Rocket-launched emergency lighting device and method of deployment thereof

Abstract

The application discloses a rocket delivery type emergency lighting device, which comprises a two-stage rocket, the two-stage rocket comprising an upper stage and a boost stage, the upper stage comprising a nose cone, the nose cone being connected with an upper stage rocket body, the upper stage rocket body being connected with a boost stage rocket body; the inside of the nose cone is provided with a lighting module, the inside of the upper stage rocket body is provided with an in-flight attitude correction module, an avionics module, a hydrogen production mechanism, a hydrogen balloon and an upper stage parachute, and the tail end of the upper stage rocket body is provided with an upper stage engine and an upper stage tail wing assembly; the inside of the boost stage rocket body is provided with a boost stage parachute and a boost stage engine, and the tail of the boost stage rocket body is provided with a boost stage tail wing assembly. The application further discloses a deployment method of the rocket delivery type emergency lighting device, and solves the problems of slow deployment, inconvenience in carrying and poor terrain adaptability of the existing emergency lighting device.

Description

Technical Field

[0001] This invention belongs to the field of emergency rescue equipment technology, and relates to a rocket-deployed emergency lighting device. This invention also relates to a deployment method for the rocket-deployed emergency lighting device. Background Technology

[0002] In nighttime emergency rescue scenarios, lighting is a key prerequisite for ensuring search and rescue efficiency and reducing the safety risks to rescuers. Common equipment for nighttime emergency rescue includes portable handheld lighting devices, fixed emergency light towers, tethered emergency lighting drones, and floating high-altitude lighting devices.

[0003] Handheld lighting equipment has a limited illumination range, typically not exceeding 50m. 2 Furthermore, their limited battery life makes them unable to cover large search and rescue areas, hindering their ability to meet the needs of large-scale, long-duration nighttime emergency rescue missions. Fixed emergency lighthouses are heavy and have many components, requiring multiple people to transport them in batches, resulting in long deployment times. They also require multiple people to work together to set up on-site, have poor terrain adaptability, and cannot be quickly deployed in complex areas such as ruins and mountains. Currently, most mainstream tethered emergency lighting drones are assembled and modified from mature drone platforms, and require open spaces and experienced pilots to operate them, which is difficult to achieve at disaster sites. Moreover, the modified drones pose safety hazards. Aerial lighting devices typically use aerial platforms, but require the preparation of large quantities of lightweight gas in advance. For emergency rescue scenarios, heavy gas cylinders need to be manually transported to designated locations to complete a series of tasks such as inflation, aerobaticization, and deployment before stable nighttime emergency lighting can be achieved, which is time-consuming and inefficient.

[0004] In summary, existing emergency lighting devices are insufficient to meet the rapid deployment needs of complex disaster sites, and suffer from problems such as slow deployment, inconvenience in carrying, and poor terrain adaptability. Therefore, there is an urgent need to develop an emergency lighting device that is fast to deploy, easy to carry, and highly adaptable to terrain. Summary of the Invention

[0005] The purpose of this invention is to provide a rocket-deployable emergency lighting device, which solves the problems of slow deployment, inconvenience in carrying, and poor terrain adaptability of existing emergency lighting devices.

[0006] Another object of the present invention is to provide a method for deploying rocket-deployed emergency lighting devices.

[0007] The technical solution adopted in this invention is a rocket-deployed emergency lighting device, which uses a two-stage rocket configuration. The two-stage rocket includes an upper stage and a booster stage. The upper stage includes a nose cone, which connects to the upper stage body, and the upper stage body connects to the booster stage body. A lighting module is installed inside the nose cone. An air attitude correction module, an avionics module, a hydrogen production mechanism, a hydrogen balloon, and an upper stage parachute are installed inside the upper stage body. An upper stage engine and an upper stage tail fin assembly are installed at the tail end. A booster stage parachute and a booster stage engine are installed inside the booster stage body. A booster stage tail fin assembly is installed at the tail end.

