Fire extinguishing bomb detonation method
By using a multiple confirmation mechanism detonation method in the fire extinguishing bomb, the mechanical disconnection of the timer and the safety pin is used to solve the problem of high risk of misoperation of the fire extinguishing bomb, and higher safety and reliability are achieved.
Patent Information
- Application Number
- CN202310744056.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2023-06-21
- Publication Date
- 2024-12-24
AI Technical Summary
Existing firefighters are prone to accidentally triggering electronic fuses during transportation and loading, resulting in high risk of misoperation.
The detonation method using a multiple confirmation mechanism includes an electronic supply module, a communication submodule and an output submodule. The mechanical disconnection of the timer and the safety pin is ensured to ensure the reliable output of the detonation signal and prevent misoperation.
It effectively prevents the misoperation of fire-extinguishing bombs, improves safety, and improves the reliability of the system by reducing dependence on electronic devices.
Smart Images
Figure CN119174891A_ABST
Abstract
Description
Technical Field
[0001] The present application relates to the field of drone firefighting technology, and in particular to a method for detonating a fire extinguishing bomb. Background Art
[0002] At present, the fire extinguishing bombs on the market are generally equipped with an electronic fuse, and a delay module is configured in the electronic fuse circuit. There are two elastic conductive plates in the electronic fuse circuit, and an insulating plate is inserted between the two conductive plates. A pull ring is connected to the insulating plate. After the pull ring is pulled out, the electronic fuse is turned on and detonated. There is a small amount of gunpowder around the electronic fuse, and there is fire extinguishing material around the gunpowder. Electronic fuses are generally used to detonate the gunpowder to disperse the fire extinguishing material around it. However, there are loopholes in the existing safety mechanism of fire extinguishing bombs, and the electronic fuse may be accidentally triggered during transportation and loading. Summary of the invention
[0003] The purpose of the present application is to provide a method for detonating a fire extinguishing bomb. The method for detonating a fire extinguishing bomb of the present application detonates the fire extinguishing bomb through a multiple confirmation mechanism, thereby effectively preventing misoperation.
[0004] In order to solve the above-mentioned technical problems, the present application provides a method for detonating a fire extinguishing bomb, which is applied to a bomb-borne end module of a fire extinguishing bomb, and the fire extinguishing bomb is installed on an aircraft, and is characterized in that the bomb-borne end module includes a power supply submodule, a communication submodule and an output submodule, and the communication submodule includes a timer. The detonation method includes: S1: order the power supply submodule to power on the bomb-borne end module; S2: order the communication submodule to start the countdown of the timer when the first detonation condition is triggered; S3: when the second detonation condition is triggered and the countdown of the timer ends, order the output submodule to output a detonation signal.
[0005] Optionally, the first detonation condition is when the communication submodule is disconnected from the aircraft, and the step S2 specifically includes: enabling the communication submodule to start the countdown of the timer when it is disconnected from the aircraft.
[0006] Optionally, the communication submodule is connected to the aircraft via a communication line, and the step S2 specifically includes: instructing the communication submodule to start the countdown of the timer when the communication line is disconnected from the communication submodule.
[0007] Optionally, the output submodule is connected to a safety pin, and the second detonation condition is when the safety pin is disconnected from the output submodule, and the step S3 specifically includes: when the safety pin is disconnected from the output submodule and the timer countdown ends, causing the output submodule to output a detonation signal.
[0008] Optionally, after the fire extinguishing bomb is released, the communication line and the safety pin are disconnected from the bomb-borne end module respectively and simultaneously under the action of gravity.
[0009] Optionally, the power supply submodule includes a power switch, and the step S1 specifically includes: enabling the power supply submodule to power on the missile-mounted end module by switching the gear position of the power switch.
[0010] Optionally, the fire extinguishing bomb control system applied to an aircraft comprises the above-mentioned bomb-borne end module and an airborne end module, the bomb-borne end module is installed on the fire extinguishing bomb, and the airborne end module is installed on the aircraft and is used to set a delayed detonation time value, thereby determining the countdown of the timer of the communication submodule.
[0011] Optionally, the delayed detonation time value is calculated based on the current altitude of the aircraft and a preset detonation altitude value.
[0012]
[0013] Detonation height value, g is the acceleration due to gravity.
[0014] Optionally, the airborne terminal module includes a laser ranging module, and the current altitude of the aircraft is measured by the laser ranging module.
