CN112066798A - Solid rocket wireless measurement, launch, control, power supply and distribution and safety control system - Google Patents

Abstract

The invention discloses a solid rocket wireless measurement, launch and control power supply, distribution and safety control system, which comprises a lithium battery, an rocket-borne data chain, an rocket-borne computer, a power distributor, a safety controller and a dormancy control pin, wherein the lithium battery, the rocket-borne data chain, the rocket-borne computer, the power distributor, the safety controller and the dormancy control pin are arranged on a rocket, the rocket-borne data chain and ground wireless measurement, launch and control equipment use a wireless link for communication, uplink instruction data sent by the ground wireless measurement, launch and control equipment to the rocket-borne data chain and downlink telemetering data sent by the rocket-borne data chain to the ground wireless measurement, launch and control equipment are included, and the power supply, distribution and safety control system has a long-term low-power-. According to the invention, through the integrated design of rocket-borne equipment, remote wireless communication is directly carried out between the rocket-borne equipment and the near-end testing, launching and controlling equipment and the rocket, so that the awakening of the rocket, the control power supply and the initiating explosive device power supply and distribution are completed, and the power of the rocket control power supply and the initiating explosive device power supply is cut off after the test is finished or the rocket is recovered, so that the rocket control power supply and the initiating explosive device power supply enter.

Description

A wireless measurement, launch, control, power supply, distribution and safety control system for solid rockets

technical field

The invention relates to a solid rocket wireless measurement, launch and control power supply, distribution and safety control system, which belongs to the field of rocket wireless measurement, launch and control.

Background technique

In the existing wireless measurement and control systems for missiles and rockets, most of the near-end measurement and control equipment and the remote measurement and control equipment use wireless communication for command and feedback data transmission. It is connected by umbilical cable, adopts RS-422, CAN and 1553B and other wired communication methods for command and feedback transmission, and provides ground power for the rocket.

This kind of measurement and control system needs to arrange the remote measurement and control equipment on the launch pad, and lay AC power or generator, UPS uninterruptible power supply, etc. on the launch pad to supply power for the remote measurement and control equipment and rockets. The steel armor room protects the remote measurement and control equipment and power supply.

The existing wireless measurement, launch and control system needs to lay remote equipment near the rocket and connect it with the rocket through the umbilical cable, resulting in poor mobility and low launch efficiency during field launch; the umbilical cable cannot be reused, increasing the launch cost; due to the high risk of rocket launch , before the launch, the personnel need to be evacuated to the safe area and then powered on. The power supply and distribution of the entire arrow equipment cannot be directly driven by the power switch on the arrow.

SUMMARY OF THE INVENTION

The technical problem solved by the present invention is: in order to overcome the deficiencies of the prior art, the present invention provides a solid rocket wireless measurement, launch and control power supply, distribution and safety control system. The device and the rocket directly communicate with the rocket through long-distance wireless communication to complete the wake-up of the rocket, the power supply and distribution of the control power supply and the power supply of the pyrotechnic product, and after the test is completed or the rocket is recovered, the power supply of the rocket control power supply and the power supply of the pyrotechnic product will be powered off and enter the dormant state. To replace the remote measurement and control equipment.

The technical solution of the present invention is:

A solid rocket wireless measurement, launch, control, power supply, distribution and safety control system, comprising a lithium battery installed on the rocket, a safety controller, a distributor, a dormant control pin, an rocket data link and an rocket computer;

The rocket-borne data link communicates with the ground wireless measurement, transmission and control equipment using a wireless link, including the uplink command data sent by the ground wireless measurement, transmission and control equipment to the rocket-borne data link and the downlink telemetry sent by the arrow-borne data link to the ground wireless measurement, transmission and control equipment. data;

The lithium battery includes the first control battery, the second control battery and the pyrotechnic battery, and supplies power to the safety controller;

The safety controller directly outputs the power supply of the first control battery and the second control battery to the distributor, and controls the power supply of the pyrotechnic battery, and then outputs the power supply of the pyrotechnic battery to the distributor;

The power distributor combines the power supply of the first control battery and the second control battery into a dormant power supply and a control power supply, and uses the power supply of the pyrotechnic battery as the power supply of the pyrotechnic product, and timely provides the dormant power supply and control to the rocket data link according to the control process. Power supply, providing control power to the rocket computer, safety controller and other rocket-borne control power supply equipment, and providing pyrotechnic power to the rocket-borne pyrotechnic circuit;

The sleep control pin controls the on-off state of the output sleep power of the distributor through the output of the sleep control circuit and the input of the sleep control circuit;

The arrow-borne data link has two working modes: "low power consumption" and "full power"; it can send one control battery-connected drive to the distributor, and forward the uplink command to the safety controller through one RS-422 interface. The RS-422 interface forwards the uplink command to the onboard computer;

The on-board computer provides 3-way switch quantity instructions to the distributor, which are the control battery grid connection instruction, the first control battery disconnection preparation instruction and the second control battery disconnection preparation instruction.

Further, when the rocket is in storage or transportation, the dormant control pin is in the "disconnected" state, and the safety controller controls the power supply of the pyrotechnic battery. All devices on the arrow are in an unpowered state.

Further, after the ground test or the rocket is erected at the launch site, the operator switches the dormant control pin to the "on" state, the distributor begins to provide the dormant power supply to the rocket data link, and the rocket data link enters the "low power consumption" state. ” mode, at this time, the control power supply and the pyrotechnic power supply have no power output, and other equipment on the arrow is in an unpowered state.

