CN109799416B - Spacecraft rendezvous and docking grid-connected short circuit detection circuit - Google Patents
Spacecraft rendezvous and docking grid-connected short circuit detection circuit Download PDFInfo
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- CN109799416B CN109799416B CN201910153180.XA CN201910153180A CN109799416B CN 109799416 B CN109799416 B CN 109799416B CN 201910153180 A CN201910153180 A CN 201910153180A CN 109799416 B CN109799416 B CN 109799416B
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Abstract
The spacecraft rendezvous and docking grid-connected short circuit detection circuit comprises: the device comprises an isolation module, a voltage division module, a protection module and a voltage stabilization module; the protection module, the voltage division module and the isolation module are sequentially connected to serve as a voltage input branch; two ends of the voltage input branch are respectively connected with an external test voltage and a positive cable of a grid-connected power supply path; the voltage division module and the isolation module are sequentially connected to be used as a positive return line isolation branch; two ends of the positive loop line isolation branch are respectively used for connecting a positive cable connected with a grid-connected power supply path and an output end used for outputting hard line telemetering data to the satellite counting platform; the voltage stabilizing module and the isolating module are sequentially connected to be used as a telemetering output branch circuit; two ends of the telemetering output branch are respectively connected with the output end for grounding treatment, and a connection point between the voltage stabilizing module and the isolating module is connected with a negative cable of the grid-connected power supply path. The invention solves the safety detection of the butt joint access of different spacecrafts and ensures the safety of the 100V bus of the source-end spacecraft.
Description
Technical Field
The invention relates to a spacecraft rendezvous and docking grid-connected short circuit detection circuit, which is particularly suitable for a source-end electronic single machine which needs to perform power supply path safety check after docking of different spacecrafts, and belongs to the technical field of power supply and distribution.
Background
In order to make better use of the space environment, large spacecraft need to be built in space. However, because the existing vehicles have limited carrying capacity and cannot launch large-scale spacecrafts at one time, the current common mode is to separate the large-scale spacecrafts into small spacecrafts to launch and lift off in batches, then carry out on-orbit assembly and butt joint in the space, and after the butt joint is finished, power supply is started among different small spacecrafts.
The power supply path between the spacecrafts bears the important role of transmitting electric energy, the power supply path is normally the basic condition for the spacecrafts to finish the on-orbit task, once the power supply path has a short circuit problem, equipment on the corresponding path can be damaged, so that great loss is caused, the launching task of the spacecrafts fails, and the short circuit fault is the fatal threat of a grid-connected power supply system. Therefore, it is proposed to provide a short-circuit detection circuit inside the grid-connected single machine, perform short-circuit check on the power supply path before grid-connected power supply starts, and perform grid-connected power supply operation after determining safety.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the short-circuit detection circuit overcomes the defects of the prior art, provides a spacecraft rendezvous and docking grid-connected short-circuit detection circuit, and carries out short-circuit detection on a power supply passage in order to ensure the safety of a grid-connected power supply single machine after the spacecraft rendezvous and docking is completed.
The technical scheme of the invention is as follows:
spacecraft rendezvous and docking grid-connected short circuit detection circuit comprises: the device comprises an isolation module, a voltage division module, a protection module and a voltage stabilization module;
the protection module, the voltage division module and the isolation module are sequentially connected to serve as a voltage input branch; one end of the voltage input branch is connected with an external test voltage, and the other end of the voltage input branch is connected with a positive cable of a grid-connected power supply path;
the voltage division module and the protection module are sequentially connected to be used as a positive circuit line isolation branch; one end of the positive loop line isolation branch is connected with a positive cable of a grid-connected power supply path, and the other end of the positive loop line isolation branch is used as an output end for outputting hard line telemetering data to the satellite counting platform;
the voltage stabilizing module and the protection module are sequentially connected to serve as a telemetering output branch circuit; one end of the telemetering output branch is connected with an output end used for outputting hard line telemetering data to the satellite counting platform, the other end of the telemetering output branch is grounded, and a connection point between the voltage stabilizing module and the protection module is connected with a negative cable of a grid-connected power supply path.
The protection module comprises a plurality of magnetic latching relays connected in series.
The voltage division module comprises a plurality of groups of resistor groups connected in series, and each group of resistor groups comprises a plurality of resistors connected in parallel.
The voltage stabilizing module consists of a voltage dividing module and voltage stabilizing diodes connected in parallel at two ends of the voltage dividing module.
