Emergency landing system for airship

Abstract

The invention is suitable for the technical field of airships, and provides an emergency landing system for an airship. The helium bag and the air bag are arranged in the boat body and used for adjusting the boat body to ascend and descend; the power paddle is arranged on the boat body and is used for providing direction adjusting power; the power paddle consists of a propeller and a motor; the conduit is fixed on the helium bag and used for passing through a gas flow channel, an integrated shell is arranged on the conduit, and a protective shell is sleeved outside the integrated shell; and the electric valve is arranged on the guide pipe and is used for adjusting helium output. According to the emergency landing system for the airship, rapid landing is achieved by discharging helium, the helium discharging speed is adjusted by monitoring the landing speed, dangerous accidents caused by direct falling of equipment are effectively prevented, and the emergency landing safety is high.

Description

Technical Field

[0001] The invention belongs to the technical field of airships, and in particular relates to an emergency landing system for airships. Background Art

[0002] An airship is a lighter-than-air aircraft. The main difference between it and a hot air balloon is that it is equipped with a device for propulsion and flight control. An airship is usually composed of a hull, a pod, a tail, and a propulsion device. The flight principle of an airship mainly relies on the buoyancy generated by the difference in air density and the control of the propulsion device. When the buoyancy in the air cabin is greater than the weight of the airship itself, the airship can take off, and the propulsion device generates a reaction force to push the airship forward or change direction. The control system is responsible for adjusting the working state of the propulsion device to ensure that the airship flies according to the predetermined flight trajectory and attitude.

[0003] In the prior art, the landing method of an airship is to directly adjust the amount of air in the hull to adjust the rise and fall of the hull. The head of the hull sinks so that the hull descends during movement. This process is time-consuming and is not suitable for scenarios that require emergency landing. Summary of the invention

[0004] The present invention provides an emergency landing system for an airship, aiming to solve the problem that in the prior art, the airship landing method is to directly adjust the amount of air in the hull to adjust the rise and fall of the hull, and the head of the hull sinks so that the hull descends during the movement. This process is time-consuming and is not suitable for scenarios requiring emergency landing.

[0005] To solve the above problems, the present invention is implemented as follows: an emergency landing system for an airship, comprising: a hull; a helium bag and an air bag arranged in the hull for adjusting the lifting of the hull; a power paddle installed on the hull for providing direction adjustment power, the power paddle consisting of a propeller and an electric motor; a conduit fixed on the helium bag for passing a gas flow channel, the conduit is provided with an integrated shell, and the integrated shell is outer-mounted with a protective shell; an electric valve arranged on the conduit for adjusting the output of helium; an exhaust pipe installed on the protective shell and extending to the outside of the hull for outputting helium, the exhaust pipe is provided with a control valve for adjusting the opening and closing of the exhaust pipe.

[0006] Preferably, a valve stem is rotatably installed in the control valve, and a valve core for adjusting the opening and closing of the control valve is provided on the valve stem. The valve stem extends outside the control valve, and a handwheel is provided on the valve stem. An adjustment plate is installed on the handwheel, and an electric telescopic rod for adjusting the angle of the handwheel is hinged on the outer wall of the hull, and the output rod of the electric telescopic rod is hinged to the adjustment plate.

[0007] Preferably, a limiting block is provided on one side of the valve stem away from the handwheel. A second spring is installed on the outer wall of the control valve through a fixing plate. A limiting plate that can be clamped outside the limiting block to stabilize the valve stem is installed on the second spring. An adjusting assembly for adjusting the position of the limiting plate is provided on the control valve.

[0008] Preferably, the adjusting assembly includes an electromagnet fixed on the control valve, a guide rod installed on the limiting plate and passing through the second spring, and an iron block fixed on the guide rod and adsorbable on the electromagnet.

[0009] Preferably, the electromagnet is composed of a connecting plate installed on the outer wall of the control valve, a metal rod installed on the connecting plate, a coil sleeved outside the metal rod for conducting electricity, and a clamping plate fixed on the outer wall of the control valve and sleeved outside the metal rod. An insulating sleeve is sleeved outside the coil.

[0010] Preferably, a mesh cover for isolating impurities is installed on the top of the hull and sleeved outside the exhaust pipe. The mesh cover is provided with mesh holes allowing air to pass through. A control cabin is provided at the bottom of the hull. A radar speedometer for monitoring the speed of the hull is provided in the control cabin. Monitoring the speed of the hull is used to adjust the helium output.

[0011] Preferably, a damping spring for reducing the impact during the landing of the airship is installed at the bottom of the control cabin. A support frame for supporting the device is installed at the bottom of the damping spring. A limiting telescopic rod is installed between the support frame and the control cabin, and the limiting telescopic rod passes through the damping spring.