Further, after entering the launch process, send an uplink command to the rocket data link through the ground wireless measurement and control equipment, first wake up the rocket data link, and enter the "full power" mode; then, the rocket data link sends the control battery to the grid-connected drive. , the first control battery power supply and the second control battery power supply are merged into the control power supply network through the distributor, and all the control power supply equipment on the rocket is powered on; then, the onboard computer sends the control battery grid-connected command to ensure that the control battery passes through The backup relay in the distributor is reliably connected to the grid, and the dormant power output of the distributor is cut off; finally, the safety controller is made to release the control of the power supply of pyrotechnics, and the battery of pyrotechnics is output to the distributor to control the power supply; after the power supply and distribution is completed , the ground wireless measurement and control equipment sends measurement and control instructions to the arrow-borne computer through the arrow-borne data link.

Further, after completing the ground test or rocket landing recovery, first disconnect the power supply output of the safety controller's pyrotechnic battery; then, the rocket computer sends the first control battery disconnection preparation command and the second control battery disconnection preparation. command, and stop sending the control battery grid-connected command, so that the backup relay in the distributor is disconnected, and the dormant power supply restores power supply; then, the arrow-borne data link stops sending the control battery grid-connected drive, so that the distributor will connect the first control battery, The second control battery power supply is disconnected from the control power supply network, the control power supply is cut off, only the rocket data link is powered by the dormant power supply, and the rest of the equipment is powered off; then, the rocket data link enters the "low power consumption" mode; finally, the operation The personnel switched the dormancy control pin to the "disconnected" state, the dormancy power supply was powered off, and all the onboard equipment were powered off at this time.

Further, the control battery grid-connected drive is the power drive signal sent by the arrow data link to the distributor, which can directly drive the relay coil in the distributor. When invalid, the output is open, and the relay coil is not driven;

The control battery grid-connected command, the first control battery disconnection preparation command and the second control battery disconnection preparation command are the command signals sent by the onboard computer to the distributor. After being amplified by the triode drive circuit, the relay coil in the distributor can be driven. , when it is valid, the output control power supply +, drives the relay coil; when it is invalid, the output is open, and does not drive the relay coil;

Further, the power distributor includes a normally open relay A, a normally open relay B, a normally closed relay C, a normally closed relay D, a normally open relay E, a normally closed relay F, a normally closed relay G, and a first transistor drive circuit. , the second transistor drive circuit, the third transistor drive circuit, the first diode, the second diode and the third diode; each relay includes a control coil and an execution terminal; relay B is a backup relay;

The first control battery power supply +, the second control battery power supply + pass through the first diode and the second diode, respectively, and then merged, and then divided into two channels: one through the relay C execution terminal and the output of the sleep control loop, and through the external sleep The control pin is connected to the input of the dormant control loop and the execution end of relay D, and finally connected to the dormant power supply +; the other way through the execution end of the relay A and relay B in parallel is connected to the control power supply +;

The control battery is connected to the grid and is connected to the control power ground through the relay A coil;

Relay F is connected in parallel with the execution end of relay G and then connected in series with the coil of relay E, and then connected in parallel with the coils of relay B, relay C, and relay D; one end of the parallel circuit is connected to the control power supply +, and the other end is driven by the first triode. Connect to the control power ground;

The control power supply + the execution terminal of relay E is connected to the control battery grid-connected command and the first transistor drive circuit respectively;

The control power supply + is connected to the control power supply ground through the relay F coil and the second transistor drive circuit; the first control battery disconnection preparation command is connected to the second transistor drive circuit;

The control power supply + is connected to the control power supply ground through the relay G coil and the third transistor drive circuit; the second control battery disconnection preparation command is connected to the third transistor drive circuit;

Pyrotechnic battery regulated power supply + after passing through the third diode, it is directly connected to the inflammatory power supply +; the regulated power supply of the inflammatory product battery is directly connected to the inflammatory power supply ground;

Further, the safety controller includes an MCU module, an RS-422 interface circuit, an optocoupler isolation drive circuit, a normally open relay H and a normally open relay I; each relay includes a control coil and an execution terminal;

The RS-422 interface command input from the outside is sent to the MCU module through the RS-422 interface circuit. After the MCU module parses the command, it sends the pyrotechnic battery power supply/control command to the optocoupler isolation drive circuit;

The secondary power supply of the safety controller + the relay I coil and the relay H coil connected in parallel, and the execution end of the optocoupler isolation drive circuit, are connected to the secondary power supply of the safety controller;

Pyrotechnic battery power supply + after passing through the execution terminal of relay H, it is connected with the power supply control of the initiating power supply battery; after the power supply of the inflammatory chemical product battery passes through the execution terminal of relay I, it is connected to the power supply ground of the pyrotechnic product battery control;

Further, the arrow-borne data link uses the received dormant power supply and control power supply as a control battery for grid-connected drive;

When the arrow-borne data link is powered on, it first enters the "low power consumption" mode and operates with extremely low power consumption, so that the power stored in the control battery can provide the dormant power for the arrow-borne data link for a long time; in this mode, the arrow-borne data link The chain only receives wireless uplink command data, and when it receives the "wake up" command, it enters the "full power" mode;

In the "full power" mode, the onboard data link receives the wireless uplink command data, sends the wireless downlink telemetry data, and at the same time sends the control battery grid-connected drive to the distributor, and forwards it to the safety controller and the onboard computer through the RS-422 interface Upstream command data;

Further, the transistor driving circuit includes: a current limiting resistor R1, a resistor R2, a capacitor C1, a Zener diode T1 and an NPN transistor Q1;

The collector of the transistor Q1 is connected to the second interface, the emitter is connected to the third interface, the base is connected to the first interface through the current limiting resistor R1, and is connected to the emitter through the parallel resistor R2, capacitor C1, and Zener diode T1. ;

The first interface is connected to the input command, the second interface is connected to the external relay coil, and the third interface is connected to the external power supply ground.

