CN112953381B - Ground test method for solar cell array driving device - Google Patents
Ground test method for solar cell array driving device Download PDFInfo
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Abstract
The invention provides a ground test method for a solar cell array driving device, which comprises the following steps: connecting the ground test equipment to the ground switching module so as to provide the test signal to the ground switching module; the test signals comprise a computer ground test signal, a power supply ground test signal and a power test signal; the ground switching module is connected to the power supply controller, the satellite borne computer and the solar cell array driving device through cables, so that a computer ground test signal is provided to the satellite borne computer, a power supply ground test signal is provided to the power supply controller, and a power test signal is provided to the power supply controller and the solar cell array driving device; connecting the solar cell array driving device to a power supply controller through a cable so as to provide a power test signal to the power supply controller; enabling the power supply controller to receive a power supply ground test signal and a power test signal for testing; and enabling the spaceborne computer to carry out communication between the computer ground test port and the solar cell array driving device so as to carry out testing.
Description
Technical Field
The invention relates to the technical field of satellite ground test, in particular to a ground test method for a solar cell array driving device.
Background
The solar array driving device (SADA) is composed of a Solar Array Driving Mechanism (SADM) and a solar array driving circuit (SADE), and is a regulator of a transmission channel and a posture of energy and signals. The satellite adopts SADA to realize the stability of solar cell sailboards to the sun, so that the energy can meet the design requirement of the satellite. The SADM completes the power transmission function through a power transmission module, namely a power ring structure, and realizes the electric signal transmission of the rotating part and the fixed structure through the matching of the two parts of the ring brush.
As shown in fig. 1, the satellite SADA function is implemented in relation to the solar cell array, the power controller, and the on-board computer, including energy transmission and communication control. The + Y/-Y solar cell array is an energy source of the satellite, the generated electric energy is transmitted to the power supply controller through the SDAM power loop, and the power supply controller is responsible for the conversion and control of the satellite on-orbit power supply and is responsible for energy management; the satellite-borne computer is responsible for completing whole-satellite communication transmission; the functional connection among all the equipment of the whole satellite is completed through cables. The solar cell array power transmission is realized through a low-frequency cable, the path 1 is from the + Y solar cell array to the SADM-A connector J05, and through a power ring to the SADM-A connector J07 to the power supply controller connector X14; path 2 is-Y solar array to SADM-B connector J05, through power ring to SADM-B connector J07 to power supply controller connector X15. Communication control is realized through a 1553B bus, and the path is from SADE to the on-board computer.
The conventional satellite ground test method is shown in fig. 2. The ground test equipment 101 comprises a ground simulation square matrix 102 (for simulating the power output of the solar cell array) and a ground test system 103 (for simulating the communication interaction). The ground test equipment realizes whole-satellite energy and communication transmission by taking a cable as a medium through ground falling plugs YF5-127T and YF 5-127Z: connecting the ground analog square 102 to connector X16/X17(± Y square analog input) of the satellite power controller 104; completing communication with the computer and the power ground port 105. However, the conventional satellite ground test method has the following defects: the on-orbit SADA power supply circuit cannot be simulated and examined, and the function and the performance of the SADA cannot be tested and verified effectively, fully and for a long time in the whole satellite ground test process.
Disclosure of Invention
The invention aims to provide a ground test method for a solar cell array driving device, which aims to solve the problem that the existing ground test method cannot simulate and examine the on-orbit SADA performance.
In order to solve the above technical problem, the present invention provides a ground testing method for a solar cell array driving apparatus, comprising:
connecting the ground test equipment to the ground switching module so as to provide the test signal to the ground switching module;
the test signals comprise a computer ground test signal, a power supply ground test signal and a power test signal;
the ground switching module is connected to the power supply controller, the satellite borne computer and the solar cell array driving device through cables, so that a computer ground test signal is provided to the satellite borne computer, a power supply ground test signal is provided to the power supply controller, and a power test signal is provided to the power supply controller and the solar cell array driving device;
connecting the solar cell array driving device to a power supply controller through a cable so as to provide a power test signal to the power supply controller;
enabling the power supply controller to receive a power supply ground test signal and a power test signal for testing; and
and enabling the spaceborne computer to carry out communication between the computer ground test port and the solar cell array driving device so as to carry out testing.
