in the direction opposite to the rotation of the solar battery, and is designed in such a way that the total kinetic moment from the rotation of the solar battery and the flywheel is zero. This allows one to significantly reduce perturbations on the spacecraft from the rotation of solar batteries and to achieve high accuracy of stabilization of the spacecraft.

The installation of optical instruments of the target equipment, astrodevices, and a gyroscopic meter of the angular velocity vector of the integrated space platform control system on a single dimensionally stable design decoupled from the spacecraft body makes it possible to provide the specified accuracy of the orientation of the sighting axes of the optical instruments by eliminating mutual inconsistencies in the seats of the target equipment and command instruments of the motion control system . The use of a rotary drive for solar batteries with dynamic unloading devices or with a gentle law of increasing control torque to ensure the given accuracy of stabilization of the spacecraft, as well as the use of low-thrust plasma engines for correcting the orbit, their placement and high purity of the jet, eliminating the pollution of “cold” optics, significantly improve the technical and operational characteristics of the spacecraft. The use of the design of high-rigidity solar panels also contributes to the preset accuracy of stabilization of the spacecraft.

The equipment’s thermal conditions during spacecraft operation in the geostationary orbit are also facilitated by the priority placement of devices on the “northern” and “southern” satellite panels

Claims (1)

The modular design of the spacecraft, containing modules of the onboard equipment, having the ability to change their relative position when displayed as part of the launch vehicle and with the autonomous functioning of the spacecraft in orbit, characterized in that one of the modules contains the service equipment of the spacecraft, and the rest of the modules are the target equipment and command and measuring devices of the spacecraft control system, while the target equipment is installed in three modules: target optical instruments infrared equipment with cooled elements in the central module, and the radio-technical target equipment of the onboard repeater in the side modules, which are able to change their position relative to the central module, the specified optical devices of the target equipment and command-measuring devices of the spacecraft control system are mounted on a single dimensionally stable frame, made of structural materials with a lower coefficient of linear thermal expansion than m of the remaining structure of the central module, and combined with the frame of the central module through three hinged supports, and these cooled elements of the optical instruments of the target infrared equipment are connected to radiators that are carried outside the heat-affected zone of the spacecraft structure during the autonomous operation of the spacecraft in orbit, on the module containing the specified service equipment, solar panels are installed with reduced harmful dynamic effects on accuracy stabilization of the spacecraft due to the rigidity of their design and the use of a solar battery drive with a dynamic unloading device or a gentle law of increasing control torque, and on this module, in addition to these solar batteries, plasma engines with a working fluid that exclude pollution of optical instruments of the indicated infrared target equipment are installed with refrigerated elements.

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