A safety control system and control method for an airship based on thermal fuses

Abstract

This invention provides a safety control system and control method for an airship based on a thermal fuse. The system includes: an emergency control module, a thermal fuse activation circuit, and a BeiDou satellite communication terminal, all housed in a chassis. The emergency control module is connected to both the thermal fuse control circuit and the BeiDou satellite communication terminal. The thermal fuse control circuit is connected to the thermal fuse. The thermal fuse is connected to the outer shell of the airship. The emergency control module receives status data and programmed commands from the ground station, and uses safety control logic to determine the current flight time, communication interruption time, airship altitude, and horizontal radius of the airship's flight, and sends an activation signal to the thermal fuse activation circuit. The emergency control module also receives remote control commands from the BeiDou satellite communication terminal or the ground station and sends safety control action signals to the thermal fuse activation circuit. This invention exhibits strong environmental adaptability, enables beyond-line-of-sight control, and is low-cost, easy to operate, and highly reliable.

Description

Technical Field

[0001] This invention relates to the field of avionics control technology, and in particular to a safety control system and control method for airships based on thermal fuses. Background Technology

[0002] Aerostats are aircraft that rely on a lighter-than-air gas to maintain buoyancy in the air; helium is commonly used. Unmanned aerostats are operated by ground personnel using methods such as remote control, programmed control, or automatic flight control. Based on whether they have propulsion, they can be classified as airships and balloons; according to flight altitude, airships can be divided into general airships, stratospheric airships, near-space airships, and space airships.

[0003] When an aerostat is hovering in the air, it may lose control due to malfunctions in its power system, control system, or tethering cables, resulting in an escape. An escaped aerostat can interfere with the flight of other aircraft and pose a threat to personnel, facilities, and property on the ground. This threat is particularly greater for large unmanned aerostats or high-altitude aerostats, which have a wider flight range. Therefore, in the event of an unmanned aerostat escaping, measures should be taken to rapidly release helium to facilitate a swift landing.

[0004] A review of existing technologies revealed that traditional airship safety control systems rely on the explosion of fire control components to blast the airship body. This method requires specialized personnel, is complex to install, has low efficiency, high risk, high cost, and the fire control components are difficult to store. Summary of the Invention

[0005] In order to overcome the shortcomings of the prior art, the purpose of this invention is to provide an airship safety control system and control method based on hot fuses.

[0006] To achieve the above objectives, the present invention provides the following solution:

[0007] An airship safety control system based on hot fuse includes: an emergency control module, a hot fuse start-up circuit, and a Beidou satellite communication terminal installed in the chassis;

[0008] The emergency control module is connected to the hot fuse control circuit and the Beidou satellite communication terminal respectively; the hot fuse control circuit is connected to the hot fuse; the hot fuse is connected to the outer shell of the airship;

[0009] The emergency control module receives status data and programmable commands from the ground station, and uses safety control logic to determine the current flight time, communication interruption time, airship altitude, and horizontal radius of the airship's flight, and sends a start signal to the hot fuse activation circuit; the emergency control module is also used to receive remote control commands from the Beidou satellite communication terminal or from the ground station, and send a safety control action signal to the hot fuse activation circuit.

[0010] Preferably, it also includes a lithium battery and a manual switch;

[0011] The lithium battery is connected to the emergency control module via the manual switch, and the lithium battery is used to supply power to the emergency control module.

[0012] Preferably, it also includes: a positive relay, a negative relay, a thermal fuse on / off relay, and a test relay;

[0013] The emergency control module is connected to one end of the hot fuse control circuit via the positive relay and the hot fuse on / off relay in sequence; the emergency control module is also connected to the other end of the hot fuse control circuit via the negative relay; the test relay is connected to the hot fuse control circuit.

[0014] Preferably, it further includes: a temperature detector and a heating element;

[0015] The heating element is located at the bottom of the lithium battery, and the temperature detector is located in the chassis. Both the temperature detector and the heating element are connected to the emergency control module. The temperature detector is used to collect temperature signals in real time and send them to the emergency control module. The emergency control module is used to control the working state of the heating element according to the temperature signals and a preset temperature threshold.