Optionally, in the ground test method for the solar cell array driving apparatus, the ground test device includes a ground simulation matrix and a ground test system, the ground simulation matrix is used for simulating power output of the solar cell array, and the ground test system is used for performing communication interaction test with the satellite-borne computer and the power supply controller.
Optionally, in the ground test method for the solar cell array driving apparatus, the ground adapter module includes a first ground drop adapter, a second ground drop adapter, a ground drop plug, and a plurality of adapter plugs;
the first ground shedding adapter is connected to ground testing equipment;
the adapter plug, the second ground-dropping adapter and the ground-dropping plug are sequentially connected between the first ground-dropping adapter and the power controller;
and the rest of the adapter plugs are also connected between the first ground shedding adapter and the solar cell array driving device.
Optionally, in the ground test method for the solar cell array driving apparatus, the cable includes a fifth cable and a sixth cable, where:
the fifth cable is connected between the first ground drop adapter and the adapter plug;
the sixth cable is connected between the patch plug connected to the first ground drop adapter and the second ground drop adapter;
the ground drop plug is connected with a +/-Y square matrix analog interface of the power supply controller, a computer and a ground power supply measuring port.
Optionally, in the ground test method for the solar cell array driving apparatus, the solar cell array driving apparatus includes:
the first solar cell array driving mechanism is directly connected to the first adapter plug and is connected to the + Y solar cell array interface through the first power adapter;
the first adapter plug is also connected to the + Y solar cell array interface through the first power adapter;
the second solar cell array driving mechanism is directly connected to the second adapter plug and is connected to the-Y solar cell array interface through a second power adapter;
the second adapter plug is also connected to the-Y solar cell array interface through a second power adapter.
Optionally, in the ground test method for a solar cell array driving device, the cable further includes a first cable and a second cable, wherein:
the first cable main line is connected between the first adapter plug and the first power adapter through the cabin penetrating hole;
the first cable negative line is led out from the first adapter plug, is connected with a controller side interface of the first solar cell array driving mechanism through a cabin penetrating hole, is led out from the controller side interface of the first solar cell array driving mechanism, and is connected to the first power adapter after passing through the cabin penetrating hole twice;
and the second cable is used for short-circuiting the battery array side interface of the first solar battery array driving mechanism.
Optionally, in the ground test method for a solar cell array driving device, the cable further includes a third cable and a fourth cable, where:
the third cable positive line is connected between the second adapter plug and the second power adapter through the cabin penetrating hole;
the third cable negative line is led out by a second adapter plug, is connected with a controller side interface of the second solar cell array driving mechanism through a cabin penetrating hole, is led out by a controller side interface of the second solar cell array driving mechanism, and is connected to a second power adapter after passing through the cabin penetrating hole twice;
and the fourth cable is used for short-circuiting a battery array side interface of the second solar battery array driving mechanism.
Optionally, in the ground test method for the solar cell array driving device, the working modes of the solar cell array driving device include stall holding, zero calibration, cruise mode and fast capture;
the cruise mode is that a rotating component of the solar cell array driving mechanism rotates at the speed of 12h/360 degrees; the rapid capture is that the rotating part of the solar cell array driving mechanism rotates at the speed of 20min/360 degrees;
and under the integrated state of the whole satellite, testing the solar cell array driving device, wherein the testing process comprises the following steps:
the ground simulation matrix powers on the whole satellite;
starting a solar cell array driving device;
setting the working mode of the solar cell array driving device according to the test case;
shutting down the solar cell array driving device; and
and the ground simulation matrix is used for powering off the whole satellite.
Optionally, in the ground test method for the solar cell array driving apparatus, the solar cell array driving apparatus further includes a solar cell array driving circuit, where:
monitoring bus voltage, motor working states of a first solar cell array driving mechanism and a second solar cell array driving mechanism, temperature of the first solar cell array driving mechanism, temperature of the second solar cell array driving mechanism and temperature of a solar cell array driving circuit under different working modes of the solar cell array driving device;
the test results include: whether the bus voltage is normal or not, whether the power output is normal or not, whether the power slip ring output of the first solar cell array driving mechanism and the second solar cell array driving mechanism is normal or not and whether the solar cell array driving circuit controls the rotation to be normal or not.
