RU2619151C2 - Method of electric checks of spacecraft - Google Patents

Abstract

FIELD: electricity.

SUBSTANCE: cyclegramm of electrical inspections of the spacecrafts (SC) (1) are incorporated in the unit (4.1) of forming the operator's directive. When connecting or disconnecting the on-board AC sources (solar or rechargeable batteries) or ground simulators IBC (2) and IAB (3) - tolerance control of discrete and analog parametersis held according to the on-board telemetry and control system. Controlled by the insulation resistance of the tire bead, the directive and the test report are formed, where their current status is shown. Connecting the simulators IBC (2) and IAB (3) they establish protection for max. magnitude of the output current in two phases: min. value - at the first stage and for the required subsequent work - in the second stage. If tripping is blocked by the inclusion of the spacecraft (1) to eliminate the emergency situation (eg, A short circuit).

EFFECT: increased process reliability of electrical inspections of spacecraft.

1 dwg

Description

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

When creating the spacecraft, much attention is paid to ensuring a high degree of verification of the completing equipment of the spacecraft both individually and in interaction with each other.

This problem can only be solved if the broad functional capabilities of the technological process of electric checks of the spacecraft are provided and the test equipment is improved.

The 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” (patent RU No. 2245825), which consists in the automated issuance of technological commands and radio commands, tolerance control of discrete and analog parameters according to the on-board system telemetry and monitoring set on-board parameters of the onboard computer system, monitoring the insulation resistance of the onboard tires relative to the housing, forms manual operator guidelines, generating a test report, displaying the current status of the test process.

The disadvantage of the known method of electrical checks of the spacecraft is the lack of protection against the occurrence of abnormal short circuits at the stages of conducting mechanical work with the spacecraft, or the appearance of failures in the onboard or ground equipment between the various stages of electrical checks of the spacecraft.

The closest technical solution is the method of electrical checks of the spacecraft (patent RU No. 2447002), which is selected as a prototype.

The known method consists in turning the spacecraft on and off, including connecting or disconnecting on-board power sources or their ground simulators, automated issuing control commands, tolerance control of discrete and analog parameters according to the on-board telemetry system and monitoring the parameters of the on-board computer system, resistance monitoring insulation of the tires on the chassis, the formation of directives of the automatic program and the directives of the operator in manual mode, the formation of the 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 sources or their ground simulators, they additionally monitor the electrical resistance between the power lines of the spacecraft for compliance with its predetermined value, and when its inconsistencies in advance of the set value, the inclusion of the spacecraft is prohibited.

The disadvantage of the known method of electrical checks of the spacecraft is that the measurement of resistance between the power rails is carried out not at each turn-on, but mainly in especially critical cases, which does not fully guarantee the trouble-free operation.

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

The problem is solved in that when turning the spacecraft on and off, including connecting or disconnecting onboard power supplies or their ground simulators, automated issuing control commands, tolerance control of discrete and analog parameters according to the onboard telemetry system and monitoring the onboard computing parameters systems, monitoring the insulation resistance of airborne tires relative to the body, the formation of automatic program directives and operator’s directives in manual mode, generating a test report, displaying the current state of the test process, during the launch of the spacecraft, when connecting ground-based simulators of onboard power supplies, they are protected by the maximum output current in two stages: the minimum value is before connecting their outputs and the amount required for subsequent work - after connecting their outputs, and when the protection is activated by the output current of any ground simulator, anovku protection on the maximum value of the output current required for the subsequent work, and the further inclusion spacecraft block.

Indeed, during mechanical work with the spacecraft, short-circuit circuits can be formed abnormally, both due to improper assembly of the electrical circuits of the spacecraft and test circuits, and in the event of a malfunction in the onboard and ground equipment. In this case, the subsequent inclusion of the spacecraft can lead to serious negative consequences associated with tangible financial losses.

Currently, on a new generation spacecraft, one power bus is electrically connected to the hull. This gives a positive effect in protection against electrostatic discharges and reduces the level of interference on the busbars, however, this fact significantly increases the possibility of a short circuit between the SC power buses.

The occurrence of a short circuit between the power supply lines of the spacecraft can be detected in a timely manner if, at the stage of switching on the spacecraft, the electrical resistance between the power lines of the spacecraft is measured by flowing around the power lines with low current (from microamps to several milliamps, for example, using a multimeter).

However, during the electrical checks of the spacecraft, its numerous on and off operations are carried out, and resistance measurement between the tires is carried out in especially critical cases. This reduces the reliability of the process of electrical checks of the spacecraft. The claimed invention implements the technology of non-alternative protection of the spacecraft from emergency emergencies associated with increased current consumption by installing a mandatory protective "barrier" at the stage of inclusion of the spacecraft.