Compared with the prior art, the beneficial effects of the content of the present invention are:

(1) The wireless measurement and control power supply and distribution and safety control system of the present invention redesigns the power supply and distribution circuit and safety controller of the rocket distributor, and cooperates with the rocket data link with dormancy and wake-up functions, which can replace the ground The remote measurement and control equipment and power supply use the near-end measurement and control equipment to carry out long-distance wireless communication with the rocket to realize long-distance wake-up, power supply and power supply control of the rocket;

(2) The present invention cancels the umbilical cable between the remote ground equipment, the rocket and the ground equipment, making the ground equipment layout simpler, reducing the complexity of the system, improving the launch efficiency, reliability and environmental adaptation of the rocket, and at the same time reduced costs;

(3) In the case of only relying on the lithium battery on the rocket, the rocket can wait for the launch window for dozens of days after entering the low-power state, so it has the ability to quickly enter the launch state, and simultaneously wake up, power supply and power off. The process does not require close-range control by the operator, which ensures the safety of the operator;

(4) The wireless communication between the ground measurement and control equipment of the present invention and the rocket has the function of spread-spectrum encryption, using a pseudo-random code with a long code period, after modulation by the pseudo-random code, the signal power spectral density of the wireless communication is very low, close to random noise, It is not easy to be discovered, deciphered or suppressed or deceptive interference, so as to avoid interference with the rocket's measurement, launch and control process.

Description of drawings

Fig. 1 is the framework diagram of rocket power supply and distribution and safety control system of the present invention;

Fig. 2 is the circuit principle diagram of the distributor of the present invention;

Fig. 3 is the circuit schematic diagram of the safety controller of the present invention;

FIG. 4 is a schematic diagram of the triode driving circuit of the present invention.

Detailed ways

The present invention will be further described in detail below in conjunction with the accompanying drawings.

A solid rocket wireless measurement, launch, control, power supply, distribution and safety control system includes a lithium battery 1 installed on the rocket, an rocket data link 5, an rocket computer 6, a power distributor 3, a safety controller 2, and a sleep control pin 4;

The rocket data link 5 communicates with the ground wireless measurement, transmission and control equipment 9 using a wireless link, including the uplink command data sent by the ground wireless measurement, transmission and control equipment 9 to the rocket data link 5 and the rocket data link 5 to the ground wireless measurement, transmission and control. Downlink telemetry data sent by device 9;

The lithium battery 1 includes a first control battery, a second control battery and a pyrotechnic battery, and supplies power to the safety controller 2;

The safety controller 2 directly outputs the power supply of the first control battery and the second control battery to the distributor 3 , and controls the power supply of the pyrotechnic battery, and then outputs the power supply of the pyrotechnic battery to the distributor 3 to control the power supply.

The power distributor 3 combines the power supply of the first control battery and the second control battery into a dormant power supply and a control power supply, uses the power supply of the pyrotechnic product battery as the power supply of the pyrotechnic product, and timely provides the dormant power supply to the rocket data link 5 according to the control process. and control power supply, provide control power supply to the rocket computer 6, safety controller 2 and other rocket-borne control power supply electrical equipment, and provide pyrotechnic power to the rocket-borne pyrotechnic circuit;

The sleep control pin 4 controls the on-off state of the output sleep power of the power distributor 3 through the output of the sleep control circuit and the input of the sleep control circuit;

Arrow-borne data link 5 has two working modes of "low power consumption" and "full power"; it can send 1 control battery grid-connected drive to distributor 3, and forward uplink commands to safety controller 2 through 1 RS-422 interface , forward the uplink command to the onboard computer 6 through 1 RS-422 interface;

The on-board computer 6 provides 3-way switching commands to the distributor 3, which are respectively the control battery grid connection command, the first control battery disconnection preparation command and the second control battery disconnection preparation command;

When the rocket is in storage or transportation, the dormant control pin 4 is in the "disconnected" state, and the safety controller 2 controls the power supply of the pyrotechnic battery. The device on the arrow is in an unpowered state;

After the ground test or the rocket is erected at the launch site, the operator switches the dormant control pin 4 to the "on" state, the distributor 3 starts to provide the dormant power supply to the rocket data link 5, and the rocket data link 5 enters the "low power" state. "Consumption" mode, at this time, the control power supply and pyrotechnic power supply have no power output, and other equipment on the arrow is in an unpowered state;