[0015] The fire extinguishing bomb detonation method of the present application detonates the fire extinguishing bomb through a multiple confirmation mechanism, thereby effectively preventing misoperation. BRIEF DESCRIPTION OF THE DRAWINGS
[0016] Figure 1 Shown is a schematic diagram of the process of detonating a fire extinguishing bomb according to an embodiment of the present application;
[0017] Figure 2 Shown is a schematic diagram of the unit structure of the missile-mounted end module of an embodiment of the present application;
[0018] Figure 3 Shown is a schematic diagram of the unit structure of the airborne terminal module of an embodiment of the present application;
[0019] Figure 4 Shown is a schematic diagram of the unit structure of the fire extinguishing bomb control system of an embodiment of the present application. DETAILED DESCRIPTION
[0020] The following embodiments further illustrate the technical solution of the present application. It is to be understood that the specific embodiments described herein are only used to explain the present application. It should also be noted that, for ease of description, only the parts related to the present application are shown in the drawings, not all.
[0021] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.
[0022] In the present application, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.
[0023] like Figure 1 As shown, the method for detonating a fire extinguishing bomb in an embodiment of the present application includes the following steps:
[0024] S1: The power supply module supplies power to the missile-mounted module.
[0025] like Figure 2 As shown, the present application provides a missile-borne end module, which is installed at the upper end of the fire-extinguishing bomb and is used to detonate the fire-extinguishing bomb dropped by the aircraft. The missile-borne end module includes: a power supply submodule 100, a communication submodule 200 and an output submodule 300, and the power supply submodule 100 is used to power the missile-borne end module.
[0026] Specifically, the power supply submodule 100 includes a power switch, which enables the power supply submodule 100 to power on or off the missile-borne module by switching the gear position of the power switch. The gear position of the power switch includes but is not limited to ON and OFF. When it is necessary to prepare for detonation, the power switch is switched to the gear position ON, and the missile-borne module is powered on. When the fire extinguishing bomb is in a transportation or storage state, the power switch gear position can be set to OFF to prevent the detonation device from being accidentally triggered.
[0027] S2: Instruct the communication submodule to start the timer countdown when the first detonation condition is triggered.
[0028] The communication submodule 200 includes a timer, which enables the communication submodule 200 to be connected to the aircraft for communication and starts the timer countdown when the first detonation condition is triggered. The first detonation condition is when the communication submodule 200 is disconnected from the aircraft. Specifically, the communication submodule 200 is connected to the aircraft through a communication line, one end of the communication line is plugged into the aircraft, and the other end is plugged into the communication submodule 200, and the communication line is fixedly connected to the aircraft. When the fire extinguishing bomb is dropped, the communication line is disconnected from the communication submodule 200 due to the gravity of the fire extinguishing bomb, and the communication submodule 200 starts the timer countdown.
[0029] S3: When the second detonation condition is triggered and the timer countdown ends, the output submodule outputs a detonation signal
[0030] When the power supply submodule 100 is powered on, after the second detonation condition is triggered and the timer countdown ends, the output submodule 300 is made to output a detonation signal. Specifically, the output submodule 300 is connected to a safety pin, and the second detonation condition is when the safety pin is disconnected from the output submodule 300. Specifically, when the power supply submodule 100 is powered on and the safety pin is disconnected from the output submodule 300 of the bomb-borne end module, after the timer countdown ends, the output submodule 300 is made to output a detonation signal. In other words, when the safety pin is not separated from the bomb-borne end module, the explosion signal sending module 300 cannot successfully output the detonation signal, thereby preventing the fire extinguishing bomb from accidentally exploding. Preferably, the communication line and the safety pin are disconnected from the bomb-borne end module at the same time under the action of gravity after the fire extinguishing bomb is released. Specifically, the communication line and the safety pin can be bundled and fastened to the aircraft. After the fire extinguishing bomb is dropped, the communication line and the safety pin are separated from the bomb-carrying end module under the action of its gravity. The communication submodule 200 starts the timer countdown and outputs a detonation signal at the end of the timer countdown, thereby successfully detonating the fire extinguishing bomb at a preset height. The detonation signal is sent by this mechanical trigger condition, without relying on an electronic fuse composed of a large number of electronic devices and circuits, and has better reliability.
[0031] The airborne module obtains the delayed detonation time value according to the current altitude of the aircraft and the preset detonation altitude value. Figure 3 As shown, the airborne module includes a laser ranging module 400, and the current altitude of the aircraft is measured by the laser ranging module 400. The height difference obtained by subtracting the preset detonation height value from the current altitude of the aircraft is the height displacement difference caused by the fire extinguishing bomb falling freely under the action of gravity within the delayed detonation time. Based on the gravity acceleration g of the fire extinguishing bomb, the delayed detonation time value is calculated. Where H is the current altitude of the aircraft, and h is the preset detonation altitude value.