[0016] Preferably, it also includes an external communication interface;

[0017] The external communication interface is connected to both the emergency control module and the main computer; the external communication interface is used to realize data transmission between the emergency control module and the main computer.

[0018] Preferably, the status data includes: battery voltage, battery temperature, operating current, bladder pressure difference, hot fuse tension, longitude, latitude, altitude, and horizontal distance; the emergency control module sends the status data to the Beidou satellite communication terminal and the external communication interface at fixed intervals, and writes it into the storage unit built into the emergency control module.

[0019] Preferably, the safety control logic is as follows: when T1≥T1set or T2≥T2set or H≥Hset or D≥Dset, a safety control action signal is issued;

[0020] Where: T1set is the maximum flight time setting, T2set is the maximum communication interruption time setting, Hset is the maximum flight altitude setting, and Dset is the maximum flight horizontal radius setting; T1 is the current flight time, T2 is the communication interruption time, H is the airship altitude, and D is the airship's horizontal flight radius.

[0021] Preferably, the hot fuse control circuit includes: a positive control circuit and a negative control circuit;

[0022] The positive control circuit is connected to the hot fuse on / off relay, the hot fuse on / off relay is connected to the positive terminal of the hot fuse, and the negative control circuit is connected to the negative terminal of the hot fuse and the negative relay.

[0023] A control method for the above system, comprising:

[0024] Power on the emergency control module and determine whether the emergency control module is working properly through status data. At this time, the safety control logic is disabled. After confirming that the emergency control module is working properly, enable the thermal fuse to work effectively, and the entire airship safety control system is powered on.

[0025] Before the airship leaves the ground, a programmable command is issued from the ground station, and altitude, time and horizontal distance settings are set.

[0026] When the airship enters the flight phase, the airship's working status is determined based on the status data transmitted by the emergency control module, and remote control commands are sent to control the emergency control module to send a safety control start signal to the hot fuse start circuit and modify the control parameters.

[0027] According to specific embodiments provided by the present invention, the present invention discloses the following technical effects:

[0028] This invention provides a safety control system and control method for an airship based on a thermal fuse. The system includes: an emergency control module, a thermal fuse activation circuit, and a BeiDou satellite communication terminal, all housed in a chassis. The emergency control module is connected to both the thermal fuse control circuit and the BeiDou satellite communication terminal. The thermal fuse control circuit is connected to the thermal fuse. The thermal fuse is connected to the outer shell of the airship. The emergency control module receives status data and programmed commands from the ground station, and uses safety control logic to determine the current flight time, communication interruption time, airship altitude, and horizontal radius of the airship's flight, and sends an activation signal to the thermal fuse activation circuit. The emergency control module also receives remote control commands from the BeiDou satellite communication terminal or the ground station and sends a safety control action signal to the thermal fuse activation circuit. This invention exhibits strong environmental adaptability, enables beyond-line-of-sight operation, and is low-cost, easy to operate, and highly reliable. Attached Figure Description

[0029] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0030] Figure 1 This is a schematic diagram of the system structure provided in an embodiment of the present invention;

[0031] Figure 2 This is a schematic diagram of the hot fuse circuit structure provided in an embodiment of the present invention;

[0032] Figure 3 The installation of the tearing mechanism on the surface of the capsule provided in the embodiments of the present invention;

[0033] Figure 4 A schematic diagram of the tearing mechanism provided in an embodiment of the present invention;

[0034] Figure 5 This is a schematic diagram of the heating wire installation / connection method provided in an embodiment of the present invention;

[0035] Figure 6 A schematic diagram of the control system provided in an embodiment of the present invention;

[0036] Figure 7 This is a schematic diagram of the overall security control communication link provided in an embodiment of the present invention;

[0037] Figure 8 A flowchart of the control method provided in an embodiment of the present invention.

