CN111756361A - Time scale generating circuit and time scale distributing system of multistage carrier rocket - Google Patents
Time scale generating circuit and time scale distributing system of multistage carrier rocket Download PDFInfo
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Abstract
The invention discloses a time mark generating circuit and a time mark distributing system of a multistage launch vehicle, wherein the time mark generating circuit comprises: the electric connector is arranged between the ground and the multistage carrier rocket, and is conducted when the multistage carrier rocket is in a non-takeoff state; when the multi-stage carrier rocket takes off, the electric connector is disconnected; and the input end of the switching circuit is connected to a power supply through an electric connector, the output end of the switching circuit is connected with the sampling circuit, and the second end of the switching circuit is grounded. According to the arrangement, the takeoff signal is provided by the electric connector, and the sampling circuit transmits the takeoff signal in a digital signal manner after acquiring the takeoff signal, so that the technical scheme of adopting a takeoff contact in the traditional technology is replaced. And after the sampling circuit is identified, when the sampling circuit is transmitted by digital signals, the sampling circuit is not easily interfered by the length of a transmission line and the voltage drop, and the problem that analog quantity signals are easily triggered by mistake in the transmission process is solved, so that the transmission quality of takeoff signals is improved.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a time scale generating circuit and a time scale distributing system of a multistage launch vehicle.
Background
In the prior art, a takeoff signal is generally used as a time scale signal for a time scale signal of a multi-stage launch vehicle electrical system, and the time scale signal is used as a starting point signal for unified timing work of all related systems. As shown in fig. 1, the takeoff signal is generally given by the power distributor of the launch vehicle in a centralized manner, and the takeoff signal is obtained by switching on an electromagnetic relay by a takeoff contact switch of the launch vehicle, and the electromagnetic relay is transmitted to a takeoff and delivery utilization system and a takeoff and delivery measurement system through a contact thereof, wherein the signals in the transmission process are analog quantity signals.
In the transmission process, the takeoff signal is directly transmitted by an analog quantity signal. Because the transmission line has resistance, when current flows through the transmission line, the transmission line has voltage drop. Therefore, the analog quantity signal is inevitably influenced by the length and the voltage drop of the transmission line in the transmission process, so that the signal is easily interfered, the takeoff signal is easily triggered by mistake, and the transmission quality of the signal is influenced.
Disclosure of Invention
Therefore, the invention aims to solve the technical problem that the takeoff signal is easily interfered in the prior art, so that the takeoff signal is easily triggered by mistake, and the transmission quality of the takeoff signal is influenced. The invention further provides a time mark generation circuit and a time mark distribution system of the multi-stage launch vehicle.
The embodiment of the invention provides a time scale generating circuit of a multistage launch vehicle, which comprises: the electric connector is arranged between the ground and the multistage carrier rocket, and is conducted when the multistage carrier rocket is in a non-takeoff state; when the multi-stage carrier rocket takes off, the electric connector is disconnected; and the input end of the switching circuit is connected to a power supply through an electric connector, the first output end of the switching circuit is connected with the sampling circuit, and the second output end of the switching circuit is grounded.
Optionally, the switching circuit is any one of a triode, an MOS transistor, and an isolation optocoupler.
Optionally, the switch circuit is an isolation optocoupler, an input end anode of the isolation optocoupler is connected with the power supply, and an input end cathode of the isolation optocoupler is connected with the ground terminal.
Optionally, the time scale generating circuit further includes a filter capacitor, an output terminal of the filter capacitor is connected to a positive terminal of the input terminal, and a second terminal of the filter capacitor is connected to a negative terminal of the input terminal.
Optionally, the time scale generating circuit further comprises a rectifying diode, wherein an anode of the rectifying diode is connected with a cathode of the input terminal, and a cathode of the rectifying diode is connected with an anode of the input terminal.
Optionally, the power supply comprises a first power supply and a second power supply; the first power supply is connected with the input end of the switch circuit through the electric connector; the second power supply is connected between the output end of the switch circuit and the sampling circuit.