In the ground test method of the solar cell array driving device provided by the invention, the ground switching module is connected to the solar cell array driving device through a cable, the solar cell array driving device is connected to the power supply controller through the cable so as to provide a power test signal to the power supply controller, the power ring transmission test of the solar cell array driving device is completed according to the power output of the power supply controller, and meanwhile, the ground switching module is connected to the power supply controller and the satellite-borne computer through the cable so as to respectively provide a computer ground test signal and a power ground test signal in the test signal to the satellite-borne computer and the power supply controller, so that the ground test equipment completes SADA test control. The method makes up the defect that the performance of the SADA cannot be effectively, sufficiently and tested and verified for a long time in the whole satellite ground test process in the traditional satellite ground test scheme, and realizes comprehensive simulation and assessment of the satellite in-orbit power supply path.
In addition, due to the fact that the ground drop adapters, the ground drop plugs, the transfer connectors and other devices capable of being flexibly transferred are arranged, the test scheme can be flexibly selected according to actual test requirements.
The battery array side interface of the first solar battery array driving mechanism is directly connected with the SADM-A rotating part of the first solar battery array driving mechanism, and the second solar battery array driving mechanism is in the same manner, so that in the whole star state, the battery array side rotating part of the first solar battery array driving mechanism drives the solar battery array to rotate, but the process cannot be realized during ground test, the action cannot be simulated, and the rotation test cannot be carried out; in the invention, the battery array side interface of the first solar battery array driving mechanism is short-circuited through the second cable, so that the effect of not interfering the action of the SADM-A rotating part of the first solar battery array driving mechanism is realized, and the rotation test can be realized.
In conclusion, the satellite in-orbit power supply path testing device makes up the defects of the traditional satellite ground testing scheme, comprehensively simulates and examines the satellite in-orbit power supply path, and does not interfere with the SADM rotating component; meanwhile, a traditional test scheme access is reserved, and a test scheme can be flexibly selected according to actual test requirements. The invention can realize the SADM power loop power transmission test and the SADA functional performance test in the satellite ground test process, and is suitable for the SADA functional performance examination in the satellite ground test.
Drawings
FIG. 1 is a functional schematic diagram of a conventional satellite SADA;
FIG. 2 is a schematic diagram of a prior art satellite ground test method;
fig. 3 is a schematic diagram of a ground testing method for a solar cell array driving apparatus according to an embodiment of the invention;
fig. 4 is a schematic diagram illustrating the testing result of the operating mode of the solar cell array driving apparatus according to an embodiment of the present invention;
fig. 5 is a schematic diagram illustrating a temperature test result of a solar cell array driving apparatus according to an embodiment of the invention;
fig. 6 is a schematic diagram illustrating a bus voltage test result of a ground test method for a solar cell array driving apparatus according to an embodiment of the present invention;
fig. 7 is a schematic view illustrating a load current test result of a ground test method for a solar cell array driving apparatus according to an embodiment of the present invention;
shown in the figure: 1-ground simulation square matrix; 2-a ground test system; 3-a first ground drop adapter; 4-a second floor disconnect adapter; 5-ground falling off the plug; 6-computer and power ground test port; 7-power supply controller.
Detailed Description
The ground testing method for the solar cell array driving device provided by the invention is further described in detail below with reference to the accompanying drawings and specific embodiments. Advantages and features of the present invention will become apparent from the following description and from the claims. It is to be noted that the drawings are in a very simplified form and are not to precise scale, which is merely for the purpose of facilitating and distinctly claiming the embodiments of the present invention.
Furthermore, features from different embodiments of the invention may be combined with each other, unless otherwise indicated. For example, a feature of the second embodiment may be substituted for a corresponding or functionally equivalent or similar feature of the first embodiment, and the resulting embodiments are likewise within the scope of the disclosure or recitation of the present application.
The core idea of the invention is to provide a ground test method for a solar cell array driving device, so as to solve the problem that the existing ground test method cannot simulate and examine the on-orbit SADA performance.
In order to realize the idea, the invention provides a ground test method for a solar cell array driving device, which comprises the following steps: connecting the ground test equipment to the ground switching module so as to provide the test signal to the ground switching module; the test signals comprise a computer ground test signal, a power supply ground test signal and a power test signal; the ground switching module is connected to the power supply controller, the satellite borne computer and the solar cell array driving device through cables, so that a computer ground test signal is provided to the satellite borne computer, a power supply ground test signal is provided to the power supply controller, and a power test signal is provided to the power supply controller and the solar cell array driving device; connecting the solar cell array driving device to a power supply controller through a cable so as to provide a power test signal to the power supply controller; enabling the power supply controller to receive a power supply ground test signal and a power test signal for testing; and enabling the spaceborne computer to carry out communication between the computer ground test port and the solar cell array driving device so as to carry out testing.
