An electronic delay system for rockets

Abstract

The present application discloses an electronic delay system for rockets, and relates to the field of rocket delay devices. The electronic delay system comprises: a host human-machine interaction interface, a host control panel, and an electronic delay module connected in sequence; the host human-machine interaction interface and the electronic delay module perform data exchange through the host control panel; the host human-machine interaction interface is used to power the electronic delay module, and to set and calibrate the delay time of the electronic delay module. The present application can control the delay time of the electronic delay module with high delay accuracy.

Description

Technical Field

[0001] The present application relates to the field of rocket delay devices, and in particular to an electronic delay system for rockets. Background Art

[0002] Traditional rain-making and hail-prevention rockets, fire-extinguishing rockets, etc., use delay bodies (pyrotechnics) or traditional pyrotechnic delay devices, which have no communication and the delay is fixed and cannot be set.

[0003] When launching traditional rain-increasing and hail-prevention rockets and fire-extinguishing rockets, the ignition bridge wires of each delay device are ignited at the same time, causing the delay body to burn. After the delay device burns to the high explosive, the real ignition of the cabin is triggered. However, due to the influence of objective factors such as processing technology, altitude, temperature, humidity, and oxygen content, the delay error of the delay body will be relatively large.

[0004] Since there are almost no electronic components inside the timer of traditional rain-making and hail-prevention rockets and fire-extinguishing rockets, the ignition bridge wire is directly connected to the host control board. However, there is no communication between the timer and the host control board, so the host control board cannot know the delay and status of the timer, and there is no way to set the delay of the timer online. For the timer to trigger ignition, the host control board usually needs to increase the voltage to a certain level, and then connect the timer to trigger the delay ignition, which has very low controllability. Summary of the invention

[0005] In order to solve the above problems, the present application provides an electronic delay system for rockets.

[0006] To achieve the above-mentioned objectives, the present application provides an electronic delay system for rockets, comprising a host human-computer interaction interface, a host control panel and an electronic delay module connected in sequence; the host human-computer interaction interface and the electronic delay module exchange data through the host control panel; the host human-computer interaction interface is used to power the electronic delay module, and to set and calibrate the delay time of the electronic delay module.

[0007] Optionally, there are multiple electronic delay modules, and the multiple electronic delay modules are arranged in parallel in the compartment of the rocket.

[0008] Optionally, each of the electronic delay modules is provided with a corresponding ID.

[0009] Optionally, the host control board is used to obtain the ID, delay time and online number of the electronic delay module, and report to the host human-computer interaction interface through the RS232 interface.

[0010] Optionally, the electronic delay module includes: a 2-core input line, an energy storage capacitor, a PCBA board and a 2-core output line; the 2-core input line is connected to the host control board, and the 2-core output line is connected to the cabin site gunpowder head of the rocket;

[0011] When the electronic delay module is connected to the host control board, the energy storage capacitor is used to store electrical energy; when the electronic delay module is disconnected from the host control board, the energy storage capacitor is used to supply power to the electronic delay module.

[0012] Optionally, a rectifier bridge stack, a protection circuit, a transceiver communication circuit, a single-chip microcomputer, a bridge wire detection circuit and an ignition control circuit are arranged on the PCBA board; one end of the rectifier bridge stack is connected to the 2-core input line, the other end of the rectifier bridge stack is connected to one end of the protection circuit, the other end of the protection circuit is connected to one end of the transceiver communication circuit, the other end of the transceiver communication circuit is connected to the single-chip microcomputer, the energy storage capacitor is connected to one end of the ignition control circuit, and the other end of the ignition control circuit and the bridge wire detection circuit are both connected to the single-chip microcomputer.

[0013] Optionally, when the host control board transmits the ignition command sent by the host human-computer interaction interface to the electronic control module, the single-chip microcomputer enters the power consumption mode timing, and after the timing reaches the delay time, the ignition bridge wire is ignited through the ignition control circuit and the energy storage capacitor.

