Aircraft, and fire extinguishing bomb control system and bomb-borne end detonation device thereof

Abstract

An aircraft, and a fire extinguishing bomb control system and a bomb-borne end detonation device thereof. The bomb-borne end detonation device comprises a power supply module (100), a communication module (200) and a detonation signal sending module (300), wherein the power supply module (100) is used for energizing the bomb-borne end detonation device; the communication module (200) comprises a timer, and the communication module (200) is used for forming a communication connection with an aircraft and starting a countdown of the timer when a first trigger condition is met; and the detonation signal sending module (300) is used for outputting a detonation current signal after the countdown of the timer ends when the power supply module (100) is in an energized state and a second trigger condition is met. The bomb-borne end detonation device detonates a fire extinguishing bomb by means of a multi-confirmation mechanism, thereby effectively avoiding a misoperation.

Description

Aircraft, fire extinguishing bomb control system and bomb-mounted detonating device Technical Field

[0001] The present application relates to the field of UAV firefighting technology, and in particular to an aircraft, a fire extinguishing bomb control system, and a bomb-borne detonating device thereof. Background Art

[0002] Currently, fire extinguishing bombs on the market are generally equipped with electronic fuses, 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 the gunpowder is surrounded by fire extinguishing materials. Electronic fuses are generally used to detonate the gunpowder to disperse the fire extinguishing materials 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.

[0003] Summary of the Invention

[0004] The purpose of the present application is to provide an aircraft, a fire extinguishing bomb control system and a bomb-borne detonating device thereof. The bomb-borne detonating device of the present application detonates the fire extinguishing bomb through a multiple confirmation mechanism, effectively preventing misoperation.

[0005] In order to solve the above technical problems, the present application provides a missile-borne detonating device, including: a power supply module, a communication module and a detonating signal sending module, the power supply module is used to power the missile-borne detonating device; the communication module includes a timer, the communication module is used to communicate with the aircraft and start the timer countdown when a first trigger condition is met; the detonating signal sending module is used to output a detonating current signal after the timer countdown ends when the power supply module is powered on and a second trigger condition is met.

[0006] The present application provides a fire extinguishing bomb control system, comprising the above-mentioned bomb-borne detonating device and an airborne device, wherein the bomb-borne detonating device is installed on the fire extinguishing bomb, and the airborne device 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 module.

[0007] The present application provides an aircraft, comprising the above-mentioned fire extinguishing bomb control system.

[0008] Optionally, the first trigger condition is when the communication module is disconnected from the aircraft.

[0009] Optionally, the communication module is connected to the aircraft via a communication interface line, and the first trigger condition is when the communication interface line is disconnected from the communication module.

[0010] Optionally, the detonation signal sending module is connected to a safety pin, and the second trigger condition is when the safety pin is disconnected from the detonation signal sending module.

[0011] Optionally, after the fire extinguishing bomb is released, the communication interface line and the safety pin are disconnected from the bomb-borne detonating device at the same time due to the gravity of the bomb.

[0012] Optionally, the power supply module includes a power switch, and the power supply module powers on or off the missile-borne detonation device by switching the gear position of the power switch.

[0013] Optionally, the airborne terminal device obtains the delayed detonation time value according to the current altitude of the aircraft and a preset detonation altitude value.

[0014] Optionally, the airborne terminal device includes a laser ranging module, and the current altitude of the aircraft is measured by the laser ranging module.

[0015] The bomb-mounted detonating device of the present application detonates the fire extinguishing bomb through a multiple confirmation mechanism, effectively preventing misoperation. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] FIG1 is a schematic diagram showing the unit structure of a missile-borne end detonator according to an embodiment of the present application;

[0017] FIG2 is a schematic diagram showing a unit structure of an airborne terminal device according to an embodiment of the present application;

[0018] FIG3 is a schematic diagram showing the unit structure of the fire extinguishing bomb control system according to an embodiment of the present application. DETAILED DESCRIPTION

[0019] The following embodiments further illustrate the technical solutions of the present application. It is understood that the specific embodiments described herein are merely for the purpose of explaining the present application. It should also be noted that, for ease of description, only portions relevant to the present application are shown in the accompanying drawings, not all of them.