[0008] The invention is further characterized in that, The head cone adopts an elliptical curve shape and is made of transparent acrylic material. The lighting module includes an aluminum substrate and a COB light-emitting sheet mounted on the aluminum substrate. The aluminum substrate is connected to a bracket, which is connected to a ring-shaped fin heat sink. The ring-shaped fin heat sink is in close contact with the aluminum substrate. The lighting module is connected to a mooring cable through a waterproof aviation connector.

[0009] The nose cone cavity serves as the installation space for the lighting module, and the rear of the nose cone has a reserved insertion structure for the upper stage rocket body. A fixing plate c is installed inside the upper stage rocket body. An air attitude correction module is fixed to one side of the fixing plate c, and fixing plates d and e are installed parallel to it on the other side. The air attitude correction module is installed on the fixing plate c, and the avionics module is installed on the fixing plate d. The avionics module includes a micro flight controller, which is connected to the upper stage control circuit. The air attitude correction module includes an altimeter, an attitude sensor, four sets of 29mm ducted brushless motors and an integrated ESC propulsion unit.

[0010] A hydrogen production mechanism is installed on the fixed plate e. The hydrogen production mechanism adopts a dual storage tank structure of calcium hydride and water. The dual storage tank structure of calcium hydride and water has a built-in stirring device. The stirring device is connected to a trigger valve and produces hydrogen gas by chemical reaction. The hydrogen production mechanism is connected to a hydrogen balloon. A piston plate is installed on the side of the hydrogen balloon away from the fixed plate e to flexibly divide the space between the folded hydrogen balloon and the upper stage parachute.

[0011] The upper stage rocket body houses the upper stage engine, with its nose closely attached to the thrust plate a. The thrust plate a receives the thrust of the upper stage engine. The upper stage engine passes through the upper stage tail fin assembly, which has a mounting hole in the middle to ensure that the upper stage engine does not move laterally. The upper stage tail fin assembly houses the fixing plate f, which secures the upper stage engine. The upper stage parachute is mounted on the thrust plate a, and a piston plate is mounted above the upper stage parachute, with the piston plate closely attached to the hydrogen balloon. The upper stage rocket body separation device is located on the side of the fixed plate d away from the avionics module. The upper stage rocket body separation device separates the upper stage rocket body into two parts. The component located on the side of the fixed plate d closer to the nose cone serves as the airborne component, and the other components serve as the recovery component. Fixed plates d and e are both equipped with several anchor points. The hydrogen balloon is connected to the airborne component through the anchor points on the fixed plate d. The upper stage parachute is connected to the upper stage rocket body by two anchor points, which are respectively connected to the fixed plate d and the fixed plate e.

[0012] The booster stage rocket body houses multiple booster stage engines. The heads of these engines are closely attached to thrust plate b, which bears the thrust of the engines. The engines penetrate the tail fin assembly, which has mounting holes to prevent lateral movement. Parachute anchor points are located on thrust plate b, connecting to the booster stage parachutes. A booster stage rocket body separation device is also located inside the booster stage rocket body.

[0013] The mooring cable passes through the head cone and extends outside the head cone. The tail end of the mooring cable reel is connected to the ground control module, which includes a power supply unit, a control unit, and a brightness adjustment unit.

[0014] Another technical solution adopted in this invention is a deployment method for a rocket-deployed emergency lighting device, which is implemented according to the following steps: Step 1: The rocket is carried manually to the area where emergency lighting is needed. After the rocket is assembled and prepared on the ground, it is launched into the air with the tether cable. After the booster stage engine burns out, the upper stage rocket engine ignites and the booster stage separates from the upper stage. Step 2: Driven by the upper stage engine, the upper stage carrying the cable continues to rise, and then falls after reaching the highest point; Step 3: Activate the upper stage rocket body separation device. The empty component in the upper stage rocket body separates from the recovery component. Under the buoyancy of the hydrogen balloon, the empty component establishes stable buoyancy. Step 4: The ground control module supplies power to the lighting module via a tethered cable, and the lighting module hovers and turns on the lighting.

