On-orbit voltage stabilization source supporting manned spacecraft maintenance power-on

Abstract

The invention discloses an on-orbit voltage stabilization source supporting manned spacecraft maintenance power-on, which comprises a power supply system, a discharge switch K1, an on-orbit voltage stabilization source module, a maintenance power supply switch K2 coil, a power supply bus A and a power supply bus B. The power supply system is converged into the power supply bus B through the discharge switch K1 and provides energy for remote control and telemetering loads and other loads on a spacecraft; the power supply bus A is connected with the on-orbit voltage stabilization source module; the on-orbit voltage stabilization source module is connected with a maintenance power supply switch K2 coil, and the maintenance power supply switch K2 coil is connected with the power supply bus B. According to the on-orbit voltage stabilization source for maintenance power-on of the manned spacecraft, after on-orbit power-off maintenance of the power supply system is carried out, power supply of the power supply system is restored through on-orbit operation of an astronaut, the electrical safety of on-orbit maintenance operation of the power supply system of the spacecraft is guaranteed, an on-orbit maintenance scheme of the power supply system on the manned spacecraft is feasible, and the maintenance efficiency of the power supply system on the manned spacecraft is improved. Therefore, the purpose of prolonging the on-orbit service life of the manned spacecraft is achieved.

Description

Technical Field

[0001] The invention relates to the field of on-orbit maintenance of a power supply system of a manned spacecraft in a low-orbit space, and in particular to a voltage stabilizing source for supporting on-orbit maintenance of a manned spacecraft. Background Art

[0002] The design life of my country's space station is 15 years, and its service life can be extended through on-orbit maintenance. As the energy supply of spacecraft, the power supply system is one of the key systems to ensure the high reliability and long life of spacecraft, and it is also one of the systems with higher failure frequency in spacecraft. According to statistics, the proportion of power supply system failures accounts for 24% of the entire spacecraft system. In order to meet the needs of extending the life of my country's space station, it is necessary to carry out on-orbit maintenance of the power supply system. my country's space station uses a 100V high-voltage bus. In order to ensure the safety of astronauts when the power supply system products are repaired on-orbit, the power supply must be disconnected before maintenance. After the maintenance is completed, the power supply system faces the problem of re-powering on the orbit. Summary of the invention

[0003] In order to solve the above problems, the present invention provides an on-orbit voltage stabilizing source for supporting the maintenance and power-up of a manned spacecraft. The specific technical solution is as follows:

[0004] An on-orbit voltage-stabilizing source supporting power-on for maintenance of a manned spacecraft comprises a power supply system, a discharge switch K1, an on-orbit voltage-stabilizing source module, a maintenance power supply switch K2 coil, a power supply bus A, and a power supply bus B, wherein:

[0005] The power supply system is connected to the power supply bus B through the discharge switch K1 to provide energy for the remote control and telemetry loads and other loads on the spacecraft;

[0006] The power supply bus A is connected to the on-track voltage-stabilizing source module; the on-track voltage-stabilizing source module is connected to the maintenance power supply switch K2 coil; the maintenance power supply switch K2 coil is connected to the power supply bus B;

[0007] The on-track voltage-stabilizing source module includes a 100V power conversion circuit module, a 28VDC / DC circuit module, a main switch S1, and a 100V maintenance bus output switch S4;

[0008] One end of the main switch S1 is connected to the power supply bus A, and the other end is connected to the 100V power conversion circuit module and the 28VDC / DC circuit module;

[0009] The 100V power conversion circuit module includes a 100V maintenance bus and a 100V maintenance bus return line;

[0010] The 100V maintenance bus is connected to the power supply bus B through the 100V maintenance bus output switch S4 and the power supply switch K2 in sequence;

[0011] The 28VDC / DC circuit module includes a 28V command bus and a 28V command bus return line;

[0012] The maintenance power switch K2 wiring package includes switch S2, switch S3, and power switch K2;

[0013] The 28V command bus return line is connected to the maintenance power switch K2 coil through switches S2 and S3 respectively, and is used to connect and disconnect the power switch K2;

[0014] The discharge switch K1 adopts a relay. When the power supply bus B is normal, the discharge switch K1 is in the on state;

[0015] The on and off of the discharge switch K1 is controlled by the 28V command bus output by the 28VDC / DC circuit module; when the power supply bus B is powered off for maintenance, a command is sent through the ground data management system to disconnect the power supply system discharge switch K1 to ensure that the power supply bus B has no power output during maintenance operations;