[0038] Explanation of reference numerals in the attached figures:

[0039] 1-Emergency control module; 2-Beidou satellite communication terminal; 3-External communication interface; 4-Thermal fuse control circuit; 5-Thermal fuse; 6-Positive relay; 7-Negative relay; 8-Thermal fuse on / off relay; 9-Test relay; 10-Lithium battery; 11-Temperature detector; 12-Heating element; 13-Chassis; 14-Manual switch. Detailed Implementation

[0040] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0041] The purpose of this invention is to provide an airship safety control system and control method based on thermal fuses, which has strong environmental adaptability, can realize beyond-line-of-sight operation, and is low in cost, easy to operate, and highly reliable.

[0042] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0043] Figure 1 This is a schematic diagram of the system structure provided in an embodiment of the present invention, such as... Figure 1 As shown, the present invention provides an airship safety control system based on a hot fuse 5, including: an emergency control module 1, a hot fuse 5 start-up circuit, a Beidou satellite communication terminal 2, a lithium battery 10, a manual switch 14, a positive relay 6, a negative relay 7, a hot fuse 5 on / off relay 8, a test relay 9, a temperature detector 11, a heating element 12, and an external communication interface 3, all housed in a chassis 13.

[0044] The emergency control module 1 is connected to the hot fuse control circuit 4 and the Beidou satellite communication terminal 2 respectively; the hot fuse control circuit 4 is connected to the hot fuse 5; the hot fuse 5 is connected to the outer shell of the airship; the lithium battery 10 is connected to the emergency control module 1 through the manual switch 14, and the lithium battery 10 is used to supply power to the emergency control module 1; the external communication interface 3 is connected to the emergency control module 1 and the main computer respectively; the emergency control module 1 is connected to one end of the hot fuse control circuit 4 in sequence through the positive relay 6 and the hot fuse 5 on / off relay 8; the emergency control module 1 is also connected to the other end of the hot fuse control circuit 4 through the negative relay 7; the test relay 9 is connected to the hot fuse control circuit 4.

[0045] The emergency control module 1 receives status data and programmable commands issued by the ground station, and judges the current flight time, communication interruption time, airship altitude, and horizontal radius of the airship's flight through safety control logic, and sends a start signal to the hot fuse 5 start circuit; the emergency control module 1 is also used to receive remote control commands from the Beidou satellite communication terminal 2 or from the ground station, and send a safety control action signal to the hot fuse 5 start circuit.

[0046] The heating element 12 is disposed at the bottom of the lithium battery 10, and the temperature detector 11 is disposed in the chassis 13. Both the temperature detector 11 and the heating element 12 are connected to the emergency control module 1. The temperature detector 11 is used to collect temperature signals in real time and send them to the emergency control module 1. The emergency control module 1 is used to control the working state of the heating element 12 according to the temperature signals and preset temperature thresholds.

[0047] The external communication interface 3 is used to realize data transmission between the emergency control module 1 and the host computer.

[0048] Preferably, the status data includes: battery voltage, battery temperature, operating current, bag pressure difference, tension of hot fuse 5, longitude, latitude, altitude, and horizontal distance; the emergency control module 1 sends the status data to the Beidou satellite communication terminal 2 and the external communication interface 3 at fixed intervals, and writes it into the storage unit built into the emergency control module 1.

[0049] Specifically, the emergency control module 1 is a compact, redundant embedded computer that outputs control signals to drive the thermal fuse 5 to start. It can interact with ground telemetry and remote control via the BeiDou satellite communication terminal 2 and the external communication interface 3. The interface between the module and the BeiDou satellite communication terminal 2 is RS232, connected via the thermal fuse control circuit 4. The external communication interface 3 is an RS422 interface, directly connected to the line-of-sight communication link. The BeiDou satellite communication terminal 2 is an integrated BeiDou navigation and communication device, combining BeiDou-1 and BeiDou-2 communication terminals and a GPS receiver, supporting BeiDou short message communication services.

[0050] Preferably, the safety control logic is as follows: when T1≥T1set or T2≥T2set or H≥Hset or D≥Dset, a safety control action signal is issued; wherein: T1set is the maximum flight time setting value, T2set is the maximum communication interruption time setting value, Hset is the maximum flight altitude setting value, and Dset is the maximum flight horizontal radius setting value; T1 is the current flight time, T2 is the communication interruption time, H is the airship altitude, and D is the airship's flight horizontal radius.