The voltage input branch comprises: diode V1, diode V2, diode V3, diode V4, resistor R1, resistor 2, resistor R3, resistor R4, magnetic latching relay K1, and magnetic latching relay K2;
the anode of the diode V1 is connected with the anode of the diode V3 and then connected with an external test voltage, the cathode of the diode V1 is connected with the cathode of the diode V3, the anode of the diode V2 and the anode of the diode V4, and the cathode of the diode V2 is connected with the cathode of the diode V4 and then connected with one end of the resistor R1; one end of the resistor R2 is connected with one end of the resistor R1, the other end of the resistor R1 is connected with the other end of the resistor R2, one end of the resistor R3 and one end of the resistor R4, and the other end of the resistor R3 is connected with the other end of the resistor R4; the magnetic latching relay K1 and the magnetic latching relay K2 are connected in series, one end of the series circuit is connected to the other end of the resistor R4, and the other end of the series circuit is connected to a positive cable of the grid-connected power supply path.
The positive return line isolation branch comprises: a resistor R5, a resistor 6, a resistor R7, a resistor R8, a magnetic latching relay K3 and a magnetic latching relay K4;
the magnetic latching relay K3 and the magnetic latching relay K4 are connected in series, one end of the series circuit is connected with one end of the resistor R5, and the other end of the series circuit is connected with a positive cable of the grid-connected power supply circuit; one end of the resistor R5 is connected with one end of the resistor R6, and the other end of the resistor R5 is connected with the other end of the resistor R6, one end of the resistor R7 and one end of the resistor R8; the other end of the resistor R7 is connected with the other end of the resistor R8, and the other end of the resistor R7 is used as a telemetry output end to output hard line telemetry data to the satellite counting platform.
The telemetry output branch comprises: a resistor R9, a resistor R10, a resistor R11, a resistor R12, a zener diode V5, a magnetic latching relay K5 and a magnetic latching relay K6;
one end of the resistor R9 is connected with the telemetering output end and one end of the resistor R11, the other end of the resistor R9 is connected with one end of the resistor R10, one end of the resistor R12 and the other end of the resistor R11, and the other end of the resistor R10 is connected with the other end of the resistor R12; the anode of the voltage stabilizing diode V5 is connected with the other end of the resistor R12 and a cathode cable of a grid-connected power supply path, and the cathode of the voltage stabilizing diode V5 is connected with one end of the resistor R9; the magnetic latching relay K5 and the magnetic latching relay K6 are connected in series, one end of the series circuit is connected to the other end of the resistor R10, and the other end of the series circuit is grounded. The test voltage is + 12V.
Compared with the prior art, the invention has the beneficial effects that:
1) the voltage stabilizing module is arranged between the telemetering output and the +12V test voltage, and the voltage stabilizing diode is adopted for voltage stabilizing treatment, so that the voltage of the telemetering output is ensured not to exceed the voltage requirement of the digital telemetering interface.
2) According to the invention, the isolation module is arranged between the test voltage and the grid-connected power supply path, and the +100V grid-connected power supply path can not influence the branch of the detection system under any condition through the two series-parallel diodes.
3) According to the invention, the short circuit inspection is carried out on the power supply path between the grid-connected switches of the two butt-joint spacecrafts by using the mode of combining the voltage input branch and the magnetic latching relay, so that the safety of the 100V bus of the source-end spacecraft is ensured.
Drawings
FIG. 1 is a schematic diagram of power supply path inspection after different spacecraft are docked;
fig. 2 is a schematic diagram of a butt-joint grid-connected short circuit detection circuit of the invention.
Detailed Description
The bus safety of the spacecraft is of vital importance, after the butt joint of different spacecrafts is completed, the grid-connected single machine of the source end spacecraft needs to supply power to the grid-connected single machine of the load end spacecraft, the invention utilizes a mode of combining a +12V resistance voltage-dividing branch and a magnetic latching relay to carry out short circuit check on a power supply path between grid-connected switches of two butt joint spacecrafts, and after the safety of the power supply path is confirmed through the telemetering output of a short circuit detection circuit, a closing instruction of the grid-connected switch is executed, and the source end spacecraft starts to supply power and output.