After entering the launch process, send an uplink command to the rocket data link 5 through the ground wireless measurement and control equipment 9, first wake up the rocket data link 5, and enter the "full power" mode; then, the rocket data link 5 sends a control battery to connect to the grid. Drive, so that the first control battery power supply and the second control battery power supply are merged into the control power supply network through the distributor 3, and all the onboard control power supply equipment are powered on; then, the onboard computer 6 sends the control battery grid-connected command to ensure that The control battery is reliably connected to the grid through the backup relay in the distributor 3, and the dormant power output of the distributor 3 is cut off; finally, the safety controller 2 is released from the control of the power supply of the pyrotechnics, and the power supply of the pyrotechnics battery is output to the distributor 3. ; After the power supply and distribution is completed, the ground wireless measurement and control equipment 9 sends the measurement and control instructions to the arrow-borne computer 6 through the arrow-borne data link 5;

After completing the ground test or the recovery of the rocket landing, first disconnect the power supply output of the pyrotechnic battery of the safety controller 2; then, the rocket computer 6 sends the first control battery disconnection preparation command and the second control battery disconnection preparation command. , and stop sending the control battery grid-connected command, so that the backup relay in the distributor 3 is disconnected, and at the same time the dormant power supply restores power supply; then, the arrow-borne data link 5 stops sending the control battery grid-connected drive, so that the distributor 3 will control the first control battery. The power supply of the battery and the second control battery is disconnected from the control power supply network, the control power supply is cut off, only the arrow data link 5 is powered by the dormant power supply, and the rest of the equipment is powered off; then, the arrow data link 5 enters the "low power consumption" mode ; Finally, the operator switches the dormancy control pin 4 to the "disconnected" state, the dormancy power supply is powered off, and all the arrow-borne equipment is powered off at this time.

The control battery grid-connected drive is a power drive signal sent by the arrow data link 5 to the distributor 3, which can directly drive the relay coil in the distributor 3. When it is valid, it outputs the sleep power supply or the control power supply to drive the relay coil; when When invalid, the output is open, and the relay coil is not driven;

The control battery grid connection command, the first control battery disconnection preparation command and the second control battery disconnection preparation command are the command signals sent by the onboard computer 6 to the distributor 3, and can drive the distribution device 3 after being amplified by the triode drive circuit. When the relay coil is valid, the output control power supply + will drive the relay coil; when it is invalid, the output will be open and the relay coil will not be driven;

Distributor 3 includes normally open relay A, normally open relay B, normally closed relay C, normally closed relay D, normally open relay E, normally closed relay F, normally closed relay G, first transistor drive circuit, second three A diode drive circuit, a third triode drive circuit, a first diode, a second diode and a third diode; each relay includes a control coil and an execution terminal; relay B is a backup relay;

The first control battery power supply +, the second control battery power supply + pass through the first diode and the second diode, respectively, and then merged, and then divided into two channels: one through the relay C execution terminal and the output of the sleep control loop, and through the external sleep Control pin 4 is connected to the input of the dormant control loop and the execution end of relay D, and finally connected to the dormant power supply +; the other way through the execution end of relay A and relay B in parallel is connected to the control power supply +;

The control battery is connected to the grid and is connected to the control power ground through the relay A coil;

Relay F is connected in parallel with the execution end of relay G and then connected in series with the coil of relay E, and then connected in parallel with the coils of relay B, relay C, and relay D; one end of the parallel circuit is connected to the control power supply +, and the other end is driven by the first triode. Connect to the control power ground;

The control power supply + the execution terminal of relay E is connected to the control battery grid-connected command and the first transistor drive circuit respectively;

The control power supply + is connected to the control power supply ground through the relay F coil and the second transistor drive circuit; the first control battery disconnection preparation command is connected to the second transistor drive circuit;

The control power supply + is connected to the control power supply ground through the relay G coil and the third transistor drive circuit; the second control battery disconnection preparation command is connected to the third transistor drive circuit;

Pyrotechnic battery regulated power supply + after passing through the third diode, it is directly connected to the inflammatory power supply +; the regulated power supply of the inflammatory product battery is directly connected to the inflammatory power supply ground;

The safety controller 2 includes an MCU module, an RS-422 interface circuit, an optocoupler isolation drive circuit, a normally open relay H and a normally open relay I; each relay includes a control coil and an executive terminal;

The RS-422 interface command input from the outside is sent to the MCU module through the RS-422 interface circuit. After the MCU module parses the command, it sends the pyrotechnic battery power supply/control command to the optocoupler isolation drive circuit;

The secondary power supply of the safety controller 2 + the relay I coil and the relay H coil connected in parallel, and the execution end of the optocoupler isolation drive circuit, are connected to the secondary power supply of the safety controller 2;

Pyrotechnic battery power supply + after passing through the execution terminal of relay H, it is connected with the power supply control of the initiating power supply battery; after the power supply of the inflammatory chemical product battery passes through the execution terminal of relay I, it is connected to the power supply ground of the pyrotechnic product battery control;

The arrow-borne data link 5 uses the received dormant power supply and control power supply as a control battery for grid-connected drive;

When the arrow data link 5 is powered on, it first enters the "low power consumption" mode and operates with extremely low power consumption, so that the power stored in the control battery can provide sleep power for the arrow data link 5 for a long time; in this mode, the arrow The carrier data link 5 only receives the wireless uplink command data, and enters the "full power" mode after receiving the "wake up" command;

In the "full power" mode, the arrow-borne data link 5 receives the wireless uplink command data, sends the wireless downlink telemetry data, and at the same time sends the control battery-connected drive to the distributor 3, and sends it to the safety controller 2 and the arrow through the RS-422 interface. The carrier computer 6 forwards the uplink instruction data;

The transistor drive circuit includes a current limiting resistor R1, a resistor R2, a capacitor C1, a Zener diode T1 and an NPN transistor Q1;

The collector of the transistor Q1 is connected to the second interface, the emitter is connected to the third interface, the base is connected to the first interface through the current limiting resistor R1, and is connected to the emitter through the parallel resistor R2, capacitor C1, and Zener diode T1. ;

The first interface is connected to the input command, the second interface is connected to the external relay coil, and the third interface is connected to the external power supply ground.