[0014] Optionally, the protection circuit includes a static suppression diode, a voltage regulator diode and a fuse connected in sequence.

[0015] Optionally, an LDO power supply circuit is further provided on the PCBA board, one end of the LDO power supply circuit is connected to the other end of the protection circuit, and the other end of the LDO power supply circuit is connected to the single-chip microcomputer.

[0016] Optionally, the PCBA board is prepared by a double-sided PCB board patch process.

[0017] According to the specific embodiments provided in this application, this application has the following technical effects:

[0018] The electronic delay system for rockets provided in the present application has a host human-computer interaction interface and an electronic delay module that exchanges data through a host control panel. The delay time and status of the electronic delay module can be confirmed in real time, and the delay time of the electronic delay module can be set and calibrated online, so that the delay accuracy of the electronic delay module is high and controllable. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0020] Figure 1 A schematic diagram of the structure of an electronic delay system for a rocket provided in one embodiment of the present application;

[0021] Figure 2 It is a structural diagram of the electronic delay module;

[0022] Figure 3 This is a schematic diagram of the circuit structure of the electronic delay module. DETAILED DESCRIPTION

[0023] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0024] In order to make the above-mentioned objects, features and advantages of the present application more obvious and easy to understand, the present application is further described in detail below in conjunction with the accompanying drawings and specific implementation methods.

[0025] In an exemplary embodiment, Figure 1 As shown, an electronic delay system for rockets is provided, comprising a host human-machine interaction interface 1, a host control board 2 and an electronic delay module 3 connected in sequence; the host human-machine interaction interface 1 and the electronic delay module 3 perform data exchange with each other through the host control board 2; the host human-machine interaction interface 1 is used to power the electronic delay module 3, and to set and calibrate the delay time of the electronic delay module 3.

[0026] A rocket usually includes multiple electronic delay modules 3. In this embodiment, 6 electronic delay modules 3 are provided, and each electronic delay module 3 is provided with a corresponding ID. The electronic delay module 3 is installed in each compartment of the rocket, such as the launch compartment, the medicine compartment, and the parachute compartment. Multiple electronic delay modules are arranged in parallel in the compartment of the rocket, and the electronic delay modules in each compartment are connected in parallel inside the rocket to two contacts outside the rocket. When the rocket is in use, the two external contacts of the rocket are connected to the contacts of the rocket launcher, and the contacts of the rocket launcher are connected to the host control board 2.

[0027] In a specific embodiment, the host human-machine interaction interface 1 is connected to the host control board 2 via an RS232 interface to control the host control board 2. The host control board 2 uses a 24V DC power supply provided by the host human-machine interaction interface 1.

[0028] The host human-machine interaction interface 1 is set according to customer needs, and can be but not limited to a computer client operating system, a single-chip computer system, a programmable control system, etc. The host human-machine interaction interface 1 at least includes control buttons such as detection and ignition, and at least includes an indication display of whether the detection is normal or not.

[0029] The host human-machine interaction interface 1 generally includes an LCD display, indicator lights and buttons. The LCD display can show whether the detection is normal, the ID of the electronic delay module 3, the delay time, and the number of online electronic delay modules 3. The indicator lights indicate the working status, power status, etc., and the buttons realize the delay time change, communication detection, data acquisition and ignition of the electronic delay module 3.

[0030] The host control board 2 receives command control from the host human-machine interface 1 through the RS232 interface to realize data interaction. The host control board 2 inputs a 24V DC power supply, which is converted to power the host control board 2 through a step-down voltage regulator circuit. The output line of the host control board 2 is connected to the electronic delay module 3. The output line of the host control board 2 has voltage output control function, current detection function and communication function. If the line is abnormal, the host control board 2 will switch the output line and report the abnormality through the RS232 interface. If the line is normal, the host control board 2 will communicate with the electronic delay module 3, obtain the ID, delay time and number of online electronic delay modules of the electronic delay module 3 in each cabin, and report it to the host human-machine interaction interface 1 through the RS232 interface.