The essence of the claimed invention is illustrated by the drawing, FIG. 1, which shows a block diagram of a ground-based control and monitoring system for electrical checks of the spacecraft (the structure of the spacecraft instrumentation is not shown).

The spacecraft (KA) 1 contains, in particular, a power supply system with on-board power sources (solar and rechargeable batteries) and a stabilized voltage converter with charge and discharge converters to coordinate the operation of solar and rechargeable batteries and provide a stable voltage with a given nominal value of service system modules and payload, onboard telemetry system, onboard computer (not shown in the diagram).

During electrical checks of the spacecraft, instead of solar and rechargeable batteries, simulators of solar batteries (IHD) 2 with built-in computers 2-1 and simulators of rechargeable batteries (IAB) 3 with built-in computers 3-1 are connected.

The control and monitoring system of the spacecraft electrical checks contains:

4 - automated test complex (AIC);

4.1 - Directive formation unit - as part of the AIC;

5 - AIK computer (control unit and display information from AIK).

The computers 2-1 and 3-1 built into the IHD and IAB are connected via an inter-machine exchange (via Ethernet) with the AIK 5 computer.

AIK 4, together with AIK 5 computer and directive formation unit 4.1, provides automated issuing of control commands, tolerance control of discrete and analog parameters of KA 1 according to the on-board telemetry and monitoring system parameters of the onboard computer system, monitoring the insulation resistance of the onboard tires relative to the chassis, formation directives of the automatic program and operator directives in manual mode, the formation of the test report, displaying the current state of the test process .

The connection of the AIK 5 computer with the IHD 2-1 computer and the IAB 3-1 computer allows you to control the current operating modes of the IHD 2 and IAB 3 and to obtain operational information about their current output parameters (voltage, current).

The system operates as follows. Cyclograms of various electrical checks, including cyclograms of turning on and off the spacecraft, are automatically inserted into the operator directive 4.1 generation unit in automatic mode. The operator, through the operator’s directive drafting unit, manually launches the required sequence diagram for turning the spacecraft on and off, including connecting or disconnecting the onboard power supplies or their ground simulators IHD 2 and IAB 3, automatically issuing control commands, tolerance control of discrete and analog parameters according to on-board system for telemetry and monitoring set on-board parameters of the on-board computer system, monitoring the insulation resistance of the onboard output tires relative to the housing, the formation of automatic program directives and operator directives, the formation of a test report, and the display of the current state of the test process. In the process of turning on the spacecraft 1, when connecting ground-based simulators of on-board power sources IBS 2 and IAB 3, they are protected by the maximum value of the output current in two stages: the minimum value is the first stage and the value required for subsequent work is the second stage. If the current protection in IHD 2 or IAB 3 is activated, the inclusion of KA 1 is blocked until the non-compliance is eliminated.

Consider a specific example of turning on the spacecraft. Suppose that the spacecraft load current consumption is 50 A. We set the protection at the first stage of turning on ground-based simulators of on-board sources at a level of 1 A (safe value in case of an emergency short circuit). At the stage of switching on ground-based simulators of on-board sources, there should be no consumption from their outputs until the spacecraft is turned on. If the protection is triggered, it means that there is an abnormal short circuit somewhere. The inclusion process is stopped and analysis and elimination of contingencies are carried out. If the protection did not work (regular case), we switch the protection to 60 A and the spacecraft continues to turn on.

Thus, the proposed method of electrical checks of the spacecraft increases the reliability of the process of electrical checks of the spacecraft in the manufacturing process.

Claims (1)

The method of electrical checks of spacecraft, which consists in turning the spacecraft on and off, including connecting or disconnecting on-board power supplies or their ground simulators, automated issuing control commands, tolerance control of discrete and analog parameters according to the on-board telemetry system and monitoring the on-board tracking parameters computing system, monitoring the insulation resistance of airborne tires relative to the body, the formation of directors In addition to automatic program and operator’s directives in manual mode, generating a test report, displaying the current state of the test process, characterized in that during the switching on of the spacecraft, when ground-based simulators of on-board power supplies are connected, they are protected by the maximum output current in two stages : the minimum value - before connecting the outputs of the specified simulators and the amount required for subsequent work - after connecting the outputs of the simulators, and When protection is activated by an output current of a ground simulator protection setting on the maximum value of the output current required for the subsequent work, and the further inclusion spacecraft block.

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