[0051] Furthermore, the airship safety control system of the hot fuse 5 is powered by a battery installed in the chassis 13.

[0052] like Figure 2 As shown, the hot fuse control circuit 4 includes: a positive control circuit and a negative control circuit;

[0053] The positive control circuit is connected to the on / off relay 8 of the hot fuse 5, and the on / off relay 8 of the hot fuse 5 is connected to the positive terminal of the hot fuse 5. The negative control circuit is connected to the negative terminal of the hot fuse 5 and the negative relay 7 respectively.

[0054] Specifically, in this embodiment, when the set conditions are fully matched, the security control system activates and the hot fuse 5 is started.

[0055] In this embodiment, the emergency control module 1 receives remote control commands from the Beidou satellite communication terminal 2 or from the ground and sends a security control action signal to the security control circuit; the external communication interface 3 is an RS422 interface, used to connect to an external host computer or line-of-sight link.

[0056] Furthermore, the hot-melt wire 5 is laid on top of the airship. The hot-melt wire 5 is a hot-melt heating mechanism, in which the hot-melt wire 5 is laid on the top upper surface of the skin along the direction of the capsule cut pieces of the unmanned airship, which can heat and tear the capsule in one go to achieve rapid release of buoyancy gas, usually helium.

[0057] Optionally, the chassis 13 is equipped with a manual switch 14, which is connected between the lithium battery 10 and the emergency control module 1, and is used to connect the power supply of other equipment in the system except for the hot fuse 5 before the unmanned aerobatic vehicle takes off.

[0058] Specifically, the lithium battery 10 provides power to the entire unmanned aerostat emergency control system. Its fully charged voltage is 28V, and its discharge cut-off voltage is 22.2V. After encapsulation, it can withstand a vacuum environment. A heating element 12 is attached to the bottom surface of the lithium battery 10. In low-temperature environments, power is supplied to the heating element 12 via a relay to heat the lithium battery 10. The lithium battery 10 is also encased in insulating material, such as cotton wool.

[0059] Optionally, a temperature detector 11 is provided in the chassis 13. The temperature detector 11 is a DS18B20 and is connected to the emergency control module 1 to transmit temperature signals in real time. When the detected temperature is below 8°C, the heating element 12 is automatically turned on and heated to 14°C before automatically stopping.

[0060] In this embodiment, the emergency control module 1 can activate the thermal fuse 5 through remote control mode and program control mode. The remote control mode means that the emergency control module 1 can directly receive instructions and activate the thermal fuse 5 via the Beidou satellite communication terminal 2 or an external communication interface 3. The program control mode means that the emergency control module 1 receives status data and program control instructions, and sends a start signal to the thermal fuse control circuit 4 through safety control logic.

[0061] As an optional implementation method, the operation process of the unmanned aerostat emergency control system in this embodiment is as follows:

[0062] 1) Collect sensor data such as battery voltage, battery temperature, hot fuse operating current, and hot fuse tension, and obtain location information such as longitude, latitude, and altitude from the Beidou satellite communication terminal;

[0063] 2) Obtain program control commands by interrupting the Beidou satellite communication terminal and external communication interface, namely, enabling or disabling the thermal fuse at regular intervals, enabling or disabling the thermal fuse at altitude, enabling or disabling the thermal fuse at the horizontal radius of flight, setting the flight time T1set, setting the communication interruption time T2set, setting the altitude Hset, setting the horizontal distance Dset, and enabling the thermal fuse 5.

[0064] 3) When a command to directly activate the hot fuse is received, the emergency control module sends a start signal to the hot fuse control circuit;

[0065] 4) When the thermal fuse is automatically activated through the safety control logic, the Beidou satellite communication terminal and the external communication interface receive control parameters T1, T2, H, and D and combine them with status parameters, and then automatically activate the thermal fuse through the safety control logic.

[0066] 5) The status parameters are periodically sent to the external communication interface according to the communication protocol format at 70 millisecond intervals;

[0067] 6) Pack the status parameters into BeiDou short messages according to the communication protocol format with a period of 1 minute and 10 seconds, and send them to the BeiDou satellite communication terminal interface at regular intervals;

[0068] 7) Write the status parameters into the storage unit of the emergency control module at a 1-second interval.