[0015] A further feature of this invention is that, in step 2, the upper stage, propelled by its upper-stage engine, continues to ascend carrying the tether cable; upon reaching its highest point of 80m-100m, the upper-stage parachute deploys, and the upper-stage rocket body descends slowly. T At time 2, the altitude is H2. The upper stage rocket separation device is in a silent state; at the same time as the upper stage parachute pops out and unfolds, the hydrogen production mechanism is activated to generate hydrogen gas from the reaction of calcium hydride and water, which is then filled into the hydrogen balloon. The anchor point between the hydrogen balloon and the upper stage rocket body is located on the fixed plate d. The hydrogen balloon inflates and unfolds, and leaves the interior of the upper stage rocket body under the action of gas expansion. As hydrogen gas is added, the buoyancy of the hydrogen balloon gradually increases until the hydrogen balloon is full.

[0016] Step 3: While establishing stable buoyancy at an altitude of 50m, cut the upper stage parachute anchor point of the fixed plate d. T At time 3, the altitude is H 3. The buoyancy-holding component establishes stable buoyancy under the buoyancy of the hydrogen balloon, and the recovery component recovers the system under the action of the upper-stage parachute.

[0017] The beneficial effects of this invention are that the rocket-deployed emergency lighting device of this invention has the advantages of fast deployment speed, wide coverage, no terrain restriction, lightweight and safe and reliable, solving the core pain point of "difficult lighting and slow deployment" at disaster sites. The deployment method of the rocket-deployed emergency lighting device of this invention realizes rapid delivery, rapid deployment and stable operation of emergency lighting, meets the large-scale lighting needs of complex disaster sites, and is suitable for widespread application. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the rocket-deployed emergency lighting device of the present invention; Figure 2 This is a schematic diagram of the lighting module structure of the rocket-delivered emergency lighting device of the present invention; Figure 3 This is a cross-sectional view of the rocket-deployed emergency lighting device of the present invention; Figure 4 A schematic diagram of the rocket carrying the tethered cable taking off according to the present invention; Figure 5 This is a flowchart illustrating the deployment method of the rocket-deployed emergency lighting device of the present invention.

[0019] In the diagram, 1. Nose cone, 2. Illumination module, 3. Upper stage body, 4. Upper stage tail fin assembly, 5. Booster stage body, 6. Booster stage tail fin assembly, 7. Fixing plate a, 8. Fixing plate b, 9. Fixing plate c, 10. Fixing plate d, 11. Fixing plate e, 12. Piston plate, 13. Thrust plate a, 14. Fixing plate f, 15. Thrust plate b, 16. Attitude correction module, 17. Avionics module, 18. Hydrogen production mechanism, 19. Hydrogen balloon, 20. Upper stage parachute, 21. Booster stage parachute, 22. COB light-emitting sheet, 23. Aluminum substrate, 24. Annular fin heat sink, 25. Support frame. Detailed Implementation

[0020] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments.

[0021] Example 1 The rocket-launched emergency lighting device of the present invention, such as Figure 1 As shown, the rocket employs a two-stage configuration combined with aerodynamic technology and tethered power supply technology. The two-stage rocket includes an upper stage and a booster stage. The upper stage includes a nose cone 1, which connects to the upper stage body 3, and the upper stage body 3 connects to the booster stage body 5. The nose cone 1 houses a lighting module 2. The upper stage body 3 houses an air attitude correction module 16, an avionics module 17, a hydrogen production mechanism 18, a hydrogen balloon 19, and an upper stage parachute 20. The tail end houses the upper stage engine and the upper stage tail assembly 4. The booster stage body 5 houses the booster stage parachute 21 and the booster stage engine. The tail end houses the booster stage tail assembly 6. The two-stage rocket rapidly deploys the lighting module 2 to a preset high altitude. The aerodynamic technology combined with tethered power supply technology ensures stable nighttime illumination for the lighting module 2.

