RU2513322C2 - Method of electric checkouts for space vehicles - Google Patents

Abstract

FIELD: electricity.

SUBSTANCE: invention relates to ground testing of electrical systems of spacecrafts (SC). The method lies in switching SC on and off, including connection and disconnection from SC (10) of solar (8) and accumulator (9) battery simulators. The simulators are connected to SC through connectors (2-1, 3-1) and (5-1) respectively to the switch (5-3) and also through stabilised voltage converter (4). Power supply of the simulators (8, 9) is made from an industrial network through cables (8-1) and (9-1). At that solar battery (1) as a rule is disconnected from SC (connectors 2 and 2-1, 3 and 3-1 are open). Accumulator battery (5) from its positive side is disconnected (connectors 5-2 and 5-1 are open) from charge (6) and discharge (7) converters. An automated testing system (11) is connected to SC (10) with built-in cycle schemes for different electrical checkouts of SC and schemes of its connection/disconnection. In process of checkouts control is carried out for monitored parameters, including output current of simulators (9). This current value serves as an additional proof of SC switching on/off.

EFFECT: improving reliability and expanding functionality for the process of SC electrical checkouts.

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Description

The claimed invention relates to the electrical industry and can be used in the manufacture of spacecraft (SC).

When creating a spacecraft, much attention is paid to ensuring a high degree of reliability of electrical checks.

This problem can only be solved if multi-level control of the technological process of the spacecraft electrical checks is ensured.

A known method of electrical checks of the spacecraft, implemented by the "Automated test system for testing, electrical checks and preparation for the launch of spacecraft", described in the materials of patent No. 22585825.

The known method consists in the automated issuance of technological commands and radio commands, the tolerance control of discrete and analog parameters according to the on-board telemetry system and the monitoring of the on-board computer system parameters monitored, the insulation resistance of the airborne tires relative to the chassis, the formation of operator directives in manual mode, the generation of a test report displaying the current state of the test process.

A disadvantage of the known method of electrical checks of the spacecraft is the lack of protection against emergency situations associated with incomplete shutdown of the spacecraft during interruptions in working with it, in the event of any malfunctions in the onboard or ground equipment at various stages of the electrical checks of the spacecraft.

The closest technical solution is the method of electrical checks of the spacecraft, described in the materials of the application No. 2010141494 dated October 8, 2010 (positive decision dated October 11, 2011), which is selected as a prototype.

The known method consists in turning the spacecraft on and off, including connecting or disconnecting the onboard power sources or their ground simulators, automated issuing control commands, tolerance control of discrete and analog parameters according to the onboard telemetry system and monitoring the on-board computing system monitoring parameters, control insulation resistance of airborne tires relative to the body, the formation of automatic program directives and directives in the operator in manual mode, generating a test report, displaying the current state of the test process, characterized in that in the process of turning on the spacecraft before connecting the onboard power supplies or their ground simulators, they additionally control the electrical resistance between the power buses of the spacecraft for compliance with its predetermined value, and if it does not meet the predetermined value, the inclusion of the spacecraft is prohibited.

The known method allows you to timely detect the occurrence of an abnormal short circuit on the tires off the spacecraft, however, it does not protect against cases associated with incomplete shutdown of the spacecraft during interruptions in working with it. It should be noted that incomplete shutdown of the spacecraft leads to overdischarge of the batteries, the spacecraft onboard equipment falling under the influence of the supply voltage below the agreed value, which in turn leads to financial losses.

The task of the invention is to increase reliability and expand the functionality of the process of electrical checks of the spacecraft.

The problem is solved in that when conducting electrical checks of the spacecraft, which include turning the spacecraft on and off, including connecting or disconnecting the solar and battery simulators to the spacecraft, and monitoring the parameters set for tracking, including monitoring the output current of the battery simulators, the fact of turning the spacecraft on and off is additionally judged by the output current of the battery simulators.

Indeed, when conducting electrical checks of the spacecraft, simulators of batteries are currently widely used, which makes it possible to verify the operation of the automation of the spacecraft in the entire range of battery voltages and their signal parameters. In addition, the use of battery simulators does not require long preliminary preparation (in contrast to batteries), which reduces the time required for electrical tests of the spacecraft as a whole.