The technical principle of the present invention is described in detail as follows:

As shown in Figure 1, the work flow of the solid rocket wireless measurement, launch and control power supply and distribution and safety control system provided by the present invention is as follows:

Before the ground test or when the rocket is erected at the launch site, the whole rocket equipment is in an unpowered state; if it is necessary to enter the test and launch control or launch process, the operator switches the sleep control pin 4 to the "on" state, and the distributor 3 Start to provide the dormant power supply to the rocket data link 5, the rocket data link 5 enters the "low power consumption" mode, and starts to receive the wireless uplink wake-up command. Unpowered state; then the operator evacuated to a safe area and waited for the launch airspace;

After entering the ground test or launch process, the execution steps of the full-rocket power supply and distribution are as follows:

1. The ground measurement, transmission and control equipment sends a wake-up command upstream to the rocket data link 5, and the rocket data link 5 enters the "full power" mode and starts to send downlink telemetry data;

2. The ground measurement and control equipment sends up the arrow-borne data link 5 battery grid-connected drive command. After receiving the command, the arrow-borne data link 5 sends the control battery-connected drive to the distributor 3, and the distributor 3 connects the first control battery to supply power and the third 2. The control battery power supply is integrated into the control power supply network, so that all the control power supply equipment on the rocket is powered on;

3. The ground measurement, transmission and control equipment sends up the on-board computer 6 battery grid connection command. After receiving the command, the on-board data link 5 forwards the command to the on-board computer 6 through the RS-422 interface. After receiving the command, the on-board computer 6 sends the command to the distributor. 3 Send the control battery grid connection command, the distributor 3 uses the backup relay to reliably integrate the first control battery power supply and the second control battery power supply into the control power supply network, and cut off the output of the sleep control circuit, the input of the sleep control circuit and the inside of the distributor 3 At this time, the dormant power supply is cut off, and the arrow data link 5 only uses the control power supply to supply power;

4. The ground measurement, transmission and control equipment sends a command for connecting the pyrotechnic battery to the grid. After receiving the command, the rocket data link 5 forwards the command to the safety controller 2. The safety controller 2 releases the control of the pyrotechnic power supply and sends the 3. The output pyrotechnic battery controls the power supply, and then the rocket-borne computer 6 controls the power distributor 3 to supply power to the rocket-borne pyrotechnic circuit according to the mission requirements;

After completing the ground test or rocket landing recovery, the execution steps of the full rocket power off are as follows:

1. The ground measurement, transmission and control equipment sends a command to disconnect the explosive battery from the network. After receiving the command, the data link 5 on the rocket forwards the command to the safety controller 2. power outage;

2. After the ground measurement, transmission and control equipment sends the arrow-borne computer 6 battery disconnection preparation command upward, the arrow-borne data link 5 forwards the command to the arrow-borne computer 6, and the arrow-borne computer 6 sends the first control battery disconnection preparation to the distributor 3. The command and the second control battery disconnection preparation command, and at the same time, the control battery grid connection command becomes invalid. At this time, the backup relay is disconnected, the sleep power circuit output, the sleep power circuit input and the internal circuit of the power distributor 3 are connected, and the sleep power supply is connected. power recovery;

3. After the ground measurement, transmission and control equipment sends the arrow-borne data link 5 battery disconnection drive command, the control battery-connected drive sent by the arrow-borne data link 5 to the distributor 3 becomes invalid, and the distributor 3 turns the first control battery into an invalid state. The power supply, the second control battery power supply and the control power supply network are disconnected, and the control power supply is powered off. Only the arrow-borne data link 5 is powered by the dormant power supply, and the rest of the equipment is powered off;

4. The ground measurement and control equipment sends a sleep command upstream, and the data link 5 on the arrow enters the "low power consumption" mode;

5. The operator enters the test site and switches the dormancy control pin 4 to the "disconnected" state, and the dormancy power supply is powered off. At this time, all the onboard equipment are powered off, and the task process ends.

The wireless uplink command data adopts the PCM-DSSS-BPSK system, the frequency band is 1750MHz ~ 1850MHz, the power spectral density is very low, close to random noise, and it is not easy to be found, deciphered, or subject to suppression or deceptive interference, so as to avoid the influence of the aircraft measurement, launch and control process. The telemetry data uses the PCM-FM system, and the frequency band is 2200MHz to 2300MHz.