[0022] Example 2 Based on Example 1, in this embodiment, the head cone 1 adopts an elliptical curve shape and is made of transparent acrylic material, such as... Figure 2 As shown, the lighting module 2 includes an aluminum substrate 23 and a COB light-emitting sheet 22 mounted on the aluminum substrate. The aluminum substrate 23 is connected to a bracket 25, and the bracket 25 is connected to an annular finned heat sink 24. The annular finned heat sink 24 is in close contact with the aluminum substrate 23. The lighting module 2 is connected to a tethered cable via a waterproof aviation connector. Figure 3 As shown, the lighting module 2 is fixed to the head cone 1 by fixing plate a7 and fixing plate b8. Several fixing holes are opened on fixing plate a7 and fixing plate b8 respectively. The shape of the fixing holes on fixing plate a7 matches the shape of the annular fin heat sink 24. The fixing holes on fixing plate b8 are fixed to the mounting holes of bracket 25 by screws to prevent the lighting module 2 from shifting position.

[0023] Example 3 Based on Embodiment 2, in this embodiment, the inner cavity of the nose cone 1 serves as the installation space for the lighting module 2. The rear of the nose cone 1 has a reserved insertion structure for the upper stage rocket body 3. The nose cone 1 is inserted into the upper stage rocket body 3 and locked with screws. A fixing plate c9 is installed inside the upper stage rocket body 3. The aerial attitude correction module 16 is fixedly connected to one side of the fixing plate c9, and the fixing plates d10 and e11 are arranged parallel to each other on the other side.

[0024] An air attitude correction module 16 is mounted on fixed plate C9, and an avionics module 17 is mounted on fixed plate D10. The avionics module 17 includes a micro flight controller, which is connected to the upper-level control circuit. The air attitude correction module 16 includes an altimeter, an attitude sensor, four sets of 29mm ducted brushless motors and an integrated electronic speed controller (ESC) propulsion unit. The altimeter and attitude sensor are used to sense the hovering altitude and attitude of the hovering module in real time. The altimeter and attitude sensor, along with the four sets of 29mm ducted brushless motors and ESC propulsion units, form a closed-loop air attitude correction module. With the micro flight controller as the core, it collects pitch, roll, and yaw attitude data in real time through a six-axis gyroscope. The micro flight controller, combined with a PID control algorithm, dynamically adjusts the output thrust of the four ducted fans corresponding to the four sets of ducted brushless motors to achieve real-time compensation for lateral wind disturbance and uneven balloon buoyancy.

[0025] A hydrogen production mechanism 18 is installed on the fixed plate e11. The hydrogen production mechanism 18 adopts a dual storage tank structure of calcium hydride and water. The dual storage tank structure of calcium hydride and water has a built-in stirring device. The stirring device is connected to a trigger valve and produces hydrogen gas by chemical reaction. The hydrogen production mechanism 18 is connected to a hydrogen balloon 19. A piston plate 12 is installed on the side of the hydrogen balloon 19 away from the fixed plate e11 to flexibly divide the space between the folded hydrogen balloon 19 and the upper stage parachute 20.

[0026] The upper stage rocket body 3 houses the upper stage engine, with its head closely attached to the thrust plate a13. The thrust plate a13 bears the thrust of the upper stage engine. The upper stage engine passes through the upper stage tail assembly 4, which has a mounting hole in the middle to ensure that the upper stage engine does not move laterally. The upper stage tail assembly 4 houses the fixing plate f14, which secures the upper stage engine. The upper stage parachute 20 is mounted on the thrust plate a13, and a piston plate 12 is mounted above the upper stage parachute 20, closely attached to the hydrogen balloon 19.

