RU2459749C1 - Method of producing space apparatus - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aerospace engineering and may be used in producing telecommunication space apparatuses. Proposed method comprises producing component parts, assembling space apparatus, preparing electric power sources for operation, conducting electric tests of space apparatus for operation, mechanical strength, heat-and-vacuum endurance, and final tests including control over attachment of solar and storage batteries. Mechanical tests and control over said attachment are conducted using standard storage and solar batteries. Prior to mechanical testing, storage batteries are charged under conditions identical to standard conditions of prelaunch charging. All other tests are conducted using handling functional simulators of solar and storage batteries. Note here that solar battery simulators are connected directly to industrial power supply while storage batteries connections are implemented in two ways: directly in the case of charging interface and via guaranteed power supply system in the case of discharging interface. Standard storage batteries are stored as-charged with disconnected stabilised voltage converter.

EFFECT: higher operating performances and test reliability.

2 cl, 1 dwg

Description

The invention relates to space technology and can be used to create a connected (telecommunication) spacecraft.

A known method of manufacturing a spacecraft, including the manufacture of components, assembly of the spacecraft, conducting electrical tests for functioning, tests for mechanical stress, thermal vacuum tests, as well as final tests for the functioning of the spacecraft (patent No. 2305058 RU).

The disadvantage of this method is that it does not regulate issues related to the features of the configuration of the power system in the manufacturing process of the spacecraft, which reduces the reliability of the work.

An analysis of the sources of information on patent and scientific and technical information showed that the closest in technical essence to the prototype of the proposed technical solution is the patent of the Russian Federation No. 2156211.

A method of manufacturing a spacecraft developed according to the above patent includes the following main steps:

- make components (including solar panels, a complex of automation and voltage stabilization, as well as batteries) and assemble the spacecraft;

- conduct electrical tests of the spacecraft for operation, while the onboard equipment is powered from onboard batteries or from ground sources to preserve the resource of onboard equipment.

The disadvantages of the known method of manufacturing a spacecraft are low functionality and reliability when conducting ground tests (including electrical tests) of the spacecraft. Namely, the transition to ground power limits the capabilities of the automation complex and voltage stabilization, which may contribute to its insufficient development. In addition, if the voltage of the industrial network disappears, the spacecraft may turn out to be (unpredictably) de-energized, which is fraught with negative consequences for it. The state of charge of onboard batteries in the manufacturing process of the spacecraft and the conditions for their storage are not defined, which does not contribute to the preservation of their resource characteristics.

The objective of the technical solution proposed by the authors is to increase the functionality and reliability of the electrical testing process, as well as to preserve the resource characteristics of onboard batteries.

The problem is solved in that during electrical tests of the spacecraft for functioning, mechanical stress tests, thermal vacuum tests, as well as final tests, including docking control, solar and rechargeable batteries, mechanical stress tests and docking control of solar and rechargeable batteries carried out with standard rechargeable and solar batteries, and rechargeable batteries before testing for exposure to mechanical loadings are charged in a mode equivalent to the regular prelaunch mode, and all other tests are carried out using technological functional simulators of solar and rechargeable batteries, moreover, solar simulators are connected directly to the industrial network, and battery simulators are connected to the industrial network in combination: via the charging interface - directly , and on the discharge interface - through the guaranteed power supply system, while storing regular batteries t electrically isolated from a stabilized voltage converter, in a recharged state. In addition, prior to monitoring the docking of batteries, they are stored outside the spacecraft at the optimum storage temperature, and their dimensional and weight simulators are temporarily installed on the spacecraft, if necessary.

As a result of the analysis of the known patent and scientific and technical literature, the proposed combination of significant distinguishing features of the claimed technical solution in the known sources of information is not revealed.

Figure 1 shows a functional diagram of an autonomous spacecraft power supply system (with ground communications), explaining the work on the proposed method for manufacturing a 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 and outside the spacecraft (connectors 2 and 2-1, 3 and 3-1 are undocked). Solar cells 1 are installed (and docked) on the spacecraft 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, solar panels are constantly in the spacecraft and are electrically connected to it, and ground-based solar battery simulators are connected to specially provided technological connectors (taps) in parallel with solar panels. In this case, the blocking diodes 1-1 protect the solar cells from the flow of the so-called "dark" current.

In the presented example, solar panels 1 are located outside the spacecraft. The power supply system is made with a common negative bus. A stabilized voltage converter for coordinating the operation of solar 1 and 5 rechargeable batteries and providing a stable voltage for a specified nominal value of service system modules and 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 the stabilizer of the output voltage 4. The 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, a simulator of solar batteries 8 is connected to the input of a stabilized voltage converter through connectors 2-1 and 3-1, and instead of a battery 5, a battery simulator 9 is connected to a charging 6 and discharge 7 converters (information connections of the battery simulator 9 are not shown) . 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 battery simulator 9 has an additional connection to the industrial network through the guaranteed power supply system 10 (for power supply via the discharge interface) and cable 9-2. This principle of power supply to the simulators 8 and 9 was chosen in order to exclude the operation of the charging converter 6 to the battery simulator 9 in the event of power failure in the industrial network, since the battery simulator 9 works (in charge mode) with energy recovery in the industrial network and in the absence of The power supply in the latter will be inoperative.

The spacecraft is tested for mechanical loads and the docking of the solar 1 and 5 batteries is controlled with standard solar 1 and 5 batteries, and the batteries 5 are charged with a mode equivalent to the regular prelaunch mode before being tested for mechanical loads. The latter is due to the need to bring the batteries into a state corresponding to the spacecraft orbital launch site, where the mechanical loads are greatest. All other spacecraft tests are carried out using technological functional 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 the solar 1 and 5 rechargeable batteries with respect to the interface with a stabilized voltage converter, which is almost always impossible to implement during the development of 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. In this case, it is advisable to store the batteries 5 outside the spacecraft at a low comfortable storage temperature, and temporarily install, if necessary, their weight and weight simulators on the spacecraft. This allows you to reduce the negative impact of the storage process on the resource characteristics of the batteries.

Thus, the inventive method of manufacturing a spacecraft increases the functionality and reliability of the electrical testing process, and also allows you to save the resource characteristics of onboard batteries in the manufacturing process of the spacecraft.

Claims (2)

1. A method of manufacturing a spacecraft, including the manufacture of components, assembling a spacecraft including a power supply system having solar panels, rechargeable batteries and a stabilized voltage converter for coordinating the operation of solar and rechargeable batteries and providing stable voltage to a given nominal value of service system modules and payload, preparing sources of electricity for work, conducting electrical tests of the spacecraft for the function testing of mechanical loads, thermal vacuum tests, as well as final tests, including control of the docking of solar and rechargeable batteries, characterized in that the tests of mechanical stress and control of the docking of solar and rechargeable batteries are carried out with standard rechargeable and solar batteries, moreover, rechargeable batteries before testing for mechanical loads are charged with a mode equivalent to the standard prelaunch, and all other tests are carried out using technological functional simulators of solar and rechargeable batteries, and simulators of solar batteries are connected directly to the industrial network, and battery simulators are connected to the industrial network: by the charging interface - directly, and by the discharge interface - through the guaranteed power supply system, at this regular batteries are stored electrically isolated from a stabilized voltage converter, recharged condition. 2. A method of manufacturing a spacecraft according to claim 1, characterized in that prior to monitoring the docking of the batteries, they are stored outside the spacecraft at the optimum storage temperature, and dimensional and weight simulators are temporarily installed on the spacecraft if necessary.