阅读说明：本技术 一种多级运载火箭的时标产生电路及时标分发系统 (Time scale generating circuit and time scale distributing system of multistage carrier rocket ) 是由 彭小波 漆光平 严卿 赵也倪 于 2020-07-06 设计创作，主要内容包括：本发明公开了一种多级运载火箭的时标产生电路及时标分发系统,该时标产生电路包括：电连接器,设置于地面与所述多级运载火箭之间,当多级运载火箭处于未起飞状态时,所述电连接器导通；当多级运载火箭起飞时,所述电连接器断开；开关电路,所述开关电路的输入端通过电连接器连接至电源,输出端与采样电路连接,第二端接地。如此设置,通过采用电连接器提供起飞信号,采样电路在采集到起飞信号之后以数字信号进行传输,取代了传统技术中采用起飞触点的技术方案。并且采样电路在识别之后,以数字信号进行传输时,也不容易受到传输线路长度和压降的干扰,解决了模拟量信号在传输过程中容易误触发的问题,从而提高了对起飞信号的传输质量。(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.)

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.

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

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.