The invention also provides a time scale distribution system of the multistage launch vehicle, which comprises: the time stamp generating circuit of any of the above; the bus is laid on the sublevel carrier rocket; the multistage launch vehicle consists of a plurality of the substage launch vehicles, and signals are transmitted among the substage launch vehicles through an inter-stage connector; a main computer provided to one of the substage launch vehicles; the receiving end of the host computer is connected with the sampling circuit of the time scale generating circuit, and the output end of the host computer is connected with the bus; the sub-computers are arranged on the rest of the sub-stage carrier rockets; and the receiving end of the sub computer is connected with the bus.
Optionally, the host computer controls the terminal device in the substage launch vehicle in which the host computer is located through the master controller; and the sub-computer controls the terminal equipment in the sub-stage carrier rocket in which the sub-computer is positioned through the sub-controller.
Optionally, the terminal device is at least partially connected to the bus.
Optionally, the time scale distribution system further includes a filter circuit, an input end of the filter circuit is connected to the sampling circuit, and an output end of the filter circuit is connected to the receiving end of the host computer.
Compared with the prior art, the technical scheme of the invention has the following advantages:
1. the embodiment of the invention provides a time scale generating circuit of a multistage launch vehicle, which comprises: a power source; the electric connector is arranged between the ground and the multistage carrier rocket, and is conducted when the multistage carrier rocket is in a non-takeoff state; when the multi-stage carrier rocket takes off, the electric connector is disconnected; and the input end of the switching circuit is connected to a power supply through an electric connector, the first output end of the switching circuit is connected with the sampling circuit, and the second output end of the switching circuit is grounded.
The embodiment of the invention provides the takeoff signal by adopting the electric connector, and the sampling circuit transmits the takeoff signal by the digital signal after acquiring the takeoff signal, thereby replacing the technical scheme that the takeoff contact is adopted in the traditional technology and the analog quantity signal is directly transmitted. And after the sampling circuit identifies the takeoff signal converted from the low level to the high level, the sampling circuit is not easily interfered by the length of a transmission line and the voltage drop when the sampling circuit transmits the takeoff signal by a digital signal, so that the problem that the analog quantity signal is easily triggered by mistake in the transmission process is solved, and the transmission quality of the takeoff signal is improved.
2. The embodiment of the invention provides a time scale distribution system of a multistage launch vehicle, which comprises: a time stamp generating circuit, a bus, a host computer and a sub-computer as described in any of the above. In this configuration, after receiving the time scale signal from the time scale generating circuit through the receiving terminal, the host computer transmits the time scale signal to the sub-computers of the remaining sub-stage launch vehicles through the bus laid on each sub-stage launch vehicle. And after receiving the time scale signals, all the sub-computers perform table alignment, and perform time synchronization processing by taking the time scale signals as time zero points of initial work of the working equipment in each sub-stage carrier rocket.
3. By arranging the filtering device, the invention can filter out signal jitter or interference signals caused by the separation of the electric connectors or the interference on the circuit during the takeoff of the rocket, thereby ensuring higher reliability of the obtained takeoff signals.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a prior art takeoff signal acquisition circuit diagram;
FIG. 2 is a circuit diagram of a timing mark generation circuit according to an embodiment of the present invention;
FIG. 3 is a block diagram of a time scale distribution system according to an embodiment of the present invention;
FIG. 4 is an overall schematic diagram of a time-scale dispatch system for a multi-stage launch vehicle according to an embodiment of the present invention;
FIG. 5 is a schematic view of a multi-stage launch vehicle and rocket-ground connector according to an embodiment of the present invention;
fig. 6 is a schematic diagram of a signal waveform at an input end of an isolation optocoupler according to an embodiment of the invention.
Description of reference numerals:
1-substage launch vehicle; 2-a cable; 3-arrow ground connector; 31-dual redundant flying leads; 4-core bar; 5-steel wire; 6-interstage connector;
10-a switching circuit; 20-a sampling circuit;
a first power supply V1; a second power supply V2; a filter capacitor C; a rectifier diode D; and an isolation optocoupler Q.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In addition, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
In the prior art, a takeoff signal is generally used as a time scale signal of a multi-stage launch vehicle electrical system, and the time scale signal is used as a signal of a certain time standard. The takeoff signal is usually given by a power distribution controller of a carrier rocket in a centralized way, the takeoff signal is obtained by switching on an electromagnetic relay through a takeoff contact switch of the rocket, the electromagnetic relay is transmitted to a measuring system, a control system and an external system through a contact of the electromagnetic relay, and signals in the transmission process are analog quantity signals. In the transmission process, the analog quantity signal is directly transmitted. Because the transmission line has resistance, when current flows through the transmission line, the transmission line has voltage drop. Therefore, the analog quantity signal is inevitably influenced by the length and the voltage drop of the transmission line in the transmission process, so that the signal is easily interfered, false triggering is easily caused, and the transmission quality of the signal is influenced. In addition, the transmission mode in the prior art has the problems of more electromagnetic relays, complex wiring, poor flexibility, long line and low reliability.
