RU97983U1 - SYSTEM OF THERMAL STABILIZATION OF THE ON-BOARD RECORDING EQUIPMENT OF THE SPACE VEHICLE - Google Patents

Abstract

 1. The thermal stabilization system of the onboard recording equipment of the spacecraft, comprising a low voltage power supply unit, a switch connected to it, and at least one channel of the onboard recording equipment connected to the switch, the channel of the onboard recording equipment including:! a high voltage power system comprising at least two sections of a high voltage power system,! on-board recording equipment containing at least two recording units, each of which is connected to the corresponding section of the high-voltage power supply system,! and a temperature sensor that measures the temperature of the onboard recording equipment and a control unit associated with temperature sensors of each channel of the onboard recording equipment, the switch being able to distribute power from the low voltage power supply to each section of the high voltage power supply system of each channel of the onboard recording equipment, and the control unit by signal with a temperature sensor about exceeding a predetermined temperature regime of the channel of the onboard recording equipment, it has the ability to send a comm tator for limiting the energy consumption of the corresponding channel of the on-board recording equipment by turning off individual sections of high-voltage power. ! 2. The thermal stabilization system of the onboard recording equipment of the spacecraft according to claim 1, characterized in that the switch is a multi-channel electronic key. ! 3. The thermal stabilization system of the onboard recording equipment of the spacecraft according to claim 1, characterized in that the onboard recording apparatus

Description

The utility model relates to devices used on spacecraft (hereinafter referred to as spacecraft) for the effective thermal stabilization of the recording spacecraft onboard equipment in open space.

A number of thermal stabilization systems of various equipment are known, see, for example, the description [1]. Thermostabilization of the equipment in these devices is carried out forcibly - by thermal batteries, which are turned on depending on the readings of the temperature sensor. The disadvantage of these devices is the low reliability and high power consumption.

The known system of temperature control equipment leaky insulated container of a spacecraft [2]. In this device, the thermal stabilization of the spacecraft equipment is carried out passively, by means of heat pipes with diode thermal contactors and a heat exchanger that dissipates heat in open space, on the dark and, accordingly, cold side of the spacecraft. The disadvantage of this thermal stabilization system is its high inertia. Another disadvantage of this system is the low cooling capacity of the system, when using on the spacecraft a very hot recording equipment on board.

Also known is the temperature control system of a temperature-sensitive element described in [3]. In this device, a sensor is located on the temperature-sensitive element, which measures the temperature and, if it is exceeded, issues a command to the key to open the circuit, thereby saving the temperature-sensitive element from abnormal operation. The disadvantage of this system is that under adverse temperature conditions, the temperature-sensitive element does not work.

The proposed system of thermal stabilization of the onboard recording equipment of the spacecraft eliminates the above disadvantages of the known devices.

A specific feature of the spacecraft’s onboard recording equipment is the registration of intense particle flows (up to a million particles per second), which leads to a sharp increase (up to 50%) in energy consumption from the registration system.

When operating the equipment, the following main problems arise:

1. A significant temperature gradient on the outer surface associated with the orbit of the spacecraft imposes restrictions on the technical capabilities of high-speed equipment.

2. The fact of the inertia of the on-board system for providing thermal conditions (ASEO - automatic electric heating system) - the reaction time of up to 5 minutes, which we tested in similar experiments carried out earlier, creates the prerequisites for overheating of the registration system, especially when working on the sunny side in intensive registration mode ( sharp increases in particle fluxes).

Therefore, in order to reliably ensure normal conditions during normal operation of the instrument onboard the spacecraft, it is necessary to have adequate feedback in the “detector - sectional high-voltage power supply” system, which allows to quickly remove heat load from part of the registration system (see the description of the device below) by reducing power consumption. Additionally, in the case of registration of very intense particle flows, it is possible, by disconnecting individual sections of the detector (channels of the recording on-board equipment), it is reasonable to limit the performance of the device (that is, reduce the flow of information) to adapt it to the low performance of the data channel of the on-board telemetry system to The earth.

The technical result is to minimize the power consumption of the spacecraft cooling system, increase the cooling efficiency of the onboard equipment, reduce the inertia of the onboard equipment cooling system and reduce the overall mass characteristics of the spacecraft cooling system.