[0020] In the description of this application, it should be noted that, unless otherwise specified or limited, the terms "mounted," "connected," and "connected" should be understood broadly. For example, they can refer to fixed or detachable connections; mechanical or electrical connections; direct or indirect connections through an intermediate medium; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in this application in specific contexts.

[0021] In this application, unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may include the first and second features being in direct contact, or may include the first and second features being in contact not directly but through another feature between them. Moreover, a first feature being "above," "above," and "above" a second feature may include the first feature being directly above or obliquely above the second feature, or may simply mean that the first feature is higher in level than the second feature. A first feature being "below," "below," and "below" a second feature may include the first feature being directly below or obliquely below the second feature, or may simply mean that the first feature is lower in level than the second feature.

[0022] The following describes embodiments of the present application with reference to the accompanying drawings. As shown in FIG1 , the present application provides a missile-mounted detonating device, which is mounted on the upper end of a fire-extinguishing bomb and is used to detonate the fire-extinguishing bomb dropped from an aircraft. The missile-mounted detonating device includes a power supply module 100, a communication module 200, and a detonation signal transmission module 300. The power supply module 100 is used to power the missile-mounted detonating device; the communication module 200 includes a timer, which is used to communicate with the aircraft and start the timer countdown when a first trigger condition is met; and the detonation signal transmission module 300 is used to output a detonation current signal after the timer countdown ends when the power supply module 100 is powered and a second trigger condition is met.

[0023] Specifically, the power supply module 100 includes a power switch, which switches the power supply module 100 on and off to power the onboard detonator. The power switch positions include, but are not limited to, ON and OFF. When the power switch is switched to ON, the onboard detonator is powered on; when the power switch is switched to OFF, the onboard detonator is powered off. When the fire extinguishing bomb is in transport or storage, the power switch can be switched to OFF to prevent accidental triggering of the detonator. The first trigger condition is when the communication module 200 is disconnected from the aircraft. Specifically, the communication module 200 is connected to the aircraft via a communication interface cable. One end of the communication interface cable plugs into the aircraft, and the other end plugs into the communication module 200. The communication interface cable is fixedly connected to the aircraft. After the fire extinguishing bomb is released, the gravity of the fire extinguishing bomb disconnects the communication interface cable from the communication module 200 of the onboard detonator. At this point, the communication module 200 starts a countdown timer.

[0024] Furthermore, the detonation signal transmission module 300 is connected to a safety pin, and the second trigger condition is when the safety pin is disconnected from the detonation signal transmission module 300. Specifically, when the power supply module 100 is powered on and the safety pin is disconnected from the detonation signal transmission module 300 of the onboard detonating device, the detonation signal transmission module 300 will only output the detonation current signal after the timer countdown ends. In other words, if the safety pin is not disconnected from the onboard detonating device, the detonation signal transmission module 300 cannot successfully output the detonation current signal, thereby preventing the fire extinguishing bomb from accidentally detonating. Preferably, after the fire extinguishing bomb is released, the communication interface cable and the safety pin are simultaneously disconnected from the onboard detonating device due to the force of gravity. Specifically, the communication interface cable and safety pin can be bundled and fastened to the aircraft. After the fire extinguishing bomb is released, the communication interface cable and safety pin are simultaneously separated from the onboard detonator by gravity. The communication module 200 then starts a timer countdown and outputs a detonation current signal at the end of the timer countdown, successfully detonating the fire extinguishing bomb at a preset altitude. This mechanical triggering condition eliminates the need for an electronic fuse consisting of numerous electronic components and circuits, resulting in improved reliability.

[0025] The airborne terminal device obtains the delayed detonation time value based on the current altitude of the aircraft and the preset detonation altitude value. Specifically, as shown in Figure 2, the airborne terminal device 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 altitude value from the current altitude of the aircraft is the height displacement difference Δh caused by the free fall of the fire extinguishing bomb under the action of gravity during the delayed detonation time. Based on this, the delayed detonation time value is calculated based on the gravity acceleration g of the fire extinguishing bomb.

