Unmanned reflector lighting aircraft and ground projection system

Abstract

The application discloses an unmanned reflection lighting aircraft and ground projection system, which can be in the air for a long time and does not depend on ground energy supply, and is used for solving the problem that long-time air lighting demand cannot be met in specific environments, such as crisis environments like rescue and relief and personnel search and rescue. The unmanned reflection lighting aircraft and ground projection system comprises an aircraft body and a ground projection device; the aircraft body comprises an airbag, a jet flow wind resistance device, a fused salt charging system, a searchlight and a take-off and landing support; the ground projection device comprises a photoelectric tracking device, which is installed on an open ground surface and is provided with a reflecting mirror, can track sunlight and converge light on the fused salt charging system by means of the reflecting mirror.

Description

Technical Field

[0001] This invention belongs to the field of aircraft lighting technology, specifically relating to an unmanned reflective lighting aircraft and a ground projection system. Background Technology

[0002] Unmanned aerial vehicles (UAVs) are low in cost, have excellent nighttime illumination, and are suitable for low and medium altitude regions. However, existing UAVs must return to the ground to replenish their power after a long flight. In emergency situations such as disaster relief and search and rescue, the repeated take-off and landing of UAVs will inevitably reduce the effective flight illumination time. Summary of the Invention

[0003] In view of this, the present invention provides an unmanned reflective lighting aircraft and ground projection system that can take off for a long time without relying on ground energy replenishment, and is used to solve the problem of long-term aerial lighting needs not being met in specific environments such as disaster relief, personnel search and rescue and other crisis environments.

[0004] To address the above problems, embodiments of the present invention provide an unmanned reflective lighting aircraft and a ground projection system, including an aircraft body and a ground projection device; The aircraft body includes: An airbag, installed on top of the aircraft, is filled with helium to provide lift for the aircraft; The jet wind-resistant device is installed around the aircraft body. It draws in gas through the air intake pipe, compresses it, and then ejects it from the jet pipes in four directions to adjust the aircraft's horizontal position. The molten salt charging system absorbs sunlight reflected from the ground during the daytime when there is ample sunshine, heating the internal materials to cause an endothermic phase change. Specifically, the molten salt used is a common binary molten salt (a mixture of 60% sodium nitrate and 40% potassium nitrate). After the sun disappears, the molten salt can still provide sufficient heat in the heat pipe as an energy storage material for emergency power generation. Inside the heat flow duct, it drives a steam turbine to rotate and generate electricity. The generated electricity is stored through an energy storage device to power the aircraft itself. Searchlights are located on the lower part of the aircraft; The base and landing gear are located at the bottom of the aircraft, and the landing gear is located at the bottom of the base. The ground projection device includes: The photoelectric tracking device, installed on an open ground surface, has a reflector on it to track sunlight and use the reflector to focus the light onto the molten salt charging system.

[0005] Furthermore, a fixed support is connected below the airbag, and the landing support is connected to the fixed support via steel cables. A helium cylinder is installed inside the fixed support, and the helium cylinder is connected to the airbag via an electric valve. The helium cylinder releases a fixed amount of helium to fill the airbag and generate lift. A gas gauge on the gas cylinder records the amount of compressed helium released. An airbag exhaust port is provided above the airbag, and an electronic exhaust valve is installed at the airbag exhaust port. By releasing an appropriate amount of helium, the airbag descends to a designated height.

[0006] Furthermore, the landing gear includes four isosceles right-angled triangular steel plates, with one right-angled side of each steel plate welded to the bottom of the base along the diagonal.

[0007] Furthermore, the molten salt charging system includes a heat-absorbing section, a heat-conducting pipe, a steam turbine, and an energy storage device; The molten salt is heated by sunlight through a heat-absorbing section. It continuously absorbs heat and the molten salt power generation device transfers the heat to the steam through heat pipes. The steam drives a steam turbine to generate electricity, which is then stored in an energy storage device.

[0008] Furthermore, the jet wind-resistant device includes an air inlet pipe located in the center, four sets of jet pipes located on the same plane, the central air inlet pipe pressurizes gas through a compressed fan, and then the pressurized gas is expelled through the jet pipes to achieve dynamic adjustment of the position of the airbag suspension body, and the central air inlet pipe is equipped with a filter screen.

