RU2456639C1 - Device for recording parameters of micrometeoroids and space junk - Google Patents

Abstract

FIELD: physics.

SUBSTANCE: device for recording parameters of micrometeoroids and space junk, having a target in form of four solar panels connected to each other by a metal-insulator-metal film structure, an ion detector in form of a sphere, a measuring unit, electromagnets placed in fours on each axis of the device and connected to each other in series; the ion detector is in form of four microchannel plates, each lying parallel to the corresponding solar panel; on the outer side of the ion detector there is a solar sensor in form of a CCD matrix, connected to the measuring unit; on the front surface of the control unit there is a solar panel, on the side surfaces there are photodiodes and on the back side there is a photodiode and an antenna of a GPS receiver, wherein the ion detector, the metal-insulator-metal film structures and the photodiodes are respectively connected to units for measuring ions, conductivity of the film structures and photocurrent.

EFFECT: high efficiency of collecting ions with a receiver with large target surface area, faster operation of the control system.

1 dwg

Description

The invention is intended for use in space technology, in particular for the registration of micrometeoroids and charged particles of the ionosphere.

A device is known (a.c. N 1830499, IPC G01E 1/34, publ. 13.10.2002), which includes a flat target with holes, an ion receiver, an information processing unit.

The disadvantage of this device is the inability to use the target on a large area of the sensitive surface, and therefore, low efficiency.

A known device (Diretzel H., Eihborn etc The Heos 2 aud Helios micrometeoroid experiments. J.Phys.Sei. Justrum. 1973, 6, 3, p.209-217) is designed to record the parameters of micrometeoroids and contains a hemispherical target and a hemispherical ion receiver forms, measurement unit.

Another device (patent No. 2348949, IPC G01T 3/04, publ. 05.28.2007) is designed to detect micrometeoroid and technogenic particles, contains a target in the form of a film capacitor deposited on a metal plate, an ion receiver.

The disadvantages of such devices is the inability to use the target on a large area of the sensitive surface, and therefore, low efficiency.

As a prototype, a device was selected (patent No. 78956, IPC G01T 3/04, publ. 10.12.2008, Bull. No. 34), which includes a target from several solar panels interconnected by metal-dielectric-metal film structures, a receiver ions in the form of a ball; electromagnets of the control system.

The disadvantage of which is the weak collection of ions and the dependence of their quantity on the site of collision of high-speed particles with the target (solar panels), lack of information about the direction of the colliding particles, a long process of orientation of the device (in particular, to the Sun).

It is based on the task of increasing the efficiency of collecting ions by a receiver from a large target area (solar panels), depending on their impact location, the efficiency of solar panels aimed at the Sun, as well as improving the speed of the control system.

This problem is achieved due to the fact that in the device for recording the parameters of micrometeoroids and space debris containing a target in the form of four solar panels interconnected by a metal-dielectric-metal film structure, an ion receiver in the form of a ball, a measurement unit, electromagnets, characterized in that the electromagnets are installed in four pieces on each axis of the device and are connected together in series, the ion receiver is made in the form of four microchannel plates, each of which is a pair Along with the corresponding panel of the solar battery, on the outside of the ion receiver there is a solar sensor in the form of a CCD matrix connected to the measurement unit, a solar panel is installed on the front surface of the control unit, photodiodes are installed on the side surfaces, and a photodiode and antenna are installed on the back of it A GPS receiver, wherein the ion receiver, film structures metal-dielectric-metal, and photodiodes are connected respectively to units for measuring ions, conductivity of film structures, and photocurrents.

The invention is illustrated in the drawing, which shows the device in expanded form (operating mode).

The device for recording the parameters of micrometeoroids and space debris contains four solar panels 1 - a target, ion receivers 2, a solar sensor in the form of a CCD matrix 3, electromagnets 4, 5 and 6 are installed in three mutually orthogonal axes, four pieces per axis, solar panels are connected between each other with film structures metal-dielectric-metal 7 (target), the upper side of the control unit is a solar panel 8, a control unit with equipment 9, photodiodes 10 located on the sides of the control unit bottom and bottom, measuring unit 11, control unit 12 of the orientation system, GPS receiver 13 located at the bottom of the device.

The device operates as follows. When a micrometeoroid collides with targets 1 and 7, a plasma is formed at the point of contact, whose ions fall on the ion receiver 2. They are collected due to the voltage at the receiver equal to 250 V relative to the target. The output of the ion receiver is connected to amplifiers located at 11, which are necessary for the implementation of the registration mode of ions formed upon impact of high-speed particles (micrometeoroids or particles of space debris).

Films based on MDM structures are, like solar panels, the target of the device. When a particle hits one of the four MDM structures 7, it can short-circuit the power source or change the resistance between the capacitor plates. In this case, the capacitor (fully or partially) is discharged and the generated voltage pulse is amplified by the amplifier.

For the correct interpretation of the data on the parameters of cosmic dust, the orientation of the device (spacecraft) is necessary, which is carried out using the installed twelve electromagnets (4 on each axis), to which current pulses of the corresponding duration and amplitude are supplied from the control unit.

The control unit 12 implements the control law of the unloading of the kinetic moment of the spacecraft. This approach is based on the interaction of the executive bodies of the control system (electromagnets) with the Earth's magnetic field.

Control laws can be obtained from the basic equation for magnetic control systems:

,

,

- дипольный магнитный момент;

- вектор индукции магнитного поля Земли;

- вектор угловой скорости космического аппарата.Where

- dipole magnetic moment;

- vector of the induction of the Earth's magnetic field;

is the vector of the angular velocity of the spacecraft.

Claims (1)

A device for recording parameters of micrometeoroids and space debris, containing a target in the form of four solar panels connected to each other by a metal-dielectric-metal film structure, a ball-shaped ion receiver, a measurement unit, electromagnets, characterized in that four electromagnets are installed each the axis of the device is interconnected in series, the ion receiver is made in the form of four microchannel plates, each of which is parallel to the corresponding panel of the solar battery Rei, on the outside of the ion receiver, there is a CCD array of the Sun sensor connected to the measurement unit, a solar panel is installed on the front surface of the control unit, photodiodes are installed on the side surfaces, and a photodiode and GPS antenna are installed on the back of the unit, moreover, the ion detector, film metal-dielectric-metal structures and photodiodes are connected respectively to the units for measuring ions, conductivity of film structures and photocurrents.