The invention relates to a spacecraft rendezvous butt joint grid-connected short circuit detection circuit which is arranged in a grid-connected single machine of a source-end spacecraft, wherein the circuit comprises: magnetic latching relays, resistors and diodes. The invention utilizes a 12V resistance voltage-dividing branch in a single machine, and is connected with a 100V power supply channel in parallel through a relay and a diode, and 6 relays synchronously receive program-controlled/remote-controlled action instructions. After the spacecraft is docked, the 6 relays receive the 'ON' instruction and are simultaneously closed, a 100V power supply path is equivalent to impedance and is connected with the 12V resistance voltage division branch in parallel, whether a short circuit exists ON the 100V power supply path can be known through short circuit detection and telemetering output, when the situation that the power supply path does not have the short circuit is confirmed, the 6 relays receive the 'OFF' instruction and are simultaneously disconnected, the 12V resistance voltage division branch is disconnected with the 100V power supply path, then the closing instruction of a grid-connected switch can be executed, and power supply is started. The invention solves the safety detection of the butt joint access of different spacecrafts and ensures the safety of the 100V bus of the source-end spacecraft.
The invention discloses a spacecraft rendezvous and docking grid-connected short circuit detection circuit, which is shown in figure 2 and comprises the following components: the device comprises an isolation module, a voltage division module, a protection module and a voltage stabilization module;
the protection module, the voltage division module and the isolation module are sequentially connected to serve as a voltage input branch; one end of the voltage input branch is connected with an external test voltage, and the other end of the voltage input branch is connected with a positive cable of a grid-connected power supply path;
the voltage division module and the protection module are sequentially connected to be used as a positive circuit line isolation branch; one end of the positive loop line isolation branch is connected with a positive cable of a grid-connected power supply path, and the other end of the positive loop line isolation branch is used as an output end for outputting hard line telemetering data to the satellite counting platform;
the voltage stabilizing module and the protection module are sequentially connected to serve as a telemetering output branch circuit; one end of the telemetering output branch is connected with an output end used for outputting hard line telemetering data to the satellite counting platform, the other end of the telemetering output branch is grounded, and a connection point between the voltage stabilizing module and the protection module is connected with a negative cable of a grid-connected power supply path, namely a return line of the grid-connected power supply path.
The protection module comprises a plurality of magnetic latching relays connected in series, the voltage dividing module comprises a plurality of groups of resistor groups connected in series, each group of resistor groups comprises a plurality of resistors connected in parallel, and the voltage stabilizing module comprises a voltage dividing module and voltage stabilizing diodes connected in parallel at two ends of the voltage dividing module.
As shown in fig. 1, the voltage input branch includes: diode V1, diode V2, diode V3, diode V4, resistor R1, resistor 2, resistor R3, resistor R4, magnetic latching relay K1, and magnetic latching relay K2;
the anode of the diode V1 is connected with the anode of the diode V3 and then connected with an external test voltage, the cathode of the diode V1 is connected with the cathode of the diode V3, the anode of the diode V2 and the anode of the diode V4, and the cathode of the diode V2 is connected with the cathode of the diode V4 and then connected with one end of the resistor R1; one end of the resistor R2 is connected with one end of the resistor R1, the other end of the resistor R1 is connected with the other end of the resistor R2, one end of the resistor R3 and one end of the resistor R4, and the other end of the resistor R3 is connected with the other end of the resistor R4; the magnetic latching relay K1 and the magnetic latching relay K2 are connected in series, one end of the series circuit is connected to the other end of the resistor R4, and the other end of the series circuit is connected to a positive cable of the grid-connected power supply path.
The positive return line isolation branch comprises: a resistor R5, a resistor 6, a resistor R7, a resistor R8, a magnetic latching relay K3 and a magnetic latching relay K4;
the magnetic latching relay K3 and the magnetic latching relay K4 are connected in series, one end of the series circuit is connected with one end of the resistor R5, and the other end of the series circuit is connected with a positive cable of the grid-connected power supply circuit; one end of the resistor R5 is connected with one end of the resistor R6, and the other end of the resistor R5 is connected with the other end of the resistor R6, one end of the resistor R7 and one end of the resistor R8; the other end of the resistor R7 is connected with the other end of the resistor R8, and the other end of the resistor R7 is used as a telemetry output end to output hard line telemetry data to the satellite counting platform.