[0027] A separation device for the upper stage rocket body is installed on the side of the fixed plate d10 away from the avionics module 17. The separation device separates the upper stage rocket body 3 into two parts. The component located on the side of the fixed plate d10 closer to the nose cone 1 serves as the airborne component, and the other components serve as the recovery component. Several anchor points are provided on both the fixed plate d10 and the fixed plate e11. The hydrogen balloon 19 is connected to the airborne component through the anchor points on the fixed plate d10. The upper stage parachute 20 has two anchor points with the upper stage rocket body 3, which are respectively connected to the fixed plate d10 and the fixed plate e11.

[0028] Multiple booster engines are installed inside the booster stage body 5. The heads of the multiple booster engines are closely attached to the thrust plate b15, which bears the thrust of the multiple booster engines. The multiple booster engines pass through the booster stage tail fin assembly 6. The booster stage tail fin assembly 6 has mounting holes for the multiple booster engines in the middle to ensure that the multiple booster engines do not move laterally. Parachute anchor points are set on the thrust plate b15, and the parachute anchor points are connected to the booster stage parachute 21. A booster stage separation device is installed inside the booster stage body 5.

[0029] Both the upper stage engine and the booster stage engine use solid rocket engines.

[0030] Example 4 like Figure 4 As shown, the tether cable is connected to the lighting module 2, passes through the head cone 1 and extends out of the head cone 1. The tail end of the tether cable reel is connected to the ground control module. The ground control module includes a power supply unit, a control unit and a brightness adjustment unit, which work together to control the COB light-emitting sheet 22.

[0031] The tethering cable uses a dual-core tensile power supply cable, which is made of dual-core flexible silicone cable to stably transmit power. The strong tension generated during rocket launch prevents cable breakage and adapts to dragging during launch and changes in the tethering line during inverted flight. The end of the dual-core tensile power supply cable is electrically connected to the ground control module, serving both power transmission and tethering load-bearing functions. It is used to transmit power from the ground control module to the lighting module 2. The tethering cable reel is used to store the dual-core tensile power supply cable for easy deployment and retrieval. The power supply unit of the ground control module uses a large-capacity lithium battery pack to provide stable power to the entire system. The control unit controls the launch of the second-stage rocket structure and the opening and closing of the lighting module 2. The brightness adjustment unit adopts a stepless dimming mode, adjusting the brightness of the lighting unit according to the ambient light intensity and search and rescue needs, flexibly adjusting the brightness of the lighting unit to avoid glare from strong light affecting rescue operations.

[0032] This invention relates to a rocket-launched emergency lighting device that uses a ground-powered mode, eliminating the need to carry batteries to high altitudes. It allows for rapid deployment and is highly practical, suitable for various scenarios such as earthquakes, floods, field search and rescue, mountain disaster relief, and urban emergency repairs. The lighting brightness can be adjusted according to needs, and the rocket body is recyclable and reusable, reducing operating costs. The tethered cable serves both as a power supply and a load-bearing device. Together with the aerial attitude correction module 16, it prevents the lighting module from drifting with the wind, improving lighting stability. Example 5 The deployment method of the rocket-deployable emergency lighting device of the present invention is implemented according to the following steps: Step 1: Carry it to the area where emergency lighting is needed. After the ground assembly and preparation are completed, ignite the engine and launch it into the air with the tether cable. After the booster stage engine burns out, the upper stage rocket engine ignites. Under the action of the high-pressure gas flow ejected by the upper stage rocket engine, the booster stage separates from the upper stage. Step 2: Driven by the upper stage engine, the upper stage continues to ascend with the tether cable. After reaching the highest point, it descends. The upper stage parachute pops out and opens, causing the upper stage rocket body to descend slowly. At the same time, the hydrogen production mechanism 18 is activated and the hydrogen balloon 19 is inflated. Step 3: Activate the upper stage rocket body separation device. The empty component in the upper stage rocket body 3 separates from the recovery component. Under the buoyancy of the hydrogen balloon, the empty component establishes stable buoyancy. Step 4: The ground control module supplies power to the lighting module 2 via a tethered cable, and the lighting module 2 hovers and turns on the lighting.