[0016] The power switch K2 adopts a relay, which uses the action of an electromagnet to control the closing or opening of another circuit. When the power supply bus B is working normally, the power switch K2 is in the open state;

[0017] The power supply of the power supply switch K2 is provided by the 28V command bus in the on-rail voltage stabilization source module;

[0018] The switches S2 and S3 are both self-recovering switches;

[0019] The main switch S1 and the 100V maintenance bus output switch S4 are both lighted push button switches;

[0020] Furthermore, the power supply system adopts a lithium-ion battery.

[0021] Furthermore, the power supply system passes through the PDU discharge regulator and then flows into the power supply bus B through the discharge switch K1.

[0022] The present invention also provides a method for using the on-orbit voltage stabilizing source for powering up the manned spacecraft for maintenance, which is specifically as follows:

[0023] Step 1: After maintenance, when the power supply bus B is powered on again, the on-orbit voltage-stabilizing source module is connected; the on-orbit astronaut manually presses the main switch S1, and when the indicator light of the main switch S1 lights up, the power supply bus A supplies power to the on-orbit voltage-stabilizing source module normally;

[0024] Step 2: After the indicator light of the main switch S1 lights up, press switch S4. When the indicator light on switch S4 lights up, the 100V maintenance bus output is normal;

[0025] Step 3: After the 100V maintenance bus output in step 2 is normal, the on-orbit astronaut manually presses the switch in step 2 to turn on the power switch K2, completing the on-orbit power supply bus B;

[0026] Step 4. After the on-orbit power-on is normal, send a command through the ground data management system to turn on the power supply system discharge switch K1. After confirming that the power supply of the power supply system is normal, the on-orbit astronaut manually presses the switch S3 to disconnect the power supply switch K2, thereby disconnecting the 100V maintenance bus power supply in the on-orbit voltage-stabilizing source module. At this time, the power supply bus B is powered by the power supply system, and the operation of powering on the power supply bus B after the maintenance is completed;

[0027] Step 5: After the ground confirms that the power supply system is normal, the astronaut on orbit manually presses switch S4. After determining that the 100V maintenance bus is disconnected through the indicator light on S4, he presses the main switch S1 to turn off the on-orbit voltage stabilization source.

[0028] Compared with the prior art, the present invention has the following beneficial effects:

[0029] After the power system is powered off for maintenance on orbit, the astronauts can restore power to the system through on-orbit operations. This ensures the electrical safety of the power system maintenance operations on the spacecraft on orbit, makes the on-orbit maintenance plan of the power system on manned spacecraft feasible, and thus achieves the purpose of extending the on-orbit service life of manned spacecraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] In order to more clearly illustrate the technical solutions disclosed in the present invention, the following briefly introduces the drawings required to be used in some embodiments disclosed in the present invention. Obviously, the drawings described below are only drawings of some embodiments disclosed in the present invention. For ordinary technicians in this field, other drawings can also be obtained based on these drawings. In addition, the drawings described below can be regarded as schematic diagrams, and are not limitations on the actual size of the products involved in the embodiments disclosed in the present invention, the actual process of the method, etc.

[0031] Figure 1 This is a schematic diagram of the working principle of the on-orbit maintenance and power-on of the power supply busbar of a manned spacecraft according to the present invention.

[0032] Figure 2 This is the power supply principle diagram of the K2 coil package of the maintenance power supply switch of the present invention.

[0033] The reference numerals are: K1, discharge switch; K2, power supply switch; S1, main switch; S2, switch; S3, switch; S4, switch. DETAILED DESCRIPTION

[0034] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0035] Figure 1 The figure shows an on-orbit voltage stabilizing source for powering up a manned spacecraft during maintenance of the present invention. The on-orbit voltage stabilizing source for powering up a manned spacecraft during maintenance of the present invention comprises a power supply system, a discharge switch K1, an on-orbit voltage stabilizing source module, a maintenance power supply switch K2 coil, a power supply bus A, and a power supply bus B, wherein:

[0036] The power supply system is connected to the power supply bus B through the discharge switch K1 to provide energy for the remote control and telemetry loads and other loads on the spacecraft;