The invention provides a time scale generating circuit and a time scale distributing system of a multistage launch vehicle, which are used for solving the problems of more electromagnetic relays, complex wiring, poor flexibility, long circuit and low reliability existing in the prior art when a takeoff signal is directly transmitted by adopting an analog quantity signal.
Example 1
As shown in fig. 2, an embodiment of the present invention provides a time scale generating circuit for a multi-stage launch vehicle, where the time scale generating circuit includes an electrical connector, a switching circuit 10, and a sampling circuit 20.
The input end of the switch circuit is connected with the power supply through the electric connector, the first output end is connected with the sampling circuit, and the second output end is grounded. An electric connector is connected between the multistage carrier rocket and the ground, and when the multistage carrier rocket is in a non-takeoff state, the electric connector is not disconnected and keeps a conduction state; when the multi-stage carrier rocket takes off, the multi-stage carrier rocket can be lifted off and further away from the ground, and when the distance reaches a certain degree, the electric connector can be automatically disconnected.
In the time scale generating circuit, the switching circuit and the sampling circuit are both arranged on the multi-stage launch vehicle. Because one end of the electric connector is fixed on the ground and the other end is fixed on the multi-stage carrier rocket, before the multi-stage carrier rocket takes off, the power supply supplies power to the switching circuit through the electric connector, so that the first output end and the second output end of the switching circuit are conducted, the sampling circuit is directly grounded, and the electric signal acquired by the sampling circuit is low level; when the multi-stage carrier rocket takes off, the electric connector is disconnected, the power supply is disconnected with the switch circuit, the first output end and the second output end of the switch circuit are disconnected under the condition that no power supply supplies power for the switch circuit, and the sampling circuit supplies power through the power supply, so that the electric signal acquired by the sampling circuit is high level.
Therefore, when the signals collected by the sampling circuit are converted from low level to high level, namely the takeoff time of the multi-stage carrier rocket, the takeoff signals are provided by the electric connector, and the sampling circuit transmits the takeoff signals by digital signals after collecting the takeoff signals, so that the technical scheme that the takeoff contacts are adopted in the traditional technology and the signals are directly transmitted by analog quantity signals is replaced. And after the sampling circuit identifies the takeoff signal converted from the low level to the high level, the sampling circuit is not easily interfered by the length of a transmission line and the voltage drop when the sampling circuit transmits the takeoff signal by a digital signal, so that the problem that the analog quantity signal is easily triggered by mistake in the transmission process is solved, and the transmission quality of the takeoff signal is improved.
As shown in fig. 5, in the present embodiment, the electrical connector is a rocket ground connector 3 or a rocket ground separation device. One end of the arrow-ground connector 3 is connected with a time mark generating circuit through a cable 2, the other end of the arrow-ground connector fixes a core bar 4 on the launching platform through a steel wire 5, and the core bar 4 is connected with the arrow-ground connector 3. By taking off the rocket, the fixed steel wire 5 on the launching platform drags the core bar 4, so that the rocket-ground connector 3 is mechanically separated, and the rocket-ground connector 3 falls off and is separated. The rocket ground connector 3 is internally provided with a dual-redundancy jumper 31 for identifying a takeoff signal, one end of the dual-redundancy jumper 31 is connected with a power supply, and the other end of the dual-redundancy jumper 31 is connected with a switch circuit. When the dual-redundancy overline 31 is separated, the connection point is changed into a disconnection state from a connection state, so that the power supply is disconnected with the switch circuit, the first output end and the second output end of the switch circuit are disconnected under the condition that no power supply is used for supplying power to the switch circuit, the sampling circuit supplies power through the power supply, and therefore the electric signal acquired by the sampling circuit is converted into a high level from a low level.