[0033] Example 6 The deployment method of the rocket-deployable emergency lighting device of the present invention is as follows: Figure 5 As shown, the specific implementation steps are as follows: Step 1: The booster is carried manually to the area where emergency lighting is needed. After the assembly and preparation on the ground are completed, the booster is ignited and launched into the air. After the booster engine burns out, the booster separates from the upper stage. Step 1 involves the following steps: after ground preparation is completed, T At time 0, the altitude is H 0. After the booster engine is ignited, it propels the entire second-stage rocket structure into the air. After ignition, the rocket takes off with the tether cable. At the moment of ignition, the micro flight control receives the signal, and the altimeter and attitude sensor collect altitude and attitude signals in real time. The booster engine is used to propel the rocket upward. Propelled by multiple solid rocket motors in the booster stage, the rocket, along with its tethering cables, rapidly ascends. The booster stage tail fin assembly is used to maintain the rocket's stability during ascent. After the booster stage rocket engines burn out, the upper stage rocket engines ignite, and under the influence of the high-pressure exhaust gas ejected from the upper stage engines... T At time 1, the altitude is H 1. The booster stage and the upper stage separate, the booster stage parachute 21 pops out and opens, and the booster stage rocket body 5 is recovered.

[0034] Step 2: Driven by the upper stage engine, the upper stage carrying the cable continues to rise, and then falls after reaching the highest point; Step 2 specifically involves the upper stage, propelled by its upper-stage engine, continuing to ascend while carrying the tether cable. Upon reaching its highest point of 80-100 meters, the upper-stage parachute 20 deploys, and the upper-stage rocket body 3 descends slowly. T At time 2, the altitude is H2. The upper stage rocket body separation device is in a silent state; at the same time as the upper stage parachute 20 pops out and unfolds, the hydrogen production mechanism 18 is activated to generate hydrogen gas by the reaction of calcium hydride and water, which is then filled into the hydrogen balloon 19. The anchor point of the hydrogen balloon 19 and the upper stage rocket body 3 is located on the fixed plate d10. The hydrogen balloon 19 inflates and unfolds, and leaves the interior of the upper stage rocket body under the action of gas expansion. As hydrogen gas is filled, the buoyancy of the hydrogen balloon 19 gradually increases until the hydrogen balloon 19 is full. Step 3: Activate the upper stage rocket body separation device. The empty component in the upper stage rocket body 3 separates from the recovery component. Under the buoyancy of the hydrogen balloon, the empty component establishes a stable buoyancy at a height of 50m. At the same time, the anchor point of the upper stage parachute 20 on the fixing plate d10 is cut off. T At time 3, the altitude is H 3. The buoyancy component establishes a stable buoyancy under the buoyancy of the hydrogen balloon 19, and the recovery component recovers the system under the action of the upper-stage parachute 20.

[0035] Step 4: The ground control module supplies power to the lighting module 2 via a tethered cable, and the lighting module 2 hovers and turns on the lighting.

[0036] When suspended, the COB light-emitting sheet 22 in the lighting module 2 of the airborne component is located below the hydrogen balloon 19 to provide wide-area emergency lighting.