As shown in Figure 2, the power distributor 3 provided by the present invention controls the power supply and distribution steps as follows:

1. When the equipment on all arrows is not powered on, the execution terminals of relay A, relay B and relay E are in disconnected state, and the execution terminals of relay C, relay D, relay F and relay G are in closed state;

2. When the sleep control pin 4 outside the distributor 3 is switched to the on state, the first control battery supplies power, the second control battery supplies power through the closed relay C execution terminal, the output of the sleep control loop, the sleep control pin 4, and the sleep control The loop input and the closed relay D execution terminal provide the dormant power supply to the arrow data link 5;

3. When the control battery grid-connected drive becomes "valid", supply power to the relay A coil, the relay A execution terminal becomes closed, and connect the first control battery power supply + and the second control battery power supply + with the control power supply +. At this time, all arrows control the power supply and the electrical equipment is powered on;

4. When the control battery grid connection command becomes "valid", the first transistor drive circuit is turned on, and the coils of relay B, relay C, relay D, and relay E are powered by the control power supply. At this time, relay B executes The terminal is closed to ensure that the first control battery power supply +, the second control battery power supply + and the control power supply + are reliably connected, and the execution terminals of relay C and relay D are disconnected, so that the sleep control pin 4, the output of the sleep control circuit, and the input of the sleep control circuit It is disconnected from the circuit inside the distributor 3, the dormant power supply is cut off, and the execution end of the relay E is closed, so that the control power supply + take over the control battery grid-connected command sends an effective command to the first transistor drive circuit to realize the relay self-locking;

5. After the power supply of the pyrotechnic battery is controlled by the power distributor 3, it is used as the pyrotechnic power supply, and the external output is controlled by the pyrotechnic circuit;

In the power distributor 3 provided by the present invention, when all the equipment on the arrow is in the power-on state, the steps of controlling the power supply to cut off are as follows:

1. When the first control battery disconnection preparation command and the second control battery disconnection preparation command become "valid", the second transistor drive circuit and the third transistor drive circuit are turned on, and the relay F and the relay The coil of G is powered by the control power supply. At this time, the relay F and the execution end of the relay G are disconnected, so that the coil of the relay E is de-energized, the execution end of the relay E is disconnected, and the relay self-locking fails;

2. When the control battery grid connection command becomes "invalid", the first transistor drive circuit is disconnected, and the coils of relay B, relay C and relay D are powered off. At this time, the execution end of relay B is disconnected, and the relay C. The execution end of relay D is closed, and the external power supply of the dormant power supply is restored;

3. When the control battery grid-connected drive becomes "inactive", the relay A coil is powered off, and the relay A execution terminal is disconnected. At this time, the first control battery power supply +, the second control battery power supply + is disconnected from the control power supply + , the distributor 3 no longer outputs the control power supply, but only outputs the sleep power supply;

4. When the dormant control pin 4 outside the distributor 3 is switched to the off state, the dormant power supply is powered off;

As shown in Figure 3, the safety controller 2 provided by the present invention controls the power supply of the pyrotechnic products as follows:

1. When the safety controller 2 is not powered on, the execution terminals of relay H and relay I are disconnected. At this time, the power supply input of the pyrotechnic battery is isolated from the power supply output of the pyrotechnic battery control, and the pyrotechnic battery control The power supply is in a controlled state, and there is no power output;

2. After the safety controller 2 is powered on, the relay H and the execution end of the relay I remain disconnected, and the power supply controlled by the pyrotechnic battery continues to maintain the control state;

3. The MCU module parses the RS-422 interface command. If the safety controller 2 is required to output the power supply of the pyrotechnic product, the MCU module changes the power supply/control command of the pyrotechnic product battery to a high level. At this time, the optocoupler isolation circuit The execution terminal of the relay turns into a conducting state, the secondary power supply starts to supply power to the coils of relay H and relay I, the execution terminals of relay H and relay I are closed, and the pyrotechnic battery supplies power + and the pyrotechnic battery controls power supply + conduction, The power supply ground of the pyrotechnic product battery is connected to the power supply ground of the pyrotechnic product battery control, and the safety controller 2 outputs the power supply of the pyrotechnic product battery to control the power supply;

4. The MCU module parses the RS-422 interface command. If the safety controller 2 is required to disconnect the power supply of the pyrotechnic product, the MCU module changes the power supply/control command of the pyrotechnic product battery to a low level. At this time, the optocoupler is isolated. The execution end of the circuit becomes disconnected, the coil of relay H and relay I are de-energized, the execution end of relay H and relay I are disconnected, the power supply of the pyrotechnic product battery + and the power supply of the pyrotechnic product battery control + disconnected, the pyrotechnic product battery is powered + disconnected. When the power supply ground of the product battery is disconnected from the power supply ground of the pyrotechnic product battery control, the safety controller 2 stops outputting the power supply of the pyrotechnic product battery control system;

As shown in Figure 4, the working state of the transistor drive circuit is as follows:

When the input command of the first interface is in an open-circuit state, the collector and the emitter of the transistor Q1 are turned off, and the second interface and the third interface are open-circuited;

When the input command of the first interface is the control power supply + state, the collector and the emitter of the transistor Q1 are connected, and the second interface and the third interface are connected.

The examples given in the present invention are as follows:

With reference to Figure 2, the selection of components is explained: Relay A and relay B need to ensure that the full arrow control power supply is supplied, and the execution terminal flows through a current of 10A. Therefore, the JQX-1130M-02821II type relay of Aerospace Electric is selected, and its execution terminal is resistive load. is 30A, which meets the derating design criteria.

Relay C and relay D are responsible for the on-off control of the dormant power supply, and the executive terminal flows through a current of 5A. Therefore, the Aerospace Electric JZC-102MF/027-01-III relay is selected, and its executive terminal resistive load is 10A, which meets the derating design criteria.