Of course, the electrical connector may also adopt other separation devices that can conduct electricity, and this embodiment is merely illustrative and not restrictive. The electric connector can be changed by those skilled in the art according to actual conditions, and the same technical effects can be achieved.
Optionally, in some embodiments of the present invention, the power supply comprises a first power supply V1 and a second power supply V2, the first power supply V1 is connected to the input terminal of the switch circuit through the electrical connector, and the second power supply V2 is connected between the output terminal of the switch circuit and the sampling circuit.
In the time scale generating circuit, the switching circuit may be any one of a triode, a MOS transistor, and an isolation optocoupler Q. In the embodiment of the present invention, an isolation optocoupler Q is taken as an example, an input end anode of the isolation optocoupler Q is connected to a power supply, an input end cathode of the isolation optocoupler Q is connected to a ground end, a first output end is connected to the sampling circuit, and a second output end is grounded.
Before the multi-stage carrier rocket takes off, a power supply supplies power to an isolation optocoupler Q through an electric connector, so that a first output end and a second output end of the isolation optocoupler Q are conducted, and a sampling circuit is directly grounded, so that an electric signal acquired by the sampling circuit is at a low level; when the multi-stage carrier rocket takes off, the electric connector is disconnected, the power supply is disconnected with the isolation optocoupler Q, the isolation optocoupler Q is disconnected with the first output end and the second output end under the condition that no power supply supplies power to the isolation optocoupler Q, the sampling circuit directly supplies power through the power supply, so that the electric signal acquired by the sampling circuit is high level, and the logic of the circuit is changed from '0' to '1'. When the signal collected by the sampling circuit is converted from low level to high level, namely the time of taking off of the multi-stage carrier rocket.
Optionally, in some embodiments of the present invention, the time scale generating circuit further includes a filter capacitor C, a first end of the filter capacitor C is connected to the positive electrode of the input end of the isolation optocoupler Q, and a second end of the filter capacitor C is connected to the negative electrode of the input end. The filter capacitor C may function as a filter in the time scale generating circuit.
The time scale generation circuit can also comprise a rectifier diode D, wherein the anode of the rectifier diode D is connected with the cathode of the input end of the isolation optocoupler Q, and the cathode of the rectifier diode D is connected with the anode of the input end of the isolation optocoupler Q. So set up, can play certain rectification effect to this time scale production circuit.
Alternatively, in some embodiments of the present invention, the power source may be a first power source V1 and a second power source V2. The first power supply V1 is connected with the input end of the switch circuit through an electric connector, and the second power supply V2 is connected between the output unit of the switch circuit and the sampling circuit.
Example 2
As shown in fig. 3 and 4, an embodiment of the present invention further provides a time scale distribution system for a multi-stage launch vehicle, where the time scale distribution system includes: the system comprises a bus, a main computer, a sub-computer and a time mark generating circuit. The CPU in the main computer can be a central processing unit such as an MCU processor or an FPGA.
The bus is laid in each substage carrier rocket 1, the multistage carrier rocket is composed of a plurality of substages carrier rockets 1, and signals are transmitted among the plurality of substages carrier rockets 1 through inter-stage connectors 6. One of all the substage carrier rockets 1 is provided with a main computer, and the other substage carrier rockets 1 are provided with sub computers. The receiving end of the main computer is connected with the sampling circuit of the time mark generating circuit, the output end of the main computer is connected with the bus, and the receiving end of the sub-computer is connected with the bus. When the takeoff signal is transmitted as a time mark signal, the time mark signal can be transmitted to all terminal devices in the whole multi-stage carrier rocket through relay forwarding of the main computer and each stage of sub-computers, and time synchronization of all the terminal devices is achieved.
In the embodiment, bus distribution is adopted, the sub-computer is used as a bus station for access, a standard interface is adopted, the interface is simple, and the transmission is realized in a digital quantity form. And the bus adopts differential signal lines, so that the anti-interference capability and reliability are greatly improved, the expansibility is good, and the flexibility is strong. Therefore, the problems of more electromagnetic relays, complex wiring, poor flexibility, long circuit and low reliability in the transmission mode in the prior art are solved. Moreover, the relay transmission time scale signal is adopted, and the relay of the relay equipment can correct the signal, improve the quality of the signal and greatly break through the limitation of the transmission distance.