[0009] Furthermore, the aircraft body also includes a controller and a signal receiving and transmitting device; the photoelectric tracking device includes a second radio transceiver, which communicates with the signal receiving and transmitting device, and the controller adjusts the attitude of the aircraft according to the signal receiving and transmitting device.

[0010] Furthermore, the photoelectric tracking device also includes a second control unit and a second rotating base; the reflector is mounted on the second rotating base via a second rotating shaft, and the second rotating base and the second rotating shaft are respectively driven by a drive motor; The second control unit receives and transmits position signals from the aircraft body via the second radio transceiver to control the drive motor to rotate, thereby rotating the reflector and concentrating the light from the reflector onto the heat-absorbing part of the molten salt charging system.

[0011] Furthermore, the photoelectric tracking device also includes an azimuth sensor and an elevation angle sensor; The azimuth sensor is located inside the second rotating base and is used to measure the rotation angle of the second rotating base in the horizontal plane. The elevation sensor is located on the second rotating axis and measures the pitch angle of the reflector and the photoelectric tracking device.

[0012] Compared with the prior art, the unmanned reflective lighting aircraft and ground projection system of the present invention have at least the following beneficial effects: The aircraft provided by this invention hovers at a designated altitude and accepts requests from ground control personnel. It is designed to provide nighttime illumination using searchlights, offering a flexible, efficient, and long-lasting disaster relief auxiliary lighting system. This unmanned aerial vehicle can continuously adjust its altitude and relative position in the air using its own jet wind-resistant device and compressed helium while maintaining its searchlights.

[0013] The above description is merely an overview of the technical solution of the present invention. In order to better understand the technical means of the present invention and to implement it in accordance with the contents of the specification, the preferred embodiments of the present invention are described in detail below with reference to the accompanying drawings. Attached Figure Description

[0014] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the following description of the embodiments will be briefly introduced. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0015] Figure 1 A structural diagram of an unmanned reflective illumination aircraft. Figure 2 for Figure 1 Vertical cross-sectional view; Figure 3 This is a structural diagram of the ground projection device; Figure 4 for Figure 1 A bottom view; Figure 5 A 3D view of an unmanned reflective lighting aircraft and its ground projection system.

[0016] In the diagram, 100 is the aircraft body, 101 is the airbag exhaust port, 102 is the airbag, 103 is the helium tank, 104 is the jet pipe, 105 is the air intake pipe, 106 is the steel cable, 107 is the signal receiving and transmitting device, 108 is the landing gear, 200 is the heat absorption section, 201 is the heat pipe, 202 is the steam turbine, 203 is the energy storage device, 305 is the second radio transceiver, 306 is the reflector, 307 is the second rotating base, 308 is the second rotating shaft, 309 is the photoelectric tracking device, and 401 is the searchlight. Detailed Implementation

[0017] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention. This invention is intended for wider application in socket-type heating pipes; therefore, it can be used in any practical application requiring suitability for a particular application.

[0018] Example 1 See Figures 1 to 5 This invention proposes an unmanned reflective lighting aircraft and a ground projection system, including an aircraft body 100 and a ground projection device. The aircraft body 100 includes an airbag 102, a jet wind-resistant device, a molten salt charging system, a searchlight 401, a base, and a landing gear 108.

[0019] See Figure 1 The airbag 102, filled with helium, is mounted on top of the aircraft and provides lift. The jet propulsion system is installed around the aircraft body 100, drawing in gas through the intake pipe 105, compressing it, and then ejecting it through four jet pipes 104 to adjust the aircraft's horizontal position. The base is located at the bottom of the aircraft, and the landing gear 108 is located at the bottom of the base. See also... Figure 2 The molten salt charging system heats the internal materials by absorbing light reflected from the ground, causing an endothermic phase change. The molten salt provides sufficient heat in the heat pipe 201, driving a steam turbine 202 to generate electricity. The generated electricity is stored in an energy storage device 203 and used to power the aircraft body 100. Specifically, a common binary molten salt (a mixture of 60% sodium nitrate and 40% potassium nitrate) is used. This allows the aircraft to remain airborne for extended periods without relying on direct ground-based energy replenishment. See also... Figure 4 Searchlight 401 is located on the lower part of the aircraft and provides nighttime illumination. See also Figure 1 The landing support 108 includes four isosceles right-angled triangular steel plates, and one right-angled side of each steel plate is welded to the bottom of the base along the diagonal.