[0026] It should be noted that the recommended detonation height for water-based fire extinguishing bombs is no less than 6 meters; the recommended detonation height for dry powder fire extinguishing bombs is no less than 8 meters, so as to achieve the best fire extinguishing effect.

[0027] In other embodiments, the preset detonation height value can also be manually set remotely on a control panel corresponding to the airborne terminal device. The control panel can be manually adjusted using the "+" and "-" buttons.

[0028] The bomb-mounted detonating device of the present application detonates the fire extinguishing bomb through a multiple confirmation mechanism, effectively preventing misoperation.

[0029] The present application provides a fire extinguishing bomb control system, as shown in FIG3 , comprising the aforementioned onboard detonator and an onboard device. The onboard detonator is mounted on top of the fire extinguishing bomb, while the onboard device is mounted on an aircraft and is used to set a delayed detonation time value, thereby determining the countdown of the timer of the communication module 200. The onboard detonator of the fire extinguishing bomb control system of the present application uses a multiple confirmation mechanism to detonate the fire extinguishing bomb, effectively preventing misoperation.

[0030] The present application provides an aircraft, including the fire extinguishing bomb control system described above. The onboard detonator of the fire extinguishing bomb control system of the aircraft of the present application detonates the fire extinguishing bomb through a multiple confirmation mechanism, effectively preventing misoperation.

[0031] The above embodiments are merely illustrative of the principles and effects of this application. Anyone skilled in the art may modify or alter the above embodiments without departing from the objectives of this application. Therefore, all equivalent modifications or alterations made by persons skilled in the art without departing from the objectives disclosed herein are intended to be covered by the claims of this application.

Claims

1. A bomb-mounted detonating device, used to detonate a fire-extinguishing bomb dropped from an aircraft, characterized in that: include: A power supply module (100), a communication module (200) and a detonation signal sending module (300), wherein the power supply module (100) is used to power on the missile-borne detonation device; the communication module (200) comprises a timer, and the communication module (200) is used to communicate with the aircraft and start the countdown of the timer when a first trigger condition is met; and the detonation signal sending module (300) is used to output a detonation current signal after the countdown of the timer ends when the power supply module (100) is powered on and a second trigger condition is met.

2. The missile-borne end detonation device according to claim 1, characterized in that: The first trigger condition is when the communication module (200) is disconnected from the aircraft.

3. The missile-borne end detonation device according to claim 1, characterized in that: The communication module (200) is connected to the aircraft via a communication interface line, and the first trigger condition is when the communication interface line is disconnected from the communication module (200).

4. The missile-borne end detonation device according to claim 3, characterized in that: The detonation signal sending module (300) is connected to a safety pin, and the second trigger condition is when the safety pin is disconnected from the detonation signal sending module (300).

5. The missile-borne end detonation device according to claim 4, characterized in that: After the fire extinguishing bomb is released, the communication interface line and the safety pin are disconnected from the bomb-carrying end detonating device at the same time under the action of its gravity.

6. The missile-borne end detonation device according to claim 1, characterized in that: The power supply module (100) comprises a power switch, and the power supply module (100) switches the gear position of the power switch to power on or off the bomb-borne detonation device.

7. A fire extinguishing bomb control system, characterized in that: It comprises a missile-borne detonating device as described in any one of claims 1 to 6, and an airborne device, wherein the missile-borne detonating device is installed on the fire extinguishing bomb, and the airborne device 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 module (200).

8. The fire extinguishing bomb control system according to claim 7, characterized in that: The airborne device obtains the delayed detonation time value according to the current altitude of the aircraft and a preset detonation altitude value.

9. The fire extinguishing bomb control system according to claim 7, characterized in that: The airborne terminal device comprises a laser ranging module (400), and the current altitude of the aircraft is measured by the laser ranging module (400).

10. An aircraft, characterized in that: It comprises a fire extinguishing bomb control system as described in any one of claims 7 to 9.

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