The technical result is generally achieved by the fact that the thermal stabilization system of the onboard recording equipment of the spacecraft includes:

low voltage power supply unit;

the associated switch;

associated with the switch, at least one channel on-board recording equipment, and the channel on-board recording equipment includes:

- a high-voltage power system comprising at least two sections of a high-voltage power system;

- on-board recording equipment containing at least two registration units, each of which is associated with the corresponding section of the high-voltage power system;

- and a temperature sensor that measures the temperature of the onboard recording equipment;

and a control unit associated with temperature sensors of each channel of the on-board recording equipment;

the switch distributes power from the low-voltage power supply unit to each section of the high-voltage power supply system for each channel of the on-board recording equipment, and the control unit, by a signal from the temperature sensor that the specified temperature mode of the channel of the on-board recording equipment is exceeded, sends a signal to the switch to limit the power consumption of the corresponding channel of the on-board recording equipment , by turning off the individual sections of the high voltage power supply.

Preferably, the switch is a multi-channel electronic key.

Preferably, the on-board recording apparatus is a scintillation detector based on at least two recording units - photomultiplier tubes.

Preferably, the on-board recording apparatus is a system of scintillation detectors — an on-board scintillation spectrometer of charged particles.

Preferably, the control unit is a microcontroller containing an amplitude-to-digital converter for digitizing signals from temperature sensors.

Preferably, the temperature sensor on-board recording equipment was installed on its surface.

In addition, it is preferable that the low-voltage power supply unit be connected to the onboard network of the spacecraft with a voltage of +28 V and have an output of +12 V.

In addition, it is preferable that each section of the high-voltage power supply system includes a +12 V to -1000 V voltage converter for supplying the respective recording units, photoelectronic multipliers.

It is also preferable that this system is housed in an unpressurized enclosure, sheathed with thermal insulation and installed on the outer surface of the spacecraft and operate in the temperature range from minus 100 to plus 100 degrees Celsius at the installation site.

It is also preferable that this system has electric heaters installed on the inner surface of the housing, turned on when the temperature reaches the lower limit point and turned off when the temperature reaches the upper temperature limit point.

It is also preferable that in this system the points of the lower and upper limit values are the temperature values plus 5 and plus 30 degrees Celsius, respectively.

Thus, the proposed technical solution is a combination of essential features that, in comparison with the prototype, have novelty.

Figure 1 shows a diagram of a device.

The proposed device shown in figure 1 contains:

1 - low-voltage power system (hereinafter referred to as SPS),

2 - high-voltage power system (hereinafter referred to as SVP),

2 (1) - the first section of the SVP,

2 (2) - the second section of the SVP,

3 - on-board recording equipment,

3 (1) - the first registration unit on-board recording equipment,

3 (2) - the second unit for recording on-board recording equipment,

4 - switch

5 - temperature sensor,

6 - control unit.

The device operates as follows.

The device is powered from the spacecraft’s onboard network with a voltage of +28 V and through SNP (1) receives an intermediate voltage of +12 V, which through the control switch (4) controls the onboard recording equipment (3 (1) and 3 (2)), through control actions from the unit control (6), in this case, a microcontroller with integrated ADC, enters the channel (s) of the on-board recording equipment to all sections of the SVP (2 (1) and 2 (2)). Each section of the SVP (2 (1) and 2 (2)) converts +12 V voltage to voltage (-1000 V) to power the first and second registration units of the on-board recording equipment (3 (1) and 3 (2)), which are on-board spacecraft recording equipment. When registering an intense flow of particles and being on the sunny side of the SC orbit, the control unit accurately monitors the temperature of the on-board recording equipment using temperature sensors (5) located on the base of the on-board recording equipment of each channel. The outputs of the temperature sensors (5) are fed to the inputs of the ADC built into the microcontroller (6). The microcontroller periodically processes the digitization of the readings of the temperature sensors (a separate temperature sensor can be installed for each PMT separately) and, when the set temperature is exceeded, it issues a control pulse to the switch (4) to control the power of the on-board recording equipment (3 (1) and 3 (2 )), or rather, to disable at least one section of the high-voltage power system (2 (1) and 2 (2)) and the corresponding registration unit - PMT, where the maximum particle registration intensity is observed. Further, as the transition period of measurements is established, either a mode of lowering the temperature or a mode of its further growth are possible. In the first case, while continuing to record the intense flow, it is possible either to continue the shutdown mode of such channels (until a stable position of the temperature value is within the specified limits), or a phased turn on of the channels. In the second case (continued increase in temperature), only the channels of neighboring PMTs are turned off, up to a steady decrease in temperature to predetermined limits. Accordingly, it is worth noting that the more channels of the on-board recording equipment and sections of the high-voltage power system are used on the spacecraft, the faster (for example, due to manipulations with the intra-unit sections) and the more stable (due to smaller steps in the transition period) thermostabilization of the on-board recording spacecraft equipment, while maintaining its operation with a known and lesser decrease in accuracy (since the accuracy of registration, as you know, depends, first of all, on the number of registered channels).