[0069] like Figure 3 As shown, the emergency tearing device's actuator uses a nickel-chromium alloy heating wire. Based on the sphere's size and volume, the tearing device employs two sets of heating wires, each set consisting of two wires. These two sets are installed on the top of the sphere, distributed on both sides of the safety controller. The two wires within each set are installed at a 90° angle, melting the bladder material. The heating wires and mounting components are detachable from the bladder for easy replacement.

[0070] like Figure 4 As shown, to ensure the heating wire adheres closely to the capsule and prevents it from swinging and abrading the capsule during assembly, inflation, and ascent, a fixing strap is installed above the heating wire. This strap is made of a transparent, adhesive-backed film, facilitating a tight fit between the heating wire and the capsule without affecting the heating wire's fusing effect. Furthermore, tension springs are installed at both ends of the heating wire. To measure the tension of these springs, a tension sensor is connected to each heating wire, with eyebolts connecting both ends of the sensor.

[0071] like Figure 5 The diagram shown is an installation schematic of a single heating wire, in which... Figure 5 (a) indicates the end where the tension sensor is installed. Figure 5 (b) indicates the end without the tension sensor. The heating wire, eyebolt, tension sensor, and tension spring are connected in series and then linked to a cord loop on the reinforcing base fabric. The cord loop is made of high-strength webbing and sewn onto the base fabric. The reinforcing base fabric is made of woven material and is heat-sealed to the bladder body, effectively improving local strength and preventing wear on the bladder body material. A woven material retaining plate is welded onto the reinforcing base fabric, through which the heating wire passes, ensuring a closer fit between the heating wire and the bladder body. A protective cover is welded above the reinforcing base fabric. After the tearing mechanism is installed, the protective cover is placed on top and secured to the base fabric around the perimeter using Velcro. The protective cover prevents wear on the bladder body at the end of the tearing mechanism during final assembly, inflation, and deflation.

[0072] like Figure 6 As shown, the emergency tearing device control system mainly consists of an emergency battery, a security control computer, a relay board, sensors (voltage, current, temperature, and tensile force sensors), a Beidou integrated unit, and a heating element. Figure 7 As shown. The safety control computer is used for command reception and signal feedback, and controls the thermal fusion actuator according to control commands. The safety control computer can communicate with the dome computer via serial port, or directly with the ground control station via the Beidou integrated unit, achieving a redundant communication design. The emergency battery uses a low-temperature, high-rate lithium battery pack to power the emergency tearing mechanism in case of external power failure. Temperature control within the control box is achieved through a thermal control device (temperature sensor and heating element), maintaining the box temperature above -10℃. Except for the tension sensor, all electronic equipment and components in the emergency tearing mechanism control system are integrated and installed within the environmental control box, meeting their normal operating temperature requirements.

[0073] Corresponding to the above system, this embodiment also provides a control method for the above system, such as... Figure 8 As shown, including

[0074] Step 801: Power on the emergency control module and determine whether the emergency control module is working properly through status data. At this time, the safety control logic is in a disabled state. After confirming that the emergency control module is working properly, enable the thermal fuse to work effectively, and the entire airship safety control system is powered on.

[0075] Step 802: Before the airship leaves the ground, use the ground station to issue a program control command and set the altitude setting value, time setting value, and horizontal distance setting value;

[0076] Step 803: When the airship enters the flight phase, the working status of the airship is determined based on the status data transmitted by the emergency control module, and a remote control command is sent to control the emergency control module to send a safety control start signal to the hot fuse start circuit and modify the control parameters.

[0077] Specifically, the control steps of the unmanned aerial vehicle emergency control system in this embodiment are as follows:

[0078] Step 1: When the unmanned aerostat is in the ground test state, first close the manual switch 15 to power on the emergency control system of the unmanned aerostat. Determine whether the emergency control system is working properly by checking the status information. At this time, the safety control logic is in the disabled state. After confirming that the system is normal, turn on the test relay to check whether the hot fuse is on and off normally, and observe the tension sensor to check whether the tension is normal.