Relay E, relay F and relay G are used to drive the triode drive circuit and relay coil, and the current flowing through the execution terminal is 0.5A. Therefore, the JZC-097MC/027-01-III type relay of Aerospace Electric is selected, and the resistance load of the execution terminal is 2A. Meets derating design guidelines.

The first diode, the second diode and the third diode are 2DK30100 diodes from Jinan Semiconductor Institute.

The following describes the selection of components with reference to Figure 3: resistor R1, resistor R2, capacitor C1, and Zener diode T1 to realize the voltage adjustment function of the base input of transistor Q1; according to the circuit characteristics, the resistance value of resistor R1 is 5KΩ; The resistance value of resistor R2 is selected as 1KΩ; the capacitance value of capacitor C1 is selected as 10uF; the breakdown voltage of Zener diode T1 is selected as 5V, and the Zener diode of Jinan Banyi Electronics BWB5V1 is selected;

The content not described in detail in the present invention is known to those skilled in the art.

Claims (10)

1. a solid rocket wireless measurement and control power supply and distribution and safety control system, is characterized in that: comprise the lithium battery (1), safety controller (2), distributor (3), dormancy control pin installed on the rocket (4), on-board data link (5) and on-board computer (6); The rocket data link (5) communicates with the ground wireless measurement, transmission and control equipment (9) using a wireless link, including uplink command data and rocket data sent by the ground wireless measurement and control equipment (9) to the rocket data link (5). The downlink telemetry data sent by the chain (5) to the ground wireless measurement, transmission and control equipment (9); The lithium battery (1) includes a first control battery, a second control battery and a pyrotechnic battery, and supplies power to the safety controller (2); The safety controller (2) directly outputs the power supply of the first control battery and the second control battery to the distributor (3), and controls the power supply of the pyrotechnic battery and then outputs the power supply of the pyrotechnic battery to the distributor (3) to control the power supply; The power distributor (3) combines the power supply of the first control battery and the second control battery into a dormant power supply and a control power supply, uses the power supply of the pyrotechnic battery as the power supply for the pyrotechnics, and sends the power supply to the rocket data link (5) in a timely manner according to the control process. ) provides dormant power and control power, provides control power to the rocket computer (6), safety controller (2) and other rocket-borne control power-consuming electrical equipment, and provides pyrotechnic power to the rocket-borne pyrotechnic circuit; The dormancy control pin (4) controls the power distribution device (3) to output the on-off state of the dormant power supply through the output of the dormant control circuit and the input of the dormant control circuit; The arrow-borne data link (5) has two working modes: "low power consumption" and "full power"; it can send a control battery-connected drive to the distributor (3), and send it to the safety controller through a RS-422 interface. (2) Forward the upward command, and forward the upward command to the onboard computer (6) through 1 RS-422 interface; The onboard computer (6) provides the power distributor (3) with 3-way switch quantity instructions, which are respectively the control battery grid connection instruction, the first control battery disconnection preparation instruction and the second control battery disconnection preparation instruction. 2. a kind of solid rocket wireless measurement, launch and control power supply and distribution and safety control system according to claim 1, is characterized as follows: when the rocket is in the storage or transportation process, the dormant control pin (4) is in a "disconnected" state , the safety controller (2) controls the power supply of the pyrotechnic battery. At this time, the dormant power supply, the control power supply and the pyrotechnic power supply have no power output, and all the equipment on the rocket is in an unpowered state. 3. a kind of solid rocket wireless measurement, launch and control power supply and distribution and safety control system according to claim 1 is characterized as follows: after ground test or rocket is erected at the launch site, the operator switches the dormant control pin (4) When it reaches the "on" state, the power distributor (3) starts to supply the dormant power supply to the arrow-borne data link (5), and the arrow-borne data link (5) enters the "low power consumption" mode. There is no power output, and other devices on the arrow are in an unpowered state. 4. a kind of solid rocket wireless measurement, launch and control power supply and distribution and safety control system according to claim 1, is characterized as follows: after entering the launch process, through the ground wireless measurement and launch control equipment (9) to the rocket data link ( 5) Send the uplink command, first wake up the data link on the arrow (5), and enter the "full power" mode; then, the data link on the arrow (5) sends the control battery for grid-connected drive, so that the first control battery supplies power and the second control battery The power supply is merged into the control power supply network through the distributor (3), and all the electric devices onboard the control power supply are powered on; then, the onboard computer (6) sends the control battery grid connection command to ensure that the control battery passes through the power distributor (3). The backup relay is connected to the grid reliably, and the dormant power output of the distributor (3) is cut off; finally, the safety controller (2) is released from the control of the power supply of the pyrotechnics, and the power supply of the pyrotechnics battery is output to the distributor (3) to control the power supply; After the power supply and distribution are completed, the ground wireless measurement, transmission and control equipment (9) sends measurement, transmission and control instructions to the rocket computer (6) through the rocket data link (5). 