The timing mark generation circuit may be the timing mark generation circuit described in any of the above embodiments, and may generate the timing mark signal.
The main computer is connected with the sampling circuit through the IO port, the main computer directly collects the state of the IO port between the main computer and the sampling circuit, and whether the takeoff signal exists or not can be determined through the state of the IO port, namely whether the time scale signal exists or not. After receiving the time scale signal from the time scale generating circuit through the receiving terminal, the host computer transmits the time scale signal to the sub computers of the remaining sub-stage launch vehicles 1 through the bus laid on each sub-stage launch vehicle 1. After receiving the time scale signals, all the sub-computers perform a table-checking process, and perform a time synchronization process by using the time scale signals as time zeros of the initial operation of the working devices in each sub-stage launch vehicles 1.
When the synchronized device does not have a bus interface, the IO time scale signal provided by the rocket-borne computer can be received through an IO interface.
Alternatively, in some embodiments of the present invention, a main controller and a main terminal device are provided in the substage launch vehicle 1 in which the main computer is located, and the main computer controls the main terminal device through the main controller. The sub-stage carrier rocket 1 where the sub-computer is located is provided with a sub-controller and sub-terminal equipment, and the sub-computer controls the sub-terminal equipment through the sub-controller.
The main terminal device or/and the sub-terminal device can be selectively accessed into the bus according to actual conditions, and at least part of the main terminal device or/and the sub-terminal device needs to be connected to the bus.
After the separation of the multi-stage carrier rockets, each sub-stage carrier rocket 1 is provided with a sub-computer and a sub-terminal device, so that technicians can recover and analyze data of the sub-stage carrier rockets 1 which land on the ground after the separation, the production efficiency of the multi-stage carrier rockets is greatly improved, and the fault tolerance rate of the multi-stage carrier rockets in the launching process is improved.
The time scale distribution system also comprises a filter circuit, wherein the input end of the filter circuit is connected with the sampling circuit, and the output end of the filter circuit is connected with the receiving end of the host computer. After the time scale signal acquired by the sampling circuit enters the filter circuit, the filter circuit filters the interference of the time scale signal.
When the multi-stage launch vehicle takes off, the electric connector is in the separation process or the circuit is interfered, so that the time scale signal has signal jitter or interference signals, the main computer is likely to make misjudgment that the 'take-off signal' is effective, and the time scale signal needs to be filtered. In addition, a filtering link is set in acquisition software, and a takeoff signal can be given only when a certain time width is continuously met, so that the purpose of filtering interference signals is achieved.
As shown in fig. 6, the diagram is a schematic diagram of a signal waveform at an input end of an isolation optocoupler in the time scale generation circuit. When the multi-stage carrier rocket does not take off, the signal at the input end of the isolation optocoupler is at a high level, and when the multi-stage carrier rocket takes off, the electric connector is interfered in the separation process or a circuit, so that the time scale signal has signal jitter or interference signals, and the signal waveform has irregular jitter. In the presence of a jamming signal, the takeoff signal is not valid. When the electric connector is separated, signal jitter occurs, and whether the signal jitter is a takeoff signal needs to be determined after a preset time delta t. After the preset time delta t, the electric connector can be confirmed to be completely disconnected, the first power supply stops supplying power to the input end of the isolation optocoupler at the moment, and the input end of the isolation optocoupler presents a low-level signal.
Therefore, when the filter circuit is adopted, the filtering time can be set to be the preset time delta t, for example, 20ms, and is not less than the time of two control cycles, and signal jitter or interference signals caused by separation of an electric connector or interference on a circuit in the takeoff process can be filtered, so that misjudgment is avoided. After each device receives the time scale signal, the delta t is deducted to be used as a real time scale zero point.
By arranging the filter circuit, the invention can filter out signal jitter or interference signals caused by the separation of the electric connectors or the interference on the circuit during the takeoff of the rocket, thereby ensuring higher reliability of the obtained takeoff signals.