[0079] Step 2: Before the unmanned aerostat takes off, a remote control command is sent through the ground control station via line-of-sight link or Beidou satellite link. The enable command for the hot fuse 5 is automatically activated at a set time or altitude. According to the flight test plan, a certain margin is considered when setting the time. For example, if the planned maximum flight time is 2 hours, the time setting parameter value can be set to 125 minutes. After setting, the status data command is used to report and confirm that the program control is in the enabled state.

[0080] Step 3: The airship leaves the ground and enters the flight phase. The flight mode is enabled. The position and working status of the airship locator are determined based on the status data transmitted by the emergency control system of the unmanned airship. Depending on the situation, the control parameters can be modified by sending a line-of-sight link or Beidou satellite link through the ground control station, or the start-up fuse 5 can be activated directly by remote control to ensure the safety of the flight process.

[0081] For the high-altitude unmanned aerostat, with a flight altitude of 20 km, a designed flight time not exceeding 420 minutes, and an allowable horizontal flight range of 290 km from the launch point, the safety control logic is set as follows: The thermal fuse is enabled at regular intervals, with T1set set to 600 minutes and T2set set to 60 minutes; the thermal fuse is disabled when the altitude is exceeded; the thermal fuse is enabled when the horizontal distance exceeds the flight range, with Dset set to 290 km.

[0082] The beneficial effects of this invention are as follows:

[0083] This invention exhibits strong environmental adaptability. The use of a thermally fused wire to cleave the capsule allows it to adapt to temperature and pressure changes from low to high altitudes. The lithium battery, installed within the chassis, is actively heated to withstand the low-temperature environment at high altitudes. It supports beyond-line-of-sight (BOS) control via a BeiDou satellite communication terminal, using BeiDou short message service. It also boasts high reliability, featuring an independent power supply battery, an emergency control module, and a BOS link, employing both program-controlled and remote-controlled modes. This newly designed safety control system based on a thermally fused wire utilizes the thermally fused wire to cleave the capsule, resulting in high efficiency, low cost, and ease of operation.

[0084] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. Regarding the methods disclosed in the embodiments, since they correspond to the systems disclosed in the embodiments, the descriptions are relatively simple; relevant parts can be referred to the system section description.

[0085] This document uses specific examples to illustrate the principles and implementation methods of the present invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of the present invention. Furthermore, those skilled in the art will recognize that, based on the ideas of the present invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of the present invention.