[0037] The power supply bus A is connected to the on-track voltage-stabilizing source module; the on-track voltage-stabilizing source module is connected to the maintenance power supply switch K2 coil; the maintenance power supply switch K2 coil is connected to the power supply bus B;

[0038] The on-track voltage-stabilizing source module includes a 100V power conversion circuit module, a 28VDC / DC circuit module, a main switch S1, and a 100V maintenance bus output switch S4;

[0039] One end of the main switch S1 is connected to the power supply bus A, and the other end is connected to the 100V power conversion circuit module and the 28VDC / DC circuit module;

[0040] The 100V power conversion circuit module includes a 100V maintenance bus and a 100V maintenance bus return line;

[0041] The 100V maintenance bus is connected to the power supply bus B through the 100V maintenance bus output switch S4 and the power supply switch K2 in sequence;

[0042] The 28VDC / DC circuit module includes a 28V command bus and a 28V command bus return line;

[0043] The maintenance power switch K2 package includes switch S2, switch S3, power switch K2, such as Figure 2 As shown;

[0044] The 28V command bus return line is connected to the maintenance power switch K2 coil through switches S2 and S3 respectively, and is used to connect and disconnect the power switch K2;

[0045] The discharge switch K1 adopts a relay. When the power supply bus B is normal, the discharge switch K1 is in the on state;

[0046] The on and off of the discharge switch K1 is controlled by the 28V command bus output by the 28VDC / DC circuit module; when the power supply bus B is powered off for maintenance, a command is sent through the ground data management system to disconnect the power supply system discharge switch K1 to ensure that the power supply bus B has no power output during maintenance operations;

[0047] The power switch K2 adopts a relay, which uses the action of an electromagnet to control the closing or opening of another circuit. When the power supply bus B is working normally, the power switch K2 is in the open state;

[0048] The power supply of the power supply switch K2 is provided by the 28V command bus in the on-rail voltage stabilization source module;

[0049] The switches S2 and S3 are both self-recovering switches;

[0050] The main switch S1 and the 100V maintenance bus output switch S4 are both lighted push button switches;

[0051] Furthermore, the power supply system adopts a lithium-ion battery.

[0052] Furthermore, the power supply system passes through the PDU discharge regulator and then flows into the power supply bus B through the discharge switch K1.

[0053] The present invention provides a method for using the on-orbit voltage stabilizing source for powering up a manned spacecraft for maintenance, which is specifically as follows:

[0054] Step 1: After maintenance, when the power supply bus B is powered on again, the on-orbit voltage-stabilizing source module is connected; the on-orbit astronaut manually presses the main switch S1, and when the indicator light of the main switch S1 lights up, the power supply bus A supplies power to the on-orbit voltage-stabilizing source module normally;

[0055] Step 2: After the indicator light of the main switch S1 lights up, press switch S4. When the indicator light on switch S4 lights up, the 100V maintenance bus output is normal;

[0056] Step 3: After the 100V maintenance bus output in step 2 is normal, the on-orbit astronaut manually presses the switch in step 2 to turn on the power switch K2, completing the on-orbit power supply bus B;

[0057] Step 4. After the on-orbit power-on is normal, send a command through the ground data management system to turn on the power supply system discharge switch K1. After confirming that the power supply of the power supply system is normal, the on-orbit astronaut manually presses the switch S3 to disconnect the power supply switch K2, thereby disconnecting the 100V maintenance bus power supply in the on-orbit voltage-stabilizing source module. At this time, the power supply bus B is powered by the power supply system, and the operation of powering on the power supply bus B after the maintenance is completed;

[0058] Step 5: After the ground confirms that the power supply system is normal, the astronaut on orbit manually presses switch S4. After determining that the 100V maintenance bus is disconnected through the indicator light on S4, he presses the main switch S1 to turn off the on-orbit voltage stabilization source.