The present embodiment provides a ground test circuit for a solar cell array driving apparatus, as shown in fig. 3, including: ground test equipment configured to connect to the ground relay module for providing a test signal to the ground relay module; the test signals comprise a computer ground test signal, a power supply ground test signal and a power test signal; the ground switching module is connected to the satellite-borne computer, the power controller 7 and the solar cell array driving device through cables, so that a computer ground test signal is provided to the satellite-borne computer, a power ground test signal is provided to the power controller, and a power test signal is provided to the power controller and the solar cell array driving device; a solar cell array driving apparatus configured to be connected to the power supply controller 7 through a cable for supplying a power test signal to the power supply controller 7; a power controller 7 configured to receive a power ground test signal and a power test signal for testing; and the on-board computer is configured to communicate with the computer ground test port and the solar cell array driving device so as to perform testing.
In the embodiment of the ground test method of the solar cell array driving device, the ground test equipment comprises a ground simulation square array 1 and a ground test system 2, wherein the ground simulation square array 1 is used for simulating the power output of a solar cell array, and the ground test system 2 is used for carrying out communication interaction test with a satellite-borne computer and a power supply controller.
In one embodiment of the ground test method for a solar array driving apparatus of the present invention, the ground adaptor module comprises a first ground release adaptor 3, a second ground release adaptor 4, a ground release plug 5 and a plurality of adaptor plugs (ZJ-X01, ZJ-J01, ZJ-J02); the first ground shedding adapter 3 is connected to ground testing equipment; the adapter plug ZJ-X01, the second ground release adapter 4 and the ground release plug 5 are sequentially connected between the first ground release adapter 3 and the power controller 7; the adapter plugs ZJ-J01 and ZJ-J02 are connected between the first ground-shedding adapter 3 and the solar cell array driving device.
In an embodiment of the ground test method for a solar array driving apparatus of the present invention, the cables include a fifth cable W05 and a sixth cable W06, wherein: the fifth cable W05 is connected between the first ground disconnect adapter 3 and a patch plug ZJ-X01; the sixth cable W06 is connected between the patch plug ZJ-X01 and the second ground drop adapter 4; the ground drop plug 5 is connected with a +/-Y square matrix analog interface (+ Y square matrix analog X16 and-Y square matrix analog X17) of the power controller 7 and a computer and power ground test port 6.
In an embodiment of the ground testing method for a solar array driving apparatus of the present invention, the solar array driving apparatus includes: the first solar cell array driving mechanism SADM-A is directly connected to the first adapter plug ZJ-J01 and is connected to the + Y solar cell array interface X14 through a first power adapter SADM-A-J07-ZJ; the first adapter plug ZJ-J01 is also connected to the + Y solar array interface X14 through the first power adapter SADM-a-J07-ZJ; the second solar cell array driving mechanism SADM-B is directly connected to the second adapter plug ZJ-J02 and is connected to the-Y solar cell array interface X15 through a second power adapter SADM-B-J07-ZJ; the second patch plug ZJ-J02 is also connected to the-Y solar array interface X15 through a second power adapter SADM-B-J07-ZJ.
In an embodiment of the ground testing method for the solar array driving apparatus of the present invention, the cable further includes a first cable W01 and a second cable W02, wherein: the first cable W01 positive line is connected between the first adapter plug ZJ-J01 and the first power adapter SADM-A-J07-ZJ through a cabin penetrating hole; the negative line of the first cable W01 is led out from a first adapter plug ZJ-J01, is connected with a controller side interface SADM-A-J07 of a first solar cell array driving mechanism SADM-A through a cabin penetrating hole, is led out from a controller side interface SADM-A-J07, and is connected to a first power adapter SADM-A-J07-ZJ after passing through the cabin penetrating hole twice; the second cable W02 short-circuits the cell array side interface SADM-a-J05 of the first solar cell array driving mechanism SADM-a.