The telemetry output branch comprises: a resistor R9, a resistor R10, a resistor R11, a resistor R12, a zener diode V5, a magnetic latching relay K5 and a magnetic latching relay K6;
one end of the resistor R9 is connected with the telemetering output end and one end of the resistor R11, the other end of the resistor R9 is connected with one end of the resistor R10, one end of the resistor R12 and the other end of the resistor R11, and the other end of the resistor R10 is connected with the other end of the resistor R12; the anode of the voltage stabilizing diode V5 is connected with the other end of the resistor R12 and a cathode cable of a grid-connected power supply path, and the cathode of the voltage stabilizing diode V5 is connected with one end of the resistor R9; the magnetic latching relay K5 and the magnetic latching relay K6 are connected in series, one end of the series circuit is connected to the other end of the resistor R10, and the other end of the series circuit is grounded.
Examples
As shown in figure 1, 6 magnetic latching relays K1-K6 are adopted, and the 6 magnetic latching relays receive the same on or off command, wherein the magnetic latching relay K1 and the magnetic latching relay K2 are in single-contact series connection, so that reliable disconnection of +12V and +100V is ensured. The magnetic latching relay K3 and the magnetic latching relay K4 are in series connection through a single contact, and reliable disconnection of the +100V and the short circuit detection branch circuit is guaranteed. Magnetic latching relay K5 and magnetic latching relay K6 are single contacts connected in series, ensuring reliable disconnection between primary ground and secondary ground.
The circuit is composed of 12 resistors from R1 to R12, and the resistors from R1 to R4, from R5 to R8 and from R9 to R12 are all formed in a two-series and two-parallel mode, so that the failure modes of open circuit and short circuit of the resistors can be effectively avoided.
The two ends of the resistor R9-the resistor R12 are connected with a voltage stabilizing diode V5 in parallel, so that the telemetering output voltage is ensured not to exceed the requirement of digital tube telemetering on a source end in the construction specification, and the safety of digital tubes is ensured.
The diodes V1-V4 are used for 4 diodes, and the impact of the +100V bus on the +12V bus can be prevented by adopting a two-serial and two-parallel mode.
The working principle of the whole circuit is as follows: after the butt joint of different spacecrafts is completed and before a grid-connected switch is closed, a single machine receives a short circuit detection opening instruction, a magnetic latching relay K1-a magnetic latching relay K6 is closed, 12V is reduced to 11V after passing through a diode V1-a diode V4, the voltage of the 11V is divided into voltage by a circuit network formed by a resistor R1-a resistor R4, a resistor R5-a resistor R8, a resistor R9-a resistor R12, a resistor R13 and a resistor R14, whether a short circuit fault exists in a power supply circuit can be judged by short circuit detection telemetering voltage output, when the short circuit detection telemetering output is less than 0.5V, the power supply circuit can be judged to have a short circuit, the fault needs to be eliminated and then is detected again, and after the power supply circuit is determined to be safe, grid-.
Claims (2)
1. Spacecraft rendezvous and docking grid-connected short-circuit detection circuit is characterized by comprising: the device comprises an isolation module, a voltage division module, a protection module and a voltage stabilization module;
the protection module, the voltage division module and the isolation module are sequentially connected to serve as a voltage input branch; one end of the voltage input branch is connected with an external test voltage, and the other end of the voltage input branch is connected with a positive cable of a grid-connected power supply path;
the voltage division module and the protection module are sequentially connected to be used as a positive circuit line isolation branch; one end of the positive loop line isolation branch is connected with a positive cable of a grid-connected power supply path, and the other end of the positive loop line isolation branch is used as an output end for outputting hard line telemetering data to the satellite counting platform;
the voltage stabilizing module and the protection module are sequentially connected to serve as a telemetering output branch circuit; one end of the telemetering output branch is connected with an output end used for outputting hard line telemetering data to the satellite counting platform, the other end of the telemetering output branch is grounded, and a connection point between the voltage stabilizing module and the protection module is connected with a negative cable of a grid-connected power supply path;
the protection module comprises a plurality of magnetic latching relays connected in series;
the voltage division module comprises a plurality of groups of resistor groups connected in series, and each group of resistor groups comprises a plurality of resistors connected in parallel;