5. a kind of solid rocket wireless measurement, launch and control power supply and distribution and safety control system according to claim 1, is characterized as follows: after completing ground test or rocket landing recovery, first disconnect the fire of safety controller (2) The industrial battery controls the power supply output; then, the onboard computer (6) sends the first control battery disconnection preparation command and the second control battery disconnection preparation command, and stops sending the control battery grid connection command, so that the power distribution device (3) is connected to the grid. The backup relay is disconnected, and the power supply is restored from the dormant power supply at the same time; then, the arrow-borne data link (5) stops the sent control battery for grid-connected drive, so that the distributor (3) supplies power from the first control battery and the second control battery to the control power supply When the network is disconnected and the control power is cut off, only the data link (5) on the rocket is powered by the sleep power supply, and the rest of the equipment is powered off; then, the data link on the rocket (5) enters the "low power consumption" mode; finally, the operator will sleep The control pin (4) is switched to the "disconnected" state, the dormant power supply is powered off, and all the onboard equipment are powered off at this time. 6. a kind of solid rocket wireless measurement, launch and control power supply and distribution and safety control system according to claim 1 is characterized as follows: The control battery grid-connected drive is a power drive signal sent by the arrow data link (5) to the distributor (3), which can directly drive the relay coil in the distributor (3). , drive the relay coil; when invalid, the output is open, and the relay coil is not driven; The control battery grid-connection command, the first control battery disconnection preparation command and the second control battery disconnection preparation command are command signals sent by the onboard computer (6) to the distributor (3), and can be driven after being amplified by the triode drive circuit The relay coil in the distributor (3), when valid, outputs the control power supply +, and drives the relay coil; when it is invalid, the output is open, and does not drive the relay coil. 7. A kind of solid rocket wireless measurement and control power supply and distribution and safety control system according to claim 1, is characterized in that: described distributor (3) comprises normally open relay A, normally open relay B, normally closed relay C, normally closed relay D, normally open relay E, normally closed relay F, normally closed relay G, the first transistor drive circuit, the second transistor drive circuit, the third transistor drive circuit, the first diode tube, the second diode and the third diode; each relay includes a control coil and an executive terminal; relay B is a backup relay; The first control battery power supply +, the second control battery power supply + pass through the first diode and the second diode, respectively, and then merged, and then divided into two channels: one through the relay C execution terminal and the output of the sleep control loop, and through the external sleep The control pin (4) is connected to the input of the sleep control loop and the execution end of the relay D, and finally connected to the sleep power supply +; the other way through the execution end of the relay A and the relay B in parallel is connected to the control power supply +; The control battery is connected to the grid and is connected to the control power ground through the relay A coil; Relay F is connected in parallel with the execution end of relay G and then connected in series with the coil of relay E, and then connected in parallel with the coils of relay B, relay C, and relay D; one end of the parallel circuit is connected to the control power supply +, and the other end is driven by the first triode. Connect to the control power ground; The control power supply + the execution terminal of relay E is connected to the control battery grid-connected command and the first transistor drive circuit respectively; The control power supply + is connected to the control power supply ground through the relay F coil and the second transistor drive circuit; the first control battery disconnection preparation command is connected to the second transistor drive circuit; The control power supply + is connected to the control power supply ground through the relay G coil and the third transistor drive circuit; the second control battery disconnection preparation command is connected to the third transistor drive circuit; Pyrotechnic battery control power supply + after passing through the third diode, it is directly connected to the initiating power supply +; the initiating power supply battery regulated power supply is directly connected to the initiating power supply ground. 8. A kind of solid rocket wireless measurement, launch, control, power supply, distribution and safety control system according to claim 1, characterized in that: the safety controller (2) comprises an MCU module, an RS-422 interface circuit, an optocoupler isolation Drive circuit, normally open relay H and normally open relay I; each relay includes a control coil and an execution terminal; The RS-422 interface command input from the outside is sent to the MCU module through the RS-422 interface circuit. After the MCU module parses the command, it sends the pyrotechnic battery power supply/control command to the optocoupler isolation drive circuit; The secondary power supply of the safety controller (2) + the relay I coil and the relay H coil connected in parallel, and the execution end of the optocoupler isolation drive circuit, are connected to the secondary power supply ground of the safety controller (2); Pyrotechnic battery power supply + after passing through the execution terminal of relay H, it is connected to the power supply control of the initiating power supply battery; after the power supply of the pyrotechnic product battery passes through the execution terminal of relay I, it is connected to the power supply ground of the inflammatory chemical product battery control. 9. a kind of solid rocket wireless measurement, launch and control power supply and distribution and safety control system according to claim 1, is characterized in that: The arrow-borne data link (5) uses the received dormant power supply and control power supply as a control battery for grid-connected drive; When the on-board data link (5) is powered on, it first enters the "low power consumption" mode, and operates with extremely low power consumption, so that the power stored in the control battery can provide the dormant power for the on-board data link (5) for a long time; In this mode, the arrow-borne data link (5) only receives wireless uplink command data, and enters the "full power" mode after receiving the "wake up" command; In the "full power" mode, the onboard data link (5) receives the wireless uplink command data, sends the wireless downlink telemetry data, and at the same time sends the control battery grid-connected drive to the power distributor (3), and sends it to the security control through the RS-422 interface. The device (2) and the onboard computer (6) forward the uplink instruction data. 10. A solid rocket wireless measurement, launch, control, power supply, distribution and safety control system according to claim 7, wherein the triode drive circuit comprises: a current limiting resistor R1, a resistor R2, a capacitor C1, a Zener diode T1 and NPN transistor Q1; The collector of the transistor Q1 is connected to the second interface, the emitter is connected to the third interface, the base is connected to the first interface through the current limiting resistor R1, and is connected to the emitter through the parallel resistor R2, capacitor C1, and Zener diode T1. ; The first interface is connected to the input command, the second interface is connected to the external relay coil, and the third interface is connected to the external power supply ground.

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