In the described system, the power consumption of the spacecraft cooling system is minimized by using only the internal resources of the recording equipment (without involving conventional spacecraft cooling systems), increasing the cooling efficiency of the onboard equipment is to save the resources of the onboard cooling system, including saving the radiation surface of the spacecraft, reducing inertia cooling of the on-board equipment is achieved due to the feedback speed of the “temperature sensor - channel switch” system, however ec, reducing the dimensions and weight of the overall characteristics of the cooling system is to use a smaller area radiation surface SC by the use of its own, autonomous from the spacecraft, the system temperature heat setting.

Thus, the presented system of thermal stabilization of the onboard recording equipment of the spacecraft allows the temperature control of the onboard equipment in the temperature range from plus 5 to plus 30 degrees Celsius in space vacuum at the installation site on the outer surface of the spacecraft in the temperature range from minus 100 to plus 100 degrees Celsius .

Literature.

1. Patent RU 2199777 C2 of 02.27.2003

2. Patent RU 2034756 C1 of 05/10/1995.

3. Patent EP 0138069 A2 of 04.24.1985.

Claims (10)

1. The thermal stabilization system of the on-board recording equipment of the spacecraft, comprising a low-voltage power unit, a switch connected to it, and at least one channel of the on-board recording equipment connected to the switch, the channel of the on-board recording equipment includes: a high voltage power system comprising at least two sections of a high voltage power system, on-board recording equipment containing at least two recording units, each of which is associated with the corresponding section of the high-voltage power system, and a temperature sensor that measures the temperature of the onboard recording equipment and a control unit associated with temperature sensors of each channel of the onboard recording equipment, the switch being able to distribute power from the low voltage power supply to each section of the high voltage power supply system of each channel of the onboard recording equipment, and the control unit by signal with a temperature sensor about exceeding a predetermined temperature regime of the channel of the onboard recording equipment, it has the ability to send a comm tator for limiting the energy consumption of the corresponding channel of the on-board recording equipment by turning off individual sections of high-voltage power. 2. The thermal stabilization system of the onboard recording equipment of the spacecraft according to claim 1, characterized in that the switch is a multi-channel electronic key. 3. The thermal stabilization system of the onboard recording equipment of the spacecraft according to claim 1, characterized in that the onboard recording equipment is a scintillation detector based on at least two recording units - photoelectronic multipliers. 4. The thermal stabilization system of the onboard recording equipment of the spacecraft according to claim 1, characterized in that the onboard recording equipment is a system of scintillation detectors - an onboard scintillation spectrometer of charged particles. 5. The thermal stabilization system of the onboard recording equipment of the spacecraft according to claim 1, characterized in that the control unit is a microcontroller containing an amplitude-to-digital converter for digitizing signals from temperature sensors. 6. The thermal stabilization system of the onboard recording equipment of the spacecraft according to claim 1, characterized in that the temperature sensor of the onboard recording equipment is installed on its surface. 7. The system of thermal stabilization of the onboard recording equipment of the spacecraft according to claim 1, characterized in that the low-voltage power unit is connected to the onboard network of the spacecraft by a voltage of +28 V and has an output of +12 V. 8. The system of thermal stabilization of the onboard recording equipment of the spacecraft according to claim 1, characterized in that each section of the high-voltage power system includes a voltage converter +12 V to -1000 V for supplying the respective registration units - photoelectronic multipliers. 9. The thermal stabilization system of the onboard recording equipment of the spacecraft according to claim 1, characterized in that the system is housed in an unpressurized enclosure covered by thermal insulation and has the ability to function on the outer surface of the spacecraft in the range from -100 to + 100 ° C at the installation site . 10. The thermal stabilization system of the onboard recording equipment of the spacecraft according to claim 9, characterized in that the system has electric heaters installed on the inner surface of the body, which can be turned on when the temperature reaches the lower limit point and turn off when the temperature on the body points of the upper limit value.