[0031] In a specific embodiment, Figure 2 As shown, the electronic delay module includes a 2-core input line 31, an energy storage capacitor 32, a PCBA board 33 and a 2-core output line 34. The 2-core input line 31 is connected to the host control board 2, and the 2-core output line 34 is connected to the cabin site gunpowder head of the rocket; when the electronic delay module 3 is connected to the host control board 2, the energy storage capacitor 32 is used to store electrical energy, and when the electronic delay module 3 is disconnected from the host control board 2, the energy storage capacitor 32 is used to power the electronic delay module 3.

[0032] like Figure 3As shown, a rectifier bridge stack, a protection circuit, a transceiver communication circuit, a single-chip microcomputer, a bridge wire detection circuit and an ignition control circuit are arranged on the PCBA board 33. One end of the rectifier bridge stack is connected to the 2-core input line 31, the other end of the rectifier bridge stack is connected to one end of the protection circuit, the other end of the protection circuit is connected to one end of the transceiver communication circuit, the other end of the transceiver communication circuit is connected to the single-chip microcomputer, the energy storage capacitor 32 is connected to one end of the ignition control circuit, and the other end of the ignition control circuit and the bridge wire detection circuit are connected to the single-chip microcomputer. An LDO power supply circuit is also arranged on the PCBA board 33, one end of the LDO power supply circuit is connected to the other end of the protection circuit, and the other end of the LDO power supply circuit is connected to the single-chip microcomputer.

[0033] In this embodiment, the PCBA board 33 is prepared by a double-sided PCB board patch process. Except for the energy storage capacitor 32, other components are soldered on the PCB board through SMT patches. After the patch is completed, the input and output line soldering points and the energy storage capacitor soldering points of the PCBA board 33 are left for post-welding. The electronic delay module 3 is encapsulated by a plastic mold. Except for the input and output line soldering points and the energy storage capacitor soldering points of the PCBA board 33, all other circuit components are protected by encapsulation. The PCBA board 33 is encapsulated in the center, and the encapsulation size is designed according to the plastic mold design matching the assembly size of the rocket body, and assembled at the ignition position of each cabin of the rocket.

[0034] The electronic delay module 3 is a slave device, which communicates with the host control board 2 through a 2-core input line 31. The single-chip microcomputer inside the electronic delay module 3 realizes half-duplex communication with the host control board 2 through a transceiver communication circuit, and realizes delayed download, networking detection, ignition command reception, etc. The main functions of the electronic delay module 3 are power-off storage, power-off energy storage and delay switch. One of the reasons why the electronic delay module 3 gradually replaces traditional pyrotechnics is that traditional pyrotechnics do not have a numbering traceability function. The electronic delay module 3 can not only store the ID through the power-off storage function, but also program the delay time of the electronic delay module, and store the delay time power-off in the interior of the electronic delay module, which has traceable, programmable and detectable effects. The power-off energy storage function is realized by the energy storage capacitor 32, which can ensure that the rocket continues to work after being disconnected from the power supply. The delay switch is the basic function of the electronic delay module 3. Each cabin needs to ignite after reaching the set delay time, so as to ensure the normal operation of the rocket.

[0035] In this embodiment, the electronic delay module 3 is powered and communicated by a 2-core input line 31. Since the electronic delay module 3 is equipped with a rectifier bridge, the 2-core input line 31 can be connected without distinguishing between positive and negative poles. The electronic delay module 3 is connected to the ignition head by a 2-core output line 34. The ignition head is a pyrotechnic component after the ignition powder is wrapped by an ignition bridge wire. The ignition bridge wire does not distinguish between positive and negative poles, so the 2-core output line 34 does not distinguish between positive and negative poles.