Claims

1. An airship safety control system based on thermal fuses, characterized in that, include: The emergency control module, hot fuse start-up circuit, and Beidou satellite communication terminal are installed in the chassis; The emergency control module is connected to the hot fuse control circuit and the Beidou satellite communication terminal respectively; the hot fuse control circuit is connected to the hot fuse; the hot fuse is connected to the outer shell of the airship; The emergency control module receives status data and programmable commands from the ground station, and uses safety control logic to determine the current flight time, communication interruption time, airship altitude, and horizontal radius of the airship's flight, and sends a start signal to the hot fuse activation circuit; the emergency control module is also used to receive remote control commands from the Beidou satellite communication terminal or from the ground station, and send a safety control action signal to the hot fuse activation circuit. It also includes: positive relays, negative relays, thermal fuse on / off relays, and test relays; The emergency control module is connected to one end of the hot fuse control circuit via the positive relay and the hot fuse on / off relay in sequence; the emergency control module is also connected to the other end of the hot fuse control circuit via the negative relay; the test relay is connected to the hot fuse control circuit. The hot fuse control circuit includes: a positive control circuit and a negative control circuit; The positive control circuit is connected to the hot fuse on / off relay, the hot fuse on / off relay is connected to the positive terminal of the hot fuse, and the negative control circuit is connected to the negative terminal of the hot fuse and the negative relay respectively. The hot-melt wire is laid on the top of the airship. The hot-melt wire is an emergency tearing mechanism. The hot-melt wire is laid on the top surface of the skin along the direction of the cut piece of the unmanned airship. It can heat up and tear the airship in one go to achieve rapid release of buoyancy gas, usually helium. The emergency tearing mechanism uses nickel-chromium alloy heating wire. According to the size and volume of the sphere, the fuse heating mechanism uses two sets of heating wires, each set consisting of two heating wires. The two sets of heating wires are installed on the top of the sphere and distributed on both sides of the safety controller. The two wires in each set are installed at a 90° angle. After the heating wire melts the bladder material, the heating wire and the mounting structure can be detached from the bladder. To ensure the heating wire adheres closely to the capsule and prevents it from swinging and abrading the capsule during assembly, inflation, and ascent, a fixing strap is installed above the heating wire. The strap is made of a transparent film material with adhesive backing, which facilitates a tight fit between the heating wire and the capsule without affecting the heating wire's melting effect. Additionally, tension springs are installed at both ends of the heating wire. To measure the tension of these springs, a tension sensor is connected to each heating wire, with eye bolts connecting both ends of the tension sensor. The installation structure of a single heating wire is as follows: the heating wire, eye bolt, tension sensor, and tension spring are connected in series and then connected to the rope buckle on the reinforcing base fabric. The rope buckle is made of high-strength webbing and is sewn onto the base fabric. The reinforcing base fabric is made of woven material and is heat-sealed to the bladder body to effectively improve local strength and prevent wear on the bladder body material. A woven material limiting piece is welded onto the reinforcing base fabric. The heating wire passes through the base fabric and the limiting piece, making the heating wire fit the bladder body more closely. A protective cover is welded on top of the reinforcing base fabric. After the emergency tearing mechanism is installed, the protective cover is put on. The protective cover is fixed to the base fabric around the perimeter by Velcro. The protective cover can prevent wear on the bladder body at the end of the tearing mechanism during the final assembly inflation and deflation process. The security control logic is as follows: when T1≥T1set or T2≥T2set or H≥Hset or D≥Dset, a security control action signal is issued; Where: T1set is the maximum flight time setting, T2set is the maximum communication interruption time setting, Hset is the maximum flight altitude setting, and Dset is the maximum flight horizontal radius setting; T1 is the current flight time, T2 is the communication interruption time, H is the airship altitude, and D is the airship's horizontal flight radius.

2. The airship safety control system based on thermal fuse according to claim 1, characterized in that, It also includes a lithium battery and a manual switch; The lithium battery is connected to the emergency control module via the manual switch, and the lithium battery is used to supply power to the emergency control module.

3. The airship safety control system based on hot fuse according to claim 2, characterized in that, Also includes: Temperature detector and heating element; The heating element is located at the bottom of the lithium battery, and the temperature detector is located in the chassis. Both the temperature detector and the heating element are connected to the emergency control module. The temperature detector is used to collect temperature signals in real time and send them to the emergency control module. The emergency control module is used to control the working state of the heating element according to the temperature signals and a preset temperature threshold.

4. The airship safety control system based on hot fuse according to claim 2, characterized in that, It also includes external communication interfaces; The external communication interface is connected to both the emergency control module and the main computer; the external communication interface is used to realize data transmission between the emergency control module and the main computer.

5. The airship safety control system based on hot fuse according to claim 4, characterized in that, The status data includes: battery voltage, battery temperature, operating current, bladder pressure difference, hot fuse tension, longitude, latitude, altitude, and horizontal distance; the emergency control module sends the status data to the Beidou satellite communication terminal and the external communication interface at fixed intervals, and writes it into the storage unit built into the emergency control module.

6. A control method for an airship safety control system based on a thermal fuse as described in any one of claims 1 to 5, characterized in that, The control method includes powering on the emergency control module, determining whether the emergency control module is working properly through status data, at which point the safety control logic is disabled; once the emergency control module is determined to be working properly, the thermal fuse can be effectively operated, and the entire airship safety control system is powered on. Before the airship leaves the ground, a programmable command is issued from the ground station, and altitude, time and horizontal distance settings are set. When the airship enters the flight phase, the airship's working status is determined based on the status data transmitted by the emergency control module, and remote control commands are sent to control the emergency control module to send a safety control start signal to the hot fuse start circuit and modify the control parameters.

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