RU2577558C1 - Device for determining orientation of object based on stars - Google Patents

Abstract

FIELD: astronautics.

SUBSTANCE: invention relates to space navigation and can be used for rapid accurate determination of spacecraft orientation relative to inertial coordinate system. Device for determining celestial orientation of object includes a housing, an optical system, a lens hood, a matrix radiation receiver, a computing device, electronic memory with onboard navigation catalogue stars. Well arrangement of the sensor is used, wherein the optical system and blind are combined into central module, partially located inside the housing of the sensor, the blind is holder of the optical system, and central module is the housing cover. Around the central module there is a single electronic board which is fixed to side walls and case base with screws. Board comprises flexible sections, at which the Board is bent so that the main fuel elements are pressed to side walls of the housing and matrix radiation receiver to case base. Note here that heat release from the walls and base of the housing is conducted by heat exchange due to heat conductivity through at least three fastening lugs of the body base and partially by radiant heat exchange with inner surface of the built-in blind. In the board under lower surface of the radiation detector array is arranged thermoelectric cooler Peltier in contact with housing base through a heat-conducting paste or gasket.

EFFECT: reduced weight and overall dimensions, as well as high heat removal.

3 cl, 6 dwg

Description

FIELD OF THE INVENTION

The invention relates to space navigation and can be used for operational accurate determination of the orientation of the spacecraft relative to the inertial coordinate system.

State of the art

Famous star sensors (ZD) of orientation of domestic and foreign production ([1] S. A. Dyatlov, R. V. Bessonov, Review of star sensors of orientation of spacecraft, Mechanics, Control and Informatics, No. 1, pp. 11-31, 2009 ) Star sensors that determine orientation parameters by comparing the image of the observed portion of the starry sky with the star catalog stored in the on-board computer memory began to be used as a means of measuring the orientation parameters of spacecraft (SC) in the late 80s. last century.

Currently, there are more than 10 manufacturers of stellar devices abroad, which produce more than 30 models of various types and purposes. In Russia, star sensors were also developed by the IKI RAS and the Mars IKB organizations, which the Yamal, BelKA, Monitor, etc. spacecraft were equipped with. However, these sensors are not autonomous, they use the onboard computer computing power to process the data. . Another organization is OAO NPP Geofizika-Cosmos, which is currently developing wide-field stellar instruments, but there have not yet been flight tests of these instruments.

One of the main leaders in the production of stellar devices is the French company SODERN, which produces stand-alone devices, i.e. able to determine orientation parameters using their own computing tools. At first, the company developed the designs of the star sensor in the form of a monoblock, however, due to mechanical distortions in the optical channel arising from the uneven distribution of temperature, the developers went to the separation of the monoblock, while it was possible to reduce the systematic error of the device and achieve accuracy in determining the direction of the optical axes. But the division into two blocks (the electronics block and the optical block) led to an increase in the mass and size of the device. In 2003, the company began the development of a new star sensor based on a CMOS sensor. The sensor consists of three or four optical heads and two electronics units, as a result of which the measurement accuracy has increased, but the mass and dimensions of the sensor have significantly increased.

The main manufacturers of stellar sensors (German company Jena-Optronik, Italian Galileo Avionica, American Ball Aerospace and Goodrich, Canadian EMS Technologies) produce stellar sensors consisting of two units - an electronics unit and an optical unit, which leads to an increase in mass (from 1.5 kg to 7 kg) and sensor dimensions; at the same time, the accuracy assessment of different manufacturers is ambiguous.

Given the fact that when launching spacecraft into orbit, every gram of cargo, as well as its size, is taken into account, significant disadvantages of the known stellar sensors are their relatively high mass and large dimensions.

The closest analogue of the claimed invention is a device for determining the coordinates of stars (stellar orientation sensor) [2] (see patent No. 111280, IPC G01C 21/00, publ. 10.12.2011). The device comprises a housing, a lens, an array photodetector, a lens hood and an electronic unit for processing information and calculating angular coordinates. A catalog of nautical stars is stored in the memory of the electronics unit, which without fail contains their coordinates in one of the celestial coordinate systems.

The disadvantages of the above analogues and prototype are large dimensions due to the presence of several blocks and poor heat dissipation.

SUMMARY OF THE INVENTION

The problem solved by the claimed invention is to reduce the mass and dimensions of the device, as well as ensuring the best heat dissipation from the electronic components of the sensor.

The technical result of the invention is to reduce the mass and dimensions of the device, as well as to increase heat dissipation.

The specified technical result is ensured by a device for determining the orientation of an object by stars, containing a housing, an optical system, a lens hood, a radiation matrix detector, a computing device (microprocessor), and an electronic memory containing an on-board catalog of navigation stars, and to reduce its size and mass, and Also, to ensure the best heat dissipation from the electronic components of the sensor, a well-mounted sensor arrangement is used, in which the optical system and the lens hood are combined in a central the ith module, partially located inside the sensor housing, while the hood is the holder of the optical system, and the central module is the housing cover; around the central module there is an electronic single board, which is fixed to the side walls and the base of the case with screws, the board includes flexible sections along which the board is bent so that the main heat-generating elements are pressed against the side walls of the case, and the matrix radiation receiver is against the base of the case, heat is discharged from the walls and base of the casing by conductive heat transfer due to heat conduction through at least three mounting tabs of the casing base and partly due to radiant heat BMENA the inner surface of the built-blend.