Optionally, in some embodiments of the present invention, the filtering circuit may perform filtering by setting software, so as to improve the accuracy of the takeoff signal by filtering out signal jitter or interference signals.
Of course, other types of filter circuits can be selected and used, and the filter function can be achieved. The embodiment is merely an illustration of the filtering device, and is not a limitation, and those skilled in the art can select other types of filtering devices according to the actual situation.
When the cabin section is crossed, a plurality of sub-stage carrier rockets 1 transmit signals through the inter-stage connector 6, and the main computer and all the sub-computers need to forward 'time scale signals' in a relay mode, so that the limitation of transmission distance is greatly broken through. And finally, time synchronization of the whole equipment of the multistage carrier rocket is realized by relaying the time scale signals.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications therefrom are within the scope of the invention.
Claims (10)
1. A time stamp generation circuit for a multi-stage launch vehicle, comprising:
the electric connector is arranged between the ground and the multistage carrier rocket, and is conducted when the multistage carrier rocket is in a non-takeoff state; when the multi-stage carrier rocket takes off, the electric connector is disconnected;
and the input end of the switching circuit is connected to a power supply through an electric connector, the first output end of the switching circuit is connected with the sampling circuit, and the second output end of the switching circuit is grounded.
2. The timing mark generation circuit according to claim 1, wherein the switching circuit is any one of a triode, a MOS transistor and an isolation optocoupler (Q).
3. The time scale generation circuit according to claim 2, wherein the switch circuit is an isolation optocoupler (Q), an input terminal of the isolation optocoupler (Q) is connected to the power supply at a positive terminal, and an input terminal of the isolation optocoupler (Q) is connected to a ground terminal at a negative terminal.
4. The time scale generation circuit according to claim 3, further comprising a filter capacitor (C), wherein a first end of the filter capacitor (C) is connected with an input end anode of the isolation optocoupler (Q), and a second end of the filter capacitor (C) is connected with an input end cathode of the isolation optocoupler (Q).
5. The time scale generation circuit according to claim 3 or 4, further comprising a rectifier diode (D), wherein an anode of the rectifier diode (D) is connected with a cathode of the input end of the isolation optocoupler (Q), and a cathode of the rectifier diode (D) is connected with an anode of the input end of the isolation optocoupler (Q).
6. The timing mark generation circuit according to claim 1, wherein the power supply includes a first power supply (V1) and a second power supply (V2); the first power supply (V1) is connected with the input end of the switch circuit through the electric connector; the second power supply (V2) is connected between the output of the switching circuit and the sampling circuit.
7. A time scale distribution system for a multi-stage launch vehicle, comprising:
a time stamp generating circuit as claimed in any one of claims 1 to 6;
the bus is laid on each substage carrier rocket (1); the multistage launch vehicle consists of a plurality of the substage launch vehicles (1), and signals are transmitted among the substage launch vehicles (1) through an inter-stage connector (6);
a main computer provided to one of the substages of the launch vehicles (1); the receiving end of the host computer is connected with the sampling circuit of the time scale generating circuit, and the output end of the host computer is connected with the bus;
the sub-computers are arranged on the rest of the sub-stage carrier rockets (1); and the receiving end of the sub computer is connected with the bus.
8. The time stamp distribution system according to claim 7,
a main controller and main terminal equipment are arranged in the sublevel carrier rocket (1) where the main computer is located, and the main computer controls the main terminal equipment through the main controller;
the sub-stage carrier rocket (1) where the sub-computers are located is internally provided with sub-controllers and sub-terminal equipment, and the sub-computers control the sub-terminal equipment through the sub-controllers.
9. The time stamp distribution system according to claim 8, wherein the master terminal device or/and the child terminal device are at least partially connected to the bus.
10. The time scale distribution system according to any one of claims 7-9, further comprising a filter circuit having an input coupled to said sampling circuit and an output coupled to a receiving end of said host computer.
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| CN202010642392.7A CN111756361A (en) | 2020-07-06 | 2020-07-06 | Time scale generating circuit and time scale distributing system of multistage carrier rocket |
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| CN202010642392.7A CN111756361A (en) | 2020-07-06 | 2020-07-06 | Time scale generating circuit and time scale distributing system of multistage carrier rocket |
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| CN (1) | CN111756361A (en) |
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