[0020] See Figure 3 and Figure 5 The ground projection device includes a photoelectric tracking device 309. The photoelectric tracking device 309 is installed on an open ground surface and has a reflector 306 on it, which can track sunlight and concentrate the light onto the molten salt charging system with the help of the reflector 306.

[0021] As a preferred embodiment of the present invention, see [link to previous document]. Figure 1A fixed support is connected to the lower part of the airbag 102. The landing support 108 is connected to the fixed support via a steel cable 106. A helium tank 103 is installed inside the fixed support. The helium tank 103 is connected to the airbag 102 via an electric valve. The helium tank 103 releases a fixed amount of helium to fill the airbag 102 and obtain lift. The gas meter counts the amount of compressed helium released. An airbag exhaust port 101 is provided above the airbag 102. An electronic exhaust valve is installed on the airbag exhaust port 101 to release an appropriate amount of helium to descend to a designated height.

[0022] As a preferred embodiment of the present invention, see [link to previous document]. Figure 2 The molten salt charging system is fixed to the base. The molten salt charging system includes a heat-absorbing section 200, a heat-conducting pipe 201, a steam turbine 202, and an energy storage device 203. The heat-absorbing section 200 receives sunlight reflected from the ground and is heated. The molten salt continuously absorbs heat. At night, the molten salt power generation device transfers heat to the steam within the heat-conducting pipe 201, which drives the steam turbine 202 to generate electricity, which is stored in the energy storage device 203. The heat-absorbing section 200 is not directly connected to the helium gasbag, jet wind-resistant device, or helium tank above; there is a certain distance between the heat-absorbing section and the latter.

[0023] As a preferred embodiment of the present invention, see [link to previous document]. Figure 1 The jet wind-resistant device includes an air inlet pipe 105 located in the center and four sets of jet pipes 104 located on the same plane. The central air inlet pipe 105 is pressurized with gas by a compressed air fan, and then the pressurized gas is pushed out through the jet pipes 104 to achieve dynamic adjustment of the position of the airbag 102 suspension. The central air inlet pipe 105 is equipped with a filter screen to filter impurities in the air.

[0024] As a preferred embodiment of the present invention, see [link to previous document]. Figure 1 The aircraft body 100 also includes a controller and a signal receiving and transmitting device 107. The photoelectric tracking device 309 includes a second radio transceiver 305, which communicates with the signal receiving and transmitting device 107. The controller adjusts the attitude of the aircraft and operates the molten salt charging system based on the brightness and illuminance parameter signals received by the signal receiving and transmitting device 107.

[0025] As a preferred embodiment of the present invention, see [link to previous document]. Figure 3The photoelectric tracking device 309 includes a second radio transceiver 305, a second control unit, and a second rotating base 307. A reflector 306 is mounted on the second rotating base 307 via a second rotating shaft 308. The second rotating base 307 and the second rotating shaft 308 are driven by drive motors. The second radio transceiver 305 communicates with the signal receiving and transmitting device 107. The second control unit receives and transmits position signals from the aircraft body 100 via the second radio transceiver 305 to control the rotation of the drive motors, thereby rotating the reflector 306 and focusing the light from the reflector 306 onto the heat-absorbing part 200 of the molten salt charging system. The second radio transceiver 305 adds a photoresistor and a photodiode to the wireless tracking device. This serves two purposes: firstly, to align the reflection of sunlight onto the heat-absorbing part of the molten salt; and secondly, to lock the aircraft's position for fine-tuning. The photoresistor receives the change in resistance in the circuit due to the feedback of light, and the photodiode changes the voltage in the circuit due to the feedback of light, serving as the input terminal for the second radio transceiver 305 to receive external light feedback.

[0026] In a preferred embodiment of the present invention, the photoelectric tracking device 309 further includes an azimuth sensor and an elevation sensor. The azimuth sensor is located inside the second rotating base 307 and is used to measure the rotation angle of the second rotating base 307 in the horizontal plane. The elevation sensor is located on the second rotating axis 308 and measures the pitch angle of the reflector 306 and the photoelectric tracking device 309.

[0027] In summary, this invention provides an unmanned aerial vehicle (UAV) lighting system capable of prolonged flight and without direct ground-based charging. This system does not rely on traditional power supplies, enabling continuous aerial illumination. Energy loss after takeoff primarily occurs due to helium release for altitude adjustment and power consumption by the jet generator for horizontal positioning. This power loss can be supplemented by the UAV's own molten salt power generation system utilizing natural light and specific reflections from the ground. The base station control system is equipped with advanced sensors and adaptive algorithms to monitor ambient light conditions in real time and adjust the balloon's position and altitude to ensure optimal lighting performance under various conditions. Furthermore, the system can collaborate with other rescue equipment via a wireless communication interface, improving overall emergency response efficiency.