In an embodiment of the ground testing method for the solar array driving apparatus of the present invention, the cable further includes a third cable W03 and a fourth cable W04, wherein: the third cable W03 is connected between the second patch plug ZJ-J02 and the second power adapter SADM-B-J07-ZJ through the cabin penetration hole; the negative line of the third cable W03 is led out from a second adapter plug ZJ-J02, is connected with a controller side interface SADM-B-J07 of a second solar cell array driving mechanism SADM-B through a cabin penetrating hole, is led out from a controller side interface SADM-B-J07, and is connected to a second power adapter SADM-B-J07-ZJ after passing through the cabin penetrating hole twice; the fourth cable W04 short-circuits the battery array side interface SADM-B-J05 of the second solar battery array driving mechanism SADM-B.
In the embodiment of the ground test method of the solar cell array driving device, the working modes of the solar cell array driving device comprise stall maintenance, zero calibration, a cruise mode and quick capture; the cruise mode is that a rotating part of the solar cell array driving mechanism rotates around a central shaft of the rotating part at the speed of 12h/360 degrees; the rapid capture is that the rotating part of the solar cell array driving mechanism rotates around the self central shaft at the speed of 20min/360 degrees; and under the integrated state of the whole satellite, testing the solar cell array driving device, wherein the testing process comprises the following steps: the ground simulation matrix powers on the whole satellite; starting a solar cell array driving device; setting the working mode of the solar cell array driving device according to the test case; shutting down the solar cell array driving device; and the ground simulation matrix refunds the power of the whole satellite.
In an embodiment of the ground testing method for a solar array driving apparatus of the present invention, the solar array driving apparatus further includes a solar array driving line SADE (not shown in fig. 3), wherein: monitoring bus voltage, motor working states of a first solar cell array driving mechanism SADM-A and a second solar cell array driving mechanism SADM-B, temperature of the first solar cell array driving mechanism, temperature of the second solar cell array driving mechanism and temperature of a solar cell array driving circuit in different working modes of the solar cell array driving device; the test results include: whether the bus voltage is normal or not, whether the power output is normal or not, whether the power slip ring output of the first solar cell array driving mechanism and the second solar cell array driving mechanism is normal or not, and whether the SADE control rotation of the solar cell array driving circuit is normal or not.
The invention relates to a special ground test cable for SADA (satellite-associated data acquisition) capable of simulating an on-orbit power supply path of a satellite, which is applied to a satellite ground test and aims to realize the purpose through the following technical scheme: the ground test cable special for the SADA consists of 6 cables named as W01-W06, the principle of the ground test cable is shown in figure 3, the ground test cable comprises a power positive line path, a power negative line path and a signal path, and the connector is the connector included in the invention. The input/output of the adapter 3 is disconnected from the first ground positively/negatively (W05-W01/W03), the SADM power loop is connected into a power loop by short-circuiting the SADM-A of the first solar cell array driving mechanism and the SADM-B power loop (W02/W04) of the second solar cell array driving mechanism through cables, so that the power negatively flows through all the SADM power loops, and the simulation that the actual power supply path is transmitted to power controllers X14 and X15 through the SDAM power loop is realized. Signals are input/output from the first ground drop adapter 3 to the second ground drop adapter 4, the ground drop plug 5 (W05-W06). The design can simulate an actual power supply path without interfering an SADM rotating part, and can realize SADM power loop power transmission test and SADA functional performance test in the satellite ground test process.
The W01 cable is used for realizing the connection of the ground test equipment, SADM-A and the power supply path of the power supply controller 7. The positive line channel is directly connected to SADM-A-J07-ZJ by a patch plug with the serial number ZJ-J01, so that the connection with a power supply controller X14 is realized; the negative line path is connected to SADM-A-J07 through ZJ-J01, and nodes defined by the same negative line are led out from other power ring nodes corresponding to SADM-A-J07 to SADM-A-J07-ZJ and further connected with a power supply controller X14. In design, the definitions of nodes corresponding to the two negative lines are completely consistent, and the physical meanings of the nodes are ground analog square matrix transmission power return lines. The adapter plug ZJ-J01 is led out from the cabin through hole of the satellite cabin plate.
The W02 cable functions to form the negative line path for power transfer through the power slip ring. Since the SADM-A-J05 and SADM-A-J07 are in point-to-point conduction relationship in SADM-A, in order to enable a negative line in W01 to form a channel, a node defined by the same negative line in SADM-A-J07, namely SADM-A-J05, is designed to be shorted.