[0037] This invention discloses a deployment method for a rocket-deployed emergency lighting device. Through a two-stage rocket combined with buoyancy and tethered power supply technology, the lighting module 2 is rapidly deployed to a predetermined altitude and buoyed, thus meeting the stable lighting needs for nighttime emergency rescue. It can be launched from confined spaces, is not limited by terrain, and requires no open takeoff and landing space. The lighting module 2 can be quickly deployed to disaster-stricken areas with blocked roads and complex terrain, overcoming the terrain limitations of traditional emergency beacons and drones. The upper-stage parachute 20 and booster-stage parachute 21 are used to safely recover the corresponding rocket body during the airdrop process, facilitating reuse and reducing operating costs. This rocket-deployed emergency lighting device deployment method offers rapid deployment, wide coverage, no terrain limitations, lightweight design, and high reliability. It is suitable for emergency lighting at various disaster sites, quickly seizing crucial rescue time, and has high practicality and promotional value.

Claims

1. A rocket-deployed emergency lighting device, characterized in that, The rocket adopts a two-stage configuration, which includes an upper stage and a booster stage. The upper stage includes a nose cone (1), which is connected to the upper stage body (3). The upper stage body (3) is connected to the booster stage body (5). The nose cone (1) is equipped with a lighting module (2). The upper stage body (3) is equipped with an air attitude correction module (16), an avionics module (17), a hydrogen production mechanism (18), a hydrogen balloon (19), and an upper stage parachute (20). The tail end is equipped with an upper stage engine and an upper stage tail fin assembly (4). The booster stage body (5) is equipped with a booster stage parachute (21) and a booster stage engine. The tail end is equipped with a booster stage tail fin assembly (6).

2. The rocket-delivered emergency lighting device according to claim 1, characterized in that, The head cone (1) adopts an elliptical curve shape and is made of transparent acrylic material. The lighting module (2) includes an aluminum substrate (23) and a COB light-emitting sheet (22) mounted on the aluminum substrate. The aluminum substrate (23) is connected to a bracket (25). The bracket (25) is connected to an annular fin heat sink (24). The annular fin heat sink (24) is in close contact with the aluminum substrate (23). The lighting module (2) is connected to a tethered cable through a waterproof aviation connector.

3. The rocket-deployed emergency lighting device according to claim 2, characterized in that, The inner cavity of the nose cone (1) serves as the installation space for the lighting module (2), and the rear of the nose cone (1) is reserved for the insertion structure of the upper stage rocket body (3); a fixing plate c (9) is set inside the upper stage rocket body (3), and an air attitude correction module (16) is fixed on one side of the fixing plate c (9), and a fixing plate d (10) and a fixing plate e (11) are set parallel to each other on the other side; an air attitude correction module (16) is set on the fixing plate c (9), and an avionics module (17) is set on the fixing plate d (10). The avionics module (17) includes a micro flight controller, which is connected to the upper stage control circuit; the air attitude correction module (16) includes an altimeter, an attitude sensor, four sets of 29mm ducted brushless motors and an integrated propulsion unit with electronic speed control.

4. The rocket-delivered emergency lighting device according to claim 3, characterized in that, The fixed plate e (11) is provided with a hydrogen production mechanism (18). The hydrogen production mechanism (18) adopts a dual storage tank structure of calcium hydride and water. The dual storage tank structure of calcium hydride and water has a built-in stirring device. The stirring device is connected to a trigger valve and produces hydrogen gas by chemical reaction. The hydrogen production mechanism (18) is connected to a hydrogen balloon (19). A piston plate (12) is provided on the side of the hydrogen balloon (19) away from the fixed plate e (11) to flexibly divide the space of the folded hydrogen balloon (19) and the upper stage parachute (20).