[0059] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention using the above disclosed contents without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the contents of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. An on-orbit voltage-stabilizing source supporting power-on for maintenance of manned spacecraft, comprising a power supply system, a discharge switch K1, an on-orbit voltage-stabilizing source module, a maintenance power supply switch K2 coil, a power supply bus A, and a power supply bus B, wherein: The power supply system is connected to the power supply bus B through the discharge switch K1 to provide energy for the remote control and telemetry loads and other loads on the spacecraft; The power supply bus A is connected to the on-track voltage-stabilizing source module; the on-track voltage-stabilizing source module is connected to the maintenance power supply switch K2 coil; the maintenance power supply switch K2 coil is connected to the power supply bus B; The on-track voltage-stabilizing source module includes a 100V power conversion circuit module, a 28VDC / DC circuit module, a main switch S1, and a 100V maintenance bus output switch S4; One end of the main switch S1 is connected to the power supply bus A, and the other end is connected to the 100V power conversion circuit module and the 28VDC / DC circuit module; The 100V power conversion circuit module includes a 100V maintenance bus and a 100V maintenance bus return line; The 100V maintenance bus is connected to the power supply bus B through the 100V maintenance bus output switch S4 and the power supply switch K2 in sequence; The 28VDC / DC circuit module includes a 28V command bus and a 28V command bus return line; The maintenance power switch K2 wiring package includes switch S2, switch S3, and power switch K2; The 28V command bus return line is connected to the maintenance power switch K2 coil through switches S2 and S3 respectively, and is used to connect and disconnect the power switch K2.

2. The on-orbit voltage stabilizing source for supporting power-on during maintenance of a manned spacecraft according to claim 1, characterized in that: The discharge switch K1 adopts a relay. When the power supply bus B is normal, the discharge switch K1 is in the on state; The connection and disconnection of the discharge switch K1 are controlled by the 28V command bus output by the 28VDC / DC circuit module; when the power supply bus B is powered off for maintenance, an instruction is sent through the ground data management system to disconnect the power supply system discharge switch K1 to ensure that the power supply bus B has no power output during maintenance operations.

3. The on-orbit voltage stabilizing source for supporting power-up of manned spacecraft maintenance according to claim 1, characterized in that: The power switch K2 adopts a relay, which uses the action of an electromagnet to control the closing or opening of another circuit. When the power supply bus B is working normally, the power switch K2 is in the open state; The power supply of the power supply switch K2 is provided by the 28V command bus in the on-rail voltage-stabilizing source module.

4. The on-orbit voltage stabilizing source for supporting power-up of manned spacecraft maintenance according to claim 1, characterized in that: The switches S2 and S3 are both self-resetting switches.

5. The on-orbit voltage stabilizing source for supporting power-on during maintenance of a manned spacecraft according to claim 1, characterized in that: The main switch S1 and the 100V maintenance bus output switch S4 are both lighted push button switches.

6. The on-orbit voltage stabilizing source for supporting power-up of manned spacecraft maintenance according to claim 1, characterized in that: The power supply system adopts lithium ion battery.

7. The on-orbit voltage stabilizing source for supporting power-up of manned spacecraft maintenance according to claim 1, characterized in that: The power supply system passes through the PDU discharge regulator and then flows into the power supply bus B through the discharge switch K1.

8. An on-orbit voltage stabilizing source for supporting power-up of manned spacecraft maintenance according to any one of claims 1 to 7, characterized in that: The method for using the on-orbit voltage stabilizing source for powering up the manned spacecraft for maintenance is as follows: Step 1: After maintenance, when the power supply bus B is powered on again, the on-orbit voltage-stabilizing source module is connected; the on-orbit astronaut manually presses the main switch S1, and when the indicator light of the main switch S1 lights up, the power supply bus A supplies power to the on-orbit voltage-stabilizing source module normally; Step 2: After the indicator light of the main switch S1 lights up, press switch S4. When the indicator light on switch S4 lights up, the 100V maintenance bus output is normal; Step 3: After the 100V maintenance bus output in step 2 is normal, the on-orbit astronaut manually presses the switch in step 2 to turn on the power switch K2, completing the on-orbit power supply bus B; Step 4. After the on-orbit power-on is normal, send a command through the ground data management system to turn on the power supply system discharge switch K1. After confirming that the power supply of the power supply system is normal, the on-orbit astronaut manually presses the switch S3 to disconnect the power supply switch K2, thereby disconnecting the 100V maintenance bus power supply in the on-orbit voltage-stabilizing source module. At this time, the power supply bus B is powered by the power supply system, and the operation of powering on the power supply bus B after the maintenance is completed; Step 5: After the ground confirms that the power supply system is normal, the astronaut on orbit manually presses switch S4. After determining that the 100V maintenance bus is disconnected through the indicator light on S4, he presses the main switch S1 to turn off the on-orbit voltage stabilization source.

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