The design principles of W03 and W04 are respectively the same as those of W01 and W02, and the adapter plug ZJ-J02 is led out from a cabin penetrating hole of the satellite cabin plate corresponding to SADM-B equipment.
The W05 cable is used for transmitting the power of the ground simulation square matrix 1, and the communication between the ground test equipment and the satellite is realized. A plug at one end of the first ground shedding adapter 3 is connected with ground testing equipment; the other end is respectively connected with three patch plugs, including a first patch plug ZJ-J01 and a second patch plug ZJ-J02 for transmitting power and a patch plug ZJ-X01 for transmitting ground test commands and telemetering.
The W06 cable is used for connecting the command and telemetry line led out by the adapter plug ZJ-X01 with the satellite ground drop plug 5 through the second ground drop adapter 4 to form an information transmission channel.
The satellite SADA working mode comprises four modes of stall keeping, zero calibration, cruise mode and quick capture. Wherein, the cruising mode is 0.0084 degree/s, namely the slow rotating mode of MEO orbit 12h rotating 1 circle; the fast capture is 0.3 degrees/s, i.e. 20min 1 turn fast spin mode.
TABLE 1SADA Special test procedure
And (5) carrying out SADA test in the whole satellite integrated state, wherein the test flow is shown in table 1. And under different SADA working modes, monitoring the bus voltage, the working state of the SADM-A/B motor and the SADM/SADE temperature. The test targets were: the bus voltage is normal, and the power output is normal; the output of the SADM power slip ring is normal, and the SADE control rotation is normal.
The SADA test cases and results are shown in Table 2, the working modes are shown in FIG. 4, and the remote measurement analysis of the SADM-A/B motor working modes comprises 0-stall holding, 2-cruise mode, 3-fast capture and 5-zero calibration. In the test process, the change curves of the SADA working mode, the SADA temperature, the bus voltage and the load current are shown in figures 4-7.
The SADA test verifies that when the SADA is in each working mode, the power ring works normally, the power output is normal, and the bus voltage is stabilized at 42.2V +/-0.2V; in the process that the SADM rotates for one circle quickly, the power ring works normally, and the bus voltage is stable; under a certain load, the SADM and SADE temperatures are within the normal range.
The testing method can also be used for SADA testing of satellite ground long-time large-scale tests such as thermal vacuum tests and the like, so that the real power supply access and environment of the satellite in the in-orbit process are fully simulated on the ground, the power supply function performance of the SADM power loop and the control function of the SADE are verified, the ground testing coverage is ensured, and the safety, reliability and stability of the in-orbit power supply of the satellite are ensured.
TABLE 2SADA test cases and results
In summary, the above embodiments describe in detail different configurations of the ground testing method for the solar array driving apparatus, and it is understood that the present invention includes, but is not limited to, the configurations listed in the above embodiments, and any modifications made on the configurations provided in the above embodiments are within the scope of the present invention. One skilled in the art can take the contents of the above embodiments to take a counter-measure.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. For the system disclosed by the embodiment, the description is relatively simple because the system corresponds to the method disclosed by the embodiment, and the relevant points can be referred to the method part for description.
The above description is only for the purpose of describing the preferred embodiments of the present invention, and is not intended to limit the scope of the present invention, and any variations and modifications made by those skilled in the art based on the above disclosure are within the scope of the appended claims.
Claims (8)
1. A ground test method for a solar cell array driving device is characterized by comprising the following steps:
connecting the ground test equipment to the ground switching module so as to provide the test signal to the ground switching module;
the test signals comprise a computer ground test signal, a power supply ground test signal and a power test signal;
the ground switching module is connected to the power supply controller, the satellite borne computer and the solar cell array driving device through cables, so that a computer ground test signal is provided to the satellite borne computer, a power supply ground test signal is provided to the power supply controller, and a power test signal is provided to the power supply controller and the solar cell array driving device;
connecting the solar cell array driving device to a power supply controller through a cable so as to provide a power test signal to the power supply controller;
enabling the power supply controller to receive a power supply ground test signal and a power test signal for testing; and
enabling the spaceborne computer to carry out communication between the computer ground test port and the solar cell array driving device so as to carry out testing;
the ground adapter module comprises a first ground falling adapter, a second ground falling adapter, a ground falling plug and a plurality of adapter plugs;
the first ground shedding adapter is connected to ground testing equipment;
the adapter plug, the second ground-dropping adapter and the ground-dropping plug are sequentially connected between the first ground-dropping adapter and the power controller;
and the rest of the adapter plugs are also connected between the first ground shedding adapter and the solar cell array driving device.