[0028] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention in any way. Any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention shall still fall within the scope of the technical solution of the present invention.

Claims

1. An unmanned reflective lighting aircraft and ground projection system, characterized in that: Includes the aircraft body (100) and the ground projection device; The aircraft body (100) includes: An airbag (102) is installed on the top of the aircraft. The airbag (102) is filled with helium to provide lift for the aircraft. The jet wind-resistant device is installed around the aircraft body (100). It draws in gas through the air intake pipe (105), compresses it, and then ejects it through the jet pipes (104) in four directions to adjust the horizontal position of the aircraft. The molten salt charging system includes a heat-absorbing part (200), a heat-conducting pipe (201), a steam turbine (202), and an energy storage device (203). The molten salt charging system heats the internal material by absorbing the light reflected from the ground, causing an endothermic phase change. The molten salt provides sufficient heat in the heat flow circulation of the heat-conducting pipe (201), which drives the steam turbine (202) to rotate and generate electricity inside the heat circulation system. The generated electricity is stored through the energy storage device (203) to supply power to the aircraft body (100). Searchlight (401), located at the bottom of the aircraft; The base and landing gear (108) are located at the bottom of the aircraft and the landing gear (108) is located at the bottom of the base. The ground projection device includes: The photoelectric tracking device (309) has a reflector (306) on it, which uses the reflector (306) to focus light onto the molten salt charging system.

2. The unmanned reflective lighting aircraft and ground projection system according to claim 1, characterized in that: A fixed support is connected below the airbag (102). The landing support (108) is connected to the fixed support via a steel cable (106). A helium tank (103) is installed inside the fixed support. The helium tank (103) is connected to the airbag (102) via an electric valve. The helium tank (103) releases a fixed amount of helium to fill the airbag (102) to obtain lift. The gas meter counts the amount of compressed helium released. An airbag exhaust port (101) is provided above the airbag (102). An electronic exhaust valve is installed on the airbag exhaust port (101). By releasing an appropriate amount of helium, the airbag descends to a designated height.

3. The unmanned reflective lighting aircraft and ground projection system according to claim 2, characterized in that: The landing gear (108) includes four isosceles right-angled triangular steel plates, one right-angled side of each steel plate being welded to the bottom of the base along the diagonal.

4. The unmanned reflective lighting aircraft and ground projection system according to claim 3, characterized in that: The jet wind-resistant device includes an air inlet pipe (105) located in the center, and four sets of jet pipes (104) located on the same plane. The central air inlet pipe (105) is pressurized with gas by a compressed air fan, and then the pressurized gas is pushed out through the jet pipes (104) to realize dynamic adjustment of the position of the airbag (102) suspension body. The central air inlet pipe (105) is equipped with a filter screen.

5. The unmanned reflective lighting aircraft and ground projection system according to claim 4, characterized in that: The aircraft body (100) also includes a controller and a signal receiving and transmitting device (107). The photoelectric tracking device (309) includes a second radio transceiver (305), which communicates with the signal receiving and transmitting device (107). The controller adjusts the attitude of the aircraft according to the signal receiving and transmitting device (107).

6. The unmanned reflective lighting aircraft and ground projection system according to claim 5, characterized in that: The photoelectric tracking device (309) also includes a second control unit and a second rotating base (307); the reflector (306) is mounted on the second rotating base (307) via a second rotating shaft (308), and the second rotating base (307) and the second rotating shaft (308) are driven by drive motors respectively; The second control unit receives and transmits position signals from the aircraft body (100) via the second radio transceiver (305) to control the rotation of the drive motor, thereby rotating the reflector (306) and concentrating the light from the reflector (306) onto the heat-absorbing part (200) of the molten salt charging system.

7. The unmanned reflective lighting aircraft and ground projection system according to claim 6, characterized in that: The photoelectric tracking device (309) also includes an azimuth sensor and an elevation angle sensor; The azimuth sensor is located inside the second rotating base (307) to measure the rotation angle of the second rotating base (307) in the horizontal plane, and the elevation sensor is located on the second rotating axis (308) to measure the pitch angle of the reflector (306) and the photoelectric tracking device (309).

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