[0036] In this embodiment, the electronic delay module 3 can realize protection against mis-ignition input. The electronic delay module 3 is provided with a protection circuit, which includes a fuse, a voltage-stabilizing diode and a static suppression diode. When the input voltage and static electricity exceed the static suppression diode and the voltage-stabilizing diode, the current increases, and the fuse at the front end of the 2-core input line 31 will be burned, thereby completely disconnecting the circuit at the rear end, thereby avoiding mis-ignition of the ignition bridge wire caused by high-voltage breakdown.

[0037] In this embodiment, the electronic delay module 3 is provided with an LDO power supply circuit, and the input wide voltage 7V-28V is stepped down to 5V voltage through the LDO power supply circuit to power the single chip microcomputer.

[0038] In this embodiment, the electronic delay module 3 has an ignition bridge wire detection function, which can detect whether the ignition bridge wire is broken. After the electronic delay module 3 is powered on, a slight current will flow through the ignition bridge wire. The bridge wire detection circuit detects through the input port of the single-chip microcomputer in the electronic delay module 3. When the ignition bridge wire is broken, the input port of the single-chip microcomputer will be suspended, resulting in a change in the input port signal. The bridge wire detection circuit determines that the bridge wire is broken, and the electronic delay module 3 stops working and cannot communicate with the host control board 2.

[0039] In this embodiment, the communication of the electronic delay module 3 is on the same line as the power supply. When the host control board 2 supplies power to the electronic delay module 3, the electronic delay module 3 is powered, and the rectifier bridge stack can place the electric energy stored in the energy storage capacitor 32 to output it in reverse to the 2-core input line 31 of the electronic delay module 3. When the host control board 2 needs to communicate with the electronic delay module 3, the waveform output is achieved by lowering and raising the voltage of the 2-core input line 31 to achieve the purpose of sending the ignition command. After the host control board 2 sends the ignition command, the transceiver communication circuit switches to the receiving state. When the electronic delay module 3 needs to reply data to the host control board 2, the 2-core input line 31 is lowered to change the current to achieve data transmission, and the transceiver communication circuit switches to the sending state.

[0040] In the present embodiment, when the electronic delay module 3 is normally connected to the host control board 2 for power supply, the energy storage capacitor 32 is fully charged, and its electric quantity supports the electronic delay module 3 to communicate with the host control board 2. Under normal conditions, the single-chip microcomputer of the electronic delay module 3 is in a relatively large power consumption state for operation. If the rocket launch is cancelled, the electric quantity of the energy storage capacitor 32 will be gradually emptied. When the host control board 2 transmits the ignition command sent by the host human-machine interaction interface 1 to the electronic control module 3, the single-chip microcomputer of the electronic delay module 3 enters the super low power consumption mode (current is only 6uA) for timing. At this time, even if the electronic delay module 3 is separated from the host control board 2, the energy of the energy storage capacitor 32 can support the electronic delay module 3 to continue to work. After the timing reaches the delay time, the ignition bridge wire is ignited through the ignition control circuit and the energy storage capacitor 32.

[0041] The workflow of the electronic delay system for rockets provided by this application is as follows:

[0042] Step 1: When the electronic delay module 3 is produced, a non-repeating ID and a default delay time are injected.

[0043] Step 2: The electronic delay module 3 is assembled into each compartment of the rocket and connected in parallel to the trigger interface for communication detection.

[0044] Step 3: The host human-machine interface 1 connects to the trigger point of the rocket through the host control panel 2 for communication detection, and obtains the ID and delay time of the electronic delay module 3. If the cabin delay needs to be changed, change the cabin delay time through the host human-machine interface 1.

[0045] Step 4: The host human-machine interaction interface 1 operates the ignition and sends the ignition command through the host control panel 2.

[0046] Step 5: When the rocket receives the ignition command, the electronic delay module 3 in the rocket launch cabin ignites immediately, and the rocket is launched. At this time, the 2-core input line 31 is disconnected, and the electronic delay modules 3 in other cabins will be powered by the energy storage capacitor 32.

[0047] Step 6: After the delay time of the electronic delay module 3 in the rocket ammunition compartment is up, the rocket ammunition compartment opens.