2. The ground test method for the solar cell array driving device as claimed in claim 1, wherein the ground test equipment comprises a ground simulation square array and a ground test system, the ground simulation square array is used for simulating the power output of the solar cell array, and the ground test system is used for carrying out communication interaction test with the on-board computer and the power supply controller.
3. The solar array driving apparatus ground test method of claim 1, wherein the cable includes a fifth cable and a sixth cable, wherein:
the fifth cable is connected between the first ground drop adapter and the adapter plug;
the sixth cable is connected between the patch plug connected to the first ground drop adapter and the second ground drop adapter;
the ground drop plug is connected with a +/-Y square matrix analog interface of the power supply controller, a computer and a ground power supply measuring port.
4. The ground test method for the solar cell array driving apparatus according to claim 1, wherein the solar cell array driving apparatus comprises:
the first solar cell array driving mechanism is directly connected to the first adapter plug and is connected to the + Y solar cell array interface through the first power adapter;
the first adapter plug is also connected to the + Y solar cell array interface through the first power adapter;
the second solar cell array driving mechanism is directly connected to the second adapter plug and is connected to the-Y solar cell array interface through a second power adapter;
the second adapter plug is also connected to the-Y solar cell array interface through a second power adapter.
5. The solar array driving apparatus ground test method of claim 4, wherein the cable further comprises a first cable and a second cable, wherein:
the first cable main line is connected between the first adapter plug and the first power adapter through the cabin penetrating hole;
the first cable negative line is led out from the first adapter plug, is connected with a controller side interface of the first solar cell array driving mechanism through a cabin penetrating hole, is led out from the controller side interface of the first solar cell array driving mechanism, and is connected to the first power adapter after passing through the cabin penetrating hole twice;
and the second cable is used for short-circuiting the battery array side interface of the first solar battery array driving mechanism.
6. The solar array driving apparatus ground test method of claim 4, wherein the cable further comprises a third cable and a fourth cable, wherein:
the third cable positive line is connected between the second adapter plug and the second power adapter through the cabin penetrating hole;
the third cable negative line is led out by a second adapter plug, is connected with a controller side interface of the second solar cell array driving mechanism through a cabin penetrating hole, is led out by a controller side interface of the second solar cell array driving mechanism, and is connected to a second power adapter after passing through the cabin penetrating hole twice;
and the fourth cable is used for short-circuiting a battery array side interface of the second solar battery array driving mechanism.
7. The ground test method for the solar cell array driving device according to claim 4, wherein the working modes of the solar cell array driving device comprise stall holding, zero calibration, cruise mode and fast capture;
the cruise mode is that a rotating component of the solar cell array driving mechanism rotates at the speed of 12h/360 degrees; the rapid capture is that the rotating part of the solar cell array driving mechanism rotates at the speed of 20min/360 degrees;
and under the integrated state of the whole satellite, testing the solar cell array driving device, wherein the testing process comprises the following steps:
the ground simulation matrix powers on the whole satellite;
starting a solar cell array driving device;
setting the working mode of the solar cell array driving device according to the test case;
shutting down the solar cell array driving device; and
and the ground simulation matrix is used for powering off the whole satellite.
8. The ground test method for a solar cell array driving apparatus according to claim 4, wherein the solar cell array driving apparatus further comprises a solar cell array driving circuit, wherein:
monitoring bus voltage, motor working states of a first solar cell array driving mechanism and a second solar cell array driving mechanism, temperature of the first solar cell array driving mechanism, temperature of the second solar cell array driving mechanism and temperature of a solar cell array driving circuit under different working modes of the solar cell array driving device;
the test results include: whether the bus voltage is normal or not, whether the power output is normal or not, whether the power slip ring output of the first solar cell array driving mechanism and the second solar cell array driving mechanism is normal or not and whether the solar cell array driving circuit controls the rotation to be normal or not.
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| CN114157236A (en) | 2022-03-08 |
| CN112953381A (en) | 2021-06-11 |
| CN114157236B (en) | 2024-06-28 |
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