[0032] It should be noted that the recommended detonation height for water-based fire extinguishing bombs is not less than 6 meters; the recommended detonation height for dry powder fire extinguishing bombs is not less than 8 meters, so as to achieve the best fire extinguishing effect.
[0033] In other embodiments, the preset detonation height value can also be manually set remotely on a control panel corresponding to the airborne module. The control panel can be manually adjusted and set through the "+" and "-" buttons to cope with certain special situations.
[0034] The fire extinguishing bomb detonation method of the present application detonates the fire extinguishing bomb through a multiple confirmation mechanism, which can effectively prevent misoperation. The communication line and the safety pin are disconnected from the bomb-carrying end module at the same time under the action of gravity after the fire extinguishing bomb is dropped, and the detonation signal is sent by this mechanical trigger condition, without relying on an electronic fuse composed of a large number of electronic devices and circuits, and the reliability is better.
[0035] The above embodiments are merely illustrative of the principles and effects of the present application. Anyone familiar with the technology may modify or change the above embodiments without violating the purpose of the present application. Therefore, all equivalent modifications or changes made by a person with ordinary knowledge in the relevant technical field without departing from the purpose disclosed in the present application shall still be covered by the claims of the present application.
Claims
1. A method for detonating a fire extinguishing bomb, applied to a bomb-carrying end module of a fire extinguishing bomb, wherein the fire extinguishing bomb is installed on an aircraft, characterized in that: The missile-borne end module comprises a power supply submodule (100), a communication submodule (200) and an output submodule (300), wherein the communication submodule (200) comprises a timer, and the detonation method comprises: S1: enabling the power supply submodule (100) to power on the missile-borne end module; S2: enabling the communication submodule (200) to start the countdown of the timer when a first detonation condition is triggered; and S3: enabling the output submodule (300) to output a detonation signal when a second detonation condition is triggered and the countdown of the timer ends.
2. The method for detonating a fire extinguishing bomb according to claim 1, characterized in that: The first detonation condition is when the communication submodule (200) is disconnected from the aircraft, and the step S2 specifically comprises: causing the communication submodule (200) to start the countdown of the timer when it is disconnected from the aircraft.
3. The method for detonating a fire extinguishing bomb according to claim 1, characterized in that: The communication submodule (200) is connected to the aircraft via a communication line, and the step S2 specifically comprises: instructing the communication submodule (200) to start the countdown of the timer when the communication line is disconnected from the communication submodule (200).
4. The method for detonating a fire extinguishing bomb according to claim 3, characterized in that: The output submodule (300) is connected to a safety pin, and the second detonation condition is when the safety pin is disconnected from the output submodule (300). The step S3 specifically comprises: when the safety pin is disconnected from the output submodule (300) and the countdown of the timer ends, causing the output submodule (300) to output a detonation signal.
5. The method for detonating a fire extinguishing bomb according to claim 4, characterized in that: After the fire extinguishing bomb is dropped, the communication line and the safety pin are disconnected from the bomb-borne end module simultaneously under the action of its gravity.
6. The method for detonating a fire extinguishing bomb according to claim 1, characterized in that: The power supply submodule (100) comprises a power switch, and the step S1 specifically comprises: enabling the power supply submodule (100) to power on the missile-mounted end module by switching the gear position of the power switch.
7. The fire extinguishing bomb detonation method according to claim 1 is applied to a fire extinguishing bomb control system of an aircraft, wherein the fire extinguishing bomb control system comprises a bomb-borne end module according to any one of claims 1 to 6, and an airborne end module, wherein the bomb-borne end module is installed on the fire extinguishing bomb, and the airborne end module is installed on the aircraft and is used to set a delayed detonation time value, thereby determining the countdown of the timer of the communication submodule (200).
8. The method for detonating a fire extinguishing bomb according to claim 7, characterized in that: The delayed detonation time value is calculated based on the current altitude of the aircraft and a preset detonation altitude value.
9. The method for detonating a fire extinguishing bomb according to claim 8, characterized in that: The delayed detonation time value Where H is the current altitude of the aircraft, h is the preset detonation altitude value, and g is the gravitational acceleration.
10. The method for detonating a fire extinguishing bomb according to claim 9, characterized in that: The airborne end module comprises a laser ranging module (400), and the current altitude of the aircraft is measured by the laser ranging module (400).