[0048] Step 7: The rocket continues to rise to a certain height and then lands. When the delay time of the electronic delay module 3 in the rocket parachute cabin is up, the ignition bridge wire is ignited through the ignition control circuit and the energy storage capacitor 32, and the rocket parachute cabin opens.

[0049] Step 8: After the rocket parachute compartment opens, the rocket warhead slowly descends to the ground through a parachute, and the entire process of the rocket is completed.

[0050] The electronic delay system for rockets provided in the present application is designed with electronic technology, which can not only realize functions such as communication, delay setting, numbering, and detection, but also only requires 2 wires (2-core input line) to realize the communication and ignition energy supply of the electronic delay module.

[0051] The technical features of the above embodiments may be arbitrarily combined. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0052] This article uses specific examples to illustrate the principles and implementation methods of this application. The description of the above embodiments is only used to help understand the method and core ideas of this application. At the same time, for those skilled in the art, according to the ideas of this application, there will be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as limiting this application.

Claims

1. An electronic delay system for rockets, characterized in that: include: The host human-machine interaction interface, host control panel and electronic delay module are connected in sequence; The host human-machine interaction interface exchanges data with the electronic delay module through the host control panel; the host human-machine interaction interface is used to supply power to the electronic delay module, and to set and calibrate the delay time of the electronic delay module.

2. The electronic delay system for rockets according to claim 1, characterized in that: There are multiple electronic delay modules, and the multiple electronic delay modules are arranged in parallel in the cabin of the rocket.

3. The electronic delay system for rockets according to claim 2, characterized in that: Each of the electronic delay modules is provided with a corresponding ID.

4. The electronic delay system for rockets according to claim 3, characterized in that: The host control panel is used to obtain the ID, delay time and online number of the electronic delay module, and report to the host human-computer interaction interface through the RS232 interface.

5. The electronic delay system for rockets according to claim 1, characterized in that: The electronic delay module includes: a 2-core input line, an energy storage capacitor, a PCBA board and a 2-core output line; the 2-core input line is connected to the host control board, and the 2-core output line is connected to the rocket's cabin site gunpowder head; When the electronic delay module is connected to the host control board, the energy storage capacitor is used to store electrical energy; when the electronic delay module is disconnected from the host control board, the energy storage capacitor is used to supply power to the electronic delay module.

6. The electronic delay system for rockets according to claim 5, characterized in that: A rectifier bridge stack, a protection circuit, a transceiver communication circuit, a single-chip microcomputer, a bridge wire detection circuit and an ignition control circuit are arranged on the PCBA board; one end of the rectifier bridge stack is connected to the 2-core input line, the other end of the rectifier bridge stack is connected to one end of the protection circuit, the other end of the protection circuit is connected to one end of the transceiver communication circuit, the other end of the transceiver communication circuit is connected to the single-chip microcomputer, the energy storage capacitor is connected to one end of the ignition control circuit, and the other end of the ignition control circuit and the bridge wire detection circuit are both connected to the single-chip microcomputer.

7. The electronic delay system for rockets according to claim 6, characterized in that: When the host control board transmits the ignition command sent by the host human-machine interaction interface to the electronic control module, the single-chip microcomputer enters a low-power mode for timing. After the timing reaches the delay time, the ignition bridge wire is ignited through the ignition control circuit and the energy storage capacitor.

8. The electronic delay system for rockets according to claim 6, characterized in that: The protection circuit comprises a static suppression diode, a voltage regulator diode and a fuse which are connected in sequence.

9. The electronic delay system for rockets according to claim 6, characterized in that: The PCBA board is also provided with an LDO power supply circuit, one end of the LDO power supply circuit is connected to the other end of the protection circuit, and the other end of the LDO power supply circuit is connected to the single-chip microcomputer.

10. The electronic delay system for rockets according to claim 6, characterized in that: The PCBA board is prepared by using a double-sided PCB board patch process.

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