In addition, to cool the matrix radiation detector below the temperature of the sensor seat, a Peltier thermoelectric cooler is used, installed in the cutout of the board under the bottom surface of the matrix radiation receiver and in contact with the base of the housing through a heat-conducting paste.

In this case, the microprocessor and electronic memory are installed on a single board with flexible connecting sections.

Brief Description of the Drawings

FIG. 1 is a general view of a stellar sensor.

FIG. 2 is a sectional view of a star sensor.

FIG. 3a and FIG. 3c is a general view of an electronic single board with flexible jumpers.

FIG. 4a and FIG. 4c is a general view of a well arrangement of a sensor with an electronic single board placed around a central module.

Disclosure of invention

Items shown in the drawings:

1 - housing;

2 - optical system (lens);

3 - a hood;

4 - matrix radiation receiver;

5 - the central module;

6 - electronic single board;

7 - flexible sections of the electronic single board;

8 - thermoelectric Peltier cooler;

9 is a plate that performs the function of a housing cover.

The present invention discloses a device for determining the orientation of an object by stars, namely a star orientation sensor, comprising a housing (1), an optical system (lens) (2), a lens hood (3), a radiation matrix receiver (4), a computing device (microprocessor) , electronic memory containing an on-board catalog of nautical stars.

In order to reduce the dimensions and mass of 3D and to provide better cooling of the heat-generating elements of the board, the well layout of the sensor was used (layout scheme “well”). In this scheme, the optical system (lens) (2) and the hood (3) are combined into a central module (5), partially inserted inside the 3D housing (1). Moreover, the central module (5) can be divided into two parts: the first - extends beyond the housing and includes the upper part of the hood, and the second - located inside the housing and containing the lower part of the hood and the optical system, while the hood is the holder of the optical system. Between the first and second parts there is a plate (9) perpendicular to the axis of the sensor, which acts as a housing cover.

In order to improve the manufacturability of manufacturing 3D boards and increase the reliability of their connection, Rigid-Flex technology was used, which completely eliminates the on-board connectors and cables. The 3D board is a single electronic board (6) connected by jumpers from the flexible upper layers (7), through which the signal is transmitted. The presence of flexible jumpers (7) (flexible sections) on the board allows it to take a three-dimensional shape in accordance with the internal layout of 3D without connectors and soldered conductors, as well as have sufficient freedom of movement of the components of the board during its installation in the 3D housing.

A single electronic board (6) is placed around the central module (5) and is fixed to the side walls and the base of the housing with screws. The board includes flexible sections along which the board is bent so that the main heat-generating elements are pressed against the side walls of the housing, and the matrix radiation detector is against the base of the housing.

The total increase in the dark current and related noise caused by the action of energetic cosmic particles on the matrix radiation detector can be reduced by cooling the matrix radiation detector, because dark currents decrease by about 2 times when the temperature decreases by 5 ° C [3] (CCD47-20 Back Illuminated High Performance ΑΙΜΟ Back Illuminated CCD Sensor, e2v technologies inc., A1A-100041 Iss. 6, 2006). The matrix radiation receiver can be cooled, for example, using a thermoelectric refrigerator (Peltier element) mounted on the matrix receiver from below.

The main heat removal from the walls and the base of the housing is carried out by conductive heat transfer due to heat conduction through at least three mounting tabs of the base of the housing and partly due to radiant heat transfer from the inner surface of the integrated hood.

The part of the flexible board on which the matrix radiation detector is located is located at the base of the case and has the best conditions for heat dissipation. A Peltier thermoelectric cooler (8) is installed on the matrix radiation detector (4) below, in the board window, which contacts the receiver and the base through a heat-conducting paste or gasket. The board with the receiver is attracted to the base with screws.

For the best cooling of the remaining heat-generating microcircuits, they are placed on a voluminously folded single electronic board (6) inserted into the sensor housing (1), so as to have contact with the side walls of the housing. Heat-conducting paste or gasket is also applied to the surfaces of the microchips in contact with the case, and the corresponding components of the common board are attracted to the case wall by screws. Flexible jumpers of the board allow its main parts to move within the necessary limits for reliable contact with the heat-removing walls and the base.

Claims (3)

1. A device for determining the orientation of an object by stars, comprising a housing (1), an optical system (2), a lens hood (3), a radiation matrix receiver (4), a computing device (microprocessor), electronic memory containing an on-board catalog of navigation stars, characterized in order to reduce its dimensions and weight, as well as to ensure the best heat dissipation from the electronic components of the sensor, a well layout of the sensor is used, in which the optical system and the lens hood are combined in the central module (5), partially located first sensor within the housing, the optical system is a blend of the holder, and the central module is a housing cover; around the central module there is an electronic single board (6), which is fixed to the side walls and the base of the case with screws, the board includes flexible sections (7) along which the board is bent so that the main heat-generating elements are pressed against the side walls of the case, and the radiation matrix receiver to the base of the housing, while the heat is removed from the walls and base of the housing by conductive heat transfer due to heat conduction through at least three mounting tabs of the housing base and partially due to radiant ploobmena the inner surface of the built-blend. 2. The device according to claim 1, characterized in that a Peltier thermoelectric cooler (8) is used to cool the matrix radiation detector below the temperature of the sensor seat, installed in the cutout of the board under the lower surface of the radiation matrix receiver and in contact with the base of the housing through a heat-conducting paste or gasket . 3. The device according to claim 1, characterized in that the microprocessor and electronic memory are mounted on a single board having flexible connecting sections.

Images