Moreover, the use of battery simulators located outside the spacecraft allows, in particular, to control their output currents at any time, regardless of the operation of the spacecraft and its own or other ground-based means. Moreover, the results of the control can be used to influence other hardware that provides electrical checks of the spacecraft. Moreover, an additional level of control allows to increase the reliability of the process of electrical checks of the spacecraft.

In addition, the proposed method allows you to directly measure the output currents of battery simulators with the spacecraft turned off, which are essentially the leakage currents of the onboard batteries in the subsequent standard configuration of the spacecraft.

Figure 1 shows the functional diagram of an autonomous power supply system as part of the spacecraft (with ground communications), explaining the work on the proposed method of electrical checks of the spacecraft.

A solar battery 1 containing blocking diodes 1-1, as a rule, is in the process of manufacturing a spacecraft in the undocked state from the spacecraft (connectors 2 and 2-1, 3 and 3-1 are undocked). On the spacecraft, the solar battery 1 is installed (and docked) for the duration of testing the spacecraft for mechanical stress, as well as to control the docking of solar panels with the spacecraft. In some cases, for example, with non-oriented solar batteries, the solar battery is constantly in the spacecraft and is electrically connected to it, and ground-based simulators of the solar battery are connected to specially provided technological connectors (taps) parallel to the solar battery. In this case, the blocking diodes 1-1 protect the solar battery from the flow of the so-called "dark" current.

In the presented example, the solar battery 1 is electrically undocked from the spacecraft 10. The power supply system is made with a common negative bus. The stabilized voltage converter for coordinating the operation of the solar 1 and rechargeable 5 batteries and providing a stable voltage for the specified nominal value of the service system modules and the payload (to the right of the output buses “+” and “-” is not shown in the drawing) consists of a charging converter 6, a discharge converter 7 and output voltage stabilizer 4. Battery (in this example, one battery is used) 5 minus connected to the common negative bus, and plus through the connectors 5-2 5-1 (in the drawing these connectors undocked) from the charging and discharge transducers (connection information storage battery 5 is not shown). Instead of solar panels, the input of a stabilized voltage converter through connectors 2-1 and 3-1 is connected to a solar simulator (IHD) 8, and instead of a rechargeable battery 5, a battery simulator (IAB) 9 is connected to a charging 6 and discharge 7 converters (information connections of the simulator) battery 9 not shown). At the same time, in the solar connection circuit there is a switch 2-2, and in the battery connection circuit there is a switch 5-3, which are open in the off state of the spacecraft.

The simulator of the solar battery 8 and the simulator of the battery 9 is powered from an industrial network 220/380 V via cables 8-1 and 9-1, respectively.

The bulk of the electrical checks of the spacecraft is carried out using simulators of solar 8 and 9 rechargeable batteries. This allows you to quickly carry out the development of the spacecraft in any modes associated with the state of solar 1 and 5 rechargeable batteries with respect to the interface with a stabilized voltage converter, which is almost always impossible to implement when working out the spacecraft in a standard configuration. Regular batteries 5 are stored electrically isolated (excluding leakage currents) with a stabilized voltage converter, in a recharged state. An automated test complex (AIC) 11 is connected to the spacecraft KA 10, which has an information connection with IAB 9.

In AIC 11, cyclograms of various electrical checks are laid down, including cyclograms of turning on and off the spacecraft 10. The operator, through the operator directive generation unit, manually starts the required cyclogram. Next, the process goes automatically. The current work data is stored and displayed on the display unit (PC monitor - not shown in the drawing).

Before turning on-board power sources (or their simulators), the IAB output current is monitored and documented.

If the measured value of the output current of the IAB 9 does not correspond to the predetermined value, the inclusion of the spacecraft is blocked until the discrepancy is eliminated.

If during the shutdown of the spacecraft, after disconnecting the battery simulators from the spacecraft, the output current of the IAB does not correspond to its predetermined value, the shutdown of the spacecraft is not achieved.

Thus, the proposed method of electric checks of the spacecraft increases the reliability and extends the functionality of the process of electrical checks of the spacecraft.

Claims (1)

The method of electrical checks of the spacecraft, which consists in turning the spacecraft on and off, including connecting or disconnecting the solar and battery simulators to the spacecraft, and monitoring the parameters set for tracking, including monitoring the output current of the battery simulators, characterized in that it is about turning on and turning off the spacecraft is additionally judged by the output current of the battery simulators.