5. The rocket-delivered emergency lighting device according to claim 4, characterized in that, The upper stage rocket body (3) is equipped with an upper stage engine. The head of the upper stage engine is close to the thrust plate a (13). The thrust plate a (13) receives the thrust of the upper stage engine. The upper stage engine passes through the upper stage tail fin assembly (4). The upper stage tail fin assembly (4) has a mounting hole for the upper stage engine in the middle to ensure that the upper stage engine does not move laterally. The upper stage tail fin assembly (4) is equipped with a fixing plate f14 to fix the upper stage engine. The upper stage parachute (20) is installed on the thrust plate a (13). A piston plate (12) is installed above the upper stage parachute (20). The piston plate (12) is close to the hydrogen balloon (19). A separation device for the upper stage rocket body is set on the side of the fixed plate d (10) away from the avionics module (17). The separation device separates the upper stage rocket body (3) into two parts. The component located on the side of the fixed plate d (10) near the nose cone (1) serves as the air-holding component, and the other components serve as the recovery component. Several anchor points are set on both the fixed plate d (10) and the fixed plate e (11). The hydrogen balloon (19) is connected to the air-holding component through the anchor points on the fixed plate d (10). The upper stage parachute (20) has two anchor points with the upper stage rocket body (3), which are connected to the fixed plate d (10) and the fixed plate e (11) respectively.

6. The rocket-delivered emergency lighting device according to claim 5, characterized in that, Multiple booster engines are installed inside the booster stage body (5). The heads of the multiple booster engines are closely attached to the thrust plate b (15). The thrust plate b (15) bears the thrust of the multiple booster engines. The multiple booster engines pass through the booster stage tail fin assembly (6). The booster stage tail fin assembly (6) has mounting holes for the multiple booster engines in the middle to ensure that the multiple booster engines do not move laterally. A parachute anchor point is set on the thrust plate b (15). The parachute anchor point is connected to the booster stage parachute (21). A booster stage body separation device is installed inside the booster stage body (5).

7. The rocket-delivered emergency lighting device according to claim 6, characterized in that, The tether cable passes through the head cone (1) and extends outside the head cone (1). The tail end of the tether cable reel is connected to the ground control module, which includes a power supply unit, a control unit, and a brightness adjustment unit.

8. A deployment method for a rocket-deployed emergency lighting device, characterized in that, The specific steps are as follows: Step 1: The rocket is carried manually to the area where emergency lighting is needed. After the rocket is assembled and prepared on the ground, it is launched into the air with the tether cable. After the booster stage engine burns out, the upper stage rocket engine ignites and the booster stage separates from the upper stage. Step 2: Driven by the upper stage engine, the upper stage carrying the cable continues to rise, and then falls after reaching the highest point; Step 3: Activate the upper stage rocket body separation device. The empty component in the upper stage rocket body separates from the recovery component. Under the buoyancy of the hydrogen balloon, the empty component establishes stable buoyancy. Step 4: The ground control module supplies power to the lighting module via a tethered cable, and the lighting module hovers and turns on the lighting.

9. The deployment method of the rocket-deployed emergency lighting device according to claim 8, characterized in that, Step 2 is as follows: Under the propulsion of the upper stage engine, the upper stage, carrying the tether cable, continues to ascend; when it reaches the highest point of 80m-100m, the upper stage parachute (20) pops out and unfolds, and the upper stage rocket body (3) descends slowly. T At time 2, the altitude is H 2. The upper stage rocket body separation device is in a silent state; while the upper stage parachute (20) pops out and unfolds, the hydrogen production mechanism (18) is activated to generate hydrogen gas by the reaction of calcium hydride and water, which is then filled into the hydrogen balloon (19). The anchor point of the hydrogen balloon (19) and the upper stage rocket body (3) is located on the fixed plate d (10). The hydrogen balloon (19) inflates and unfolds, and leaves the interior of the upper stage rocket body under the action of gas expansion. As hydrogen gas is filled, the buoyancy of the hydrogen balloon (19) gradually increases until the hydrogen balloon (19) is full.

10. The deployment method of the rocket-deployed emergency lighting device according to claim 9, characterized in that, Step 3: While establishing stable buoyancy at a height of 50m, cut the anchor point of the upper stage parachute (20) of the fixed plate d (10). T At time 3, the altitude is H 3. The buoyancy component establishes a stable buoyancy under the buoyancy of the hydrogen balloon (19), and the recovery component is recovered under the action of the upper-stage parachute (20).

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