the voltage stabilizing module consists of a voltage dividing module and voltage stabilizing diodes connected in parallel at two ends of the voltage dividing module;
the voltage input branch comprises: diode V1, diode V2, diode V3, diode V4, resistor R1, resistor 2, resistor R3, resistor R4, magnetic latching relay K1, and magnetic latching relay K2;
the anode of the diode V1 is connected with the anode of the diode V3 and then connected with an external test voltage, the cathode of the diode V1 is connected with the cathode of the diode V3, the anode of the diode V2 and the anode of the diode V4, and the cathode of the diode V2 is connected with the cathode of the diode V4 and then connected with one end of the resistor R1; one end of the resistor R2 is connected with one end of the resistor R1, the other end of the resistor R1 is connected with the other end of the resistor R2, one end of the resistor R3 and one end of the resistor R4, and the other end of the resistor R3 is connected with the other end of the resistor R4; the magnetic latching relay K1 and the magnetic latching relay K2 are connected in series, one end of the series circuit is connected with the other end of the resistor R4, and the other end of the series circuit is connected with a positive cable of a grid-connected power supply circuit;
the positive return line isolation branch comprises: a resistor R5, a resistor 6, a resistor R7, a resistor R8, a magnetic latching relay K3 and a magnetic latching relay K4;
the magnetic latching relay K3 and the magnetic latching relay K4 are connected in series, one end of the series circuit is connected with one end of the resistor R5, and the other end of the series circuit is connected with a positive cable of the grid-connected power supply circuit; one end of the resistor R5 is connected with one end of the resistor R6, and the other end of the resistor R5 is connected with the other end of the resistor R6, one end of the resistor R7 and one end of the resistor R8; the other end of the resistor R7 is connected with the other end of the resistor R8, and the other end of the resistor R7 is used as a telemetering output end to output hard line telemetering data to the satellite counting platform;
the telemetry output branch comprises: a resistor R9, a resistor R10, a resistor R11, a resistor R12, a zener diode V5, a magnetic latching relay K5 and a magnetic latching relay K6;
one end of the resistor R9 is connected with the telemetering output end and one end of the resistor R11, the other end of the resistor R9 is connected with one end of the resistor R10, one end of the resistor R12 and the other end of the resistor R11, and the other end of the resistor R10 is connected with the other end of the resistor R12; the anode of the voltage stabilizing diode V5 is connected with the other end of the resistor R12 and a cathode cable of a grid-connected power supply path, and the cathode of the voltage stabilizing diode V5 is connected with one end of the resistor R9; the magnetic latching relay K5 and the magnetic latching relay K6 are connected in series, one end of the series circuit is connected to the other end of the resistor R10, and the other end of the series circuit is grounded.
2. The spacecraft meeting butt-joint grid-connected short-circuit detection circuit according to claim 1, characterized in that the test voltage is + 12V.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910153180.XA CN109799416B (en) | 2019-02-28 | 2019-02-28 | Spacecraft rendezvous and docking grid-connected short circuit detection circuit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201910153180.XA CN109799416B (en) | 2019-02-28 | 2019-02-28 | Spacecraft rendezvous and docking grid-connected short circuit detection circuit |
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| CN109799416A CN109799416A (en) | 2019-05-24 |
| CN109799416B true CN109799416B (en) | 2021-07-13 |
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Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8159366B2 (en) * | 2008-07-16 | 2012-04-17 | The Boeing Company | Measurement of current and voltage of an in-orbit solar array |
| CN102324920B (en) * | 2011-04-13 | 2013-05-01 | 北京卫星制造厂 | Fault isolation electronic switch applicable to direct current power supply system of spacecraft |
| CN102306592A (en) * | 2011-08-25 | 2012-01-04 | 航天东方红卫星有限公司 | Magnetic latching relay power supply control circuit with short circuit protection |
| CN105883011B (en) * | 2015-01-23 | 2018-06-12 | 北京空间飞行器总体设计部 | A kind of platform interface system of parallel operation Double tabletop spacecraft |
| CN204650165U (en) * | 2015-05-12 | 2015-09-16 | 成钢 | A kind of dual network beacon telemetering remote control terminal |
| CN106501640B (en) * | 2016-10-18 | 2019-05-10 | 北京空间技术研制试验中心 | Electrical property integrated test facility after reusable launch vehicle returns |
| CN206804783U (en) * | 2017-06-15 | 2017-12-26 | 盈帜科技（常州）有限公司 | A kind of short-circuit detecting circuit of outlet line |
| CN108958142B (en) * | 2018-06-15 | 2019-11-08 | 上海卫星工程研究所 | It is a kind of to disconnect control device for satellite test and the electric connector of transmitting |
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