[0012] Preferably, a material bin for storing materials is installed on one side of the control cabin. A discharge port is provided at the bottom of the material bin. A bottom plate for closing the discharge port is hinged at the bottom of the material bin. An oil cylinder for adjusting the opening and closing of the bottom plate is hinged on the support frame, and the output rod of the oil cylinder is hinged to the bottom plate.

[0013] Preferably, the support frame is made of carbon fiber composite material. An empty cabin for reducing weight is provided inside the support frame. A rubber block for assisting in shock absorption is provided at the bottom of the support frame, and the rubber block is also used to increase the friction between the device and the ground.

[0014] Preferably, a flowmeter for monitoring the helium discharge speed is provided on the exhaust pipe. A chute is provided on the control valve. A slider connected to the limiting plate is slidably installed in the chute, and the chute cooperates with the slider to limit the movement path of the limiting plate.

[0015] Compared with the related art, the emergency landing system for an airship provided by the present invention has the following beneficial effects:

[0016] Compared with the prior art, the emergency landing system for airships provided by this solution adjusts the buoyancy of the airship body by setting up helium gas bags and air bags in cooperation, and precisely controls the discharge of helium gas by using electric valves and control valves. It has changed the traditional way of adjusting the lifting and lowering of the airship body by directly adjusting the amount of air inside the airship body, which takes a long time for landing. In case of an emergency, it can quickly reduce the buoyancy of the airship body, achieve the rapid landing of the airship, greatly shorten the landing time, improve the safety and response ability of the airship in case of an emergency. By controlling the opening degree of the electric valve, the discharge speed of helium gas can be precisely controlled, so as to realize the rapid adjustment of the buoyancy of the airship body. At the same time, the control valve is provided with a valve stem and a valve core. By rotating the valve stem, the valve core can be driven to move, realizing the precise adjustment of the opening and closing of the control valve. When the airship lands, the shock-absorbing spring can undergo elastic deformation, absorbing and buffering part of the impact energy, thereby reducing the impact force generated when the airship lands. At the same time, the limit telescopic rod limits and guides the up and down movement of the control cabin, preventing the control cabin from shaking or shifting excessively under the action of the shock-absorbing spring. Adopting an integrated design is convenient for centralized control of helium gas output. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 is the front sectional structure schematic diagram of an emergency landing system for airships provided by the present invention;

[0018] Figure 2 is the system management platform architecture diagram of an emergency landing system for airships provided by the present invention;

[0019] Figure 3 is Figure 1 the enlarged structure schematic diagram of part A shown in ;

[0020] Figure 4 is the rear view structure schematic diagram of the control valve in the present invention;

[0021] Figure 5 is Figure 1 the enlarged structure schematic diagram of part B shown in ;

[0022] Figure 6 is the three-dimensional structure schematic diagram of the support frame in the present invention;

[0023] Figure 7 is the three-dimensional structure schematic diagram of the clamping plate in the present invention;

[0024] Figure 8 is the assembly structure schematic diagram of the electromagnet in the present invention;

[0025] Figure 9 is the assembly structure schematic diagram of the helium gas bag, gas transmission pipe and integrated shell in the present invention;

[0026] Figure 10This is the upward view structural schematic diagram of the material bin in the present invention.

[0027] Reference numerals: 1, hull; 2, helium balloon; 3, airbag; 4, power paddle; 5, control bin; 6, material bin; 7, damping spring; 8, support frame; 9, limit telescopic rod; 10, oil cylinder; 11, bottom plate; 12, empty bin; 13, protective shell; 14, exhaust pipe; 15, control valve; 16, valve rod; 17, handwheel; 18, adjusting plate; 19, electric telescopic rod; 20, wire mesh cover; 21, limit block; 22, fixing plate; 23, second spring; 24, limit plate; 25, chute; 26, slider; 27, guide rod; 28, iron block; 29, electromagnet; 30, connecting plate; 31, metal rod; 32, coil; 33, clamping plate; 34, conduit; 35, integrated shell; 36, electric valve. Detailed implementation manners

[0028] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the technical field to which this application belongs; the terms used in the specification of this application are only for the purpose of describing specific embodiments and are not intended to limit this application; the terms "including" and "having" and any variations thereof in the specification and claims of this application and the above drawings are intended to cover non-exclusive inclusion. The terms "first", "second", etc. in the specification and claims of this application or the above drawings are used to distinguish different objects and not to describe a specific order; the orientation or positional relationship indicated by the terms "inner", "outer", "left", "right" is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation of the present invention.

[0029] Reference to "embodiment" herein means that a particular feature, structure, or characteristic described in connection with the embodiment can be included in at least one embodiment of this application. The phrase appears in various places in the specification and does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment mutually exclusive with other embodiments. Those skilled in the art will explicitly and implicitly understand that the embodiments described herein can be combined with other embodiments.

[0030] An embodiment of the present invention provides an emergency landing system for an airship, as Figure 1-10As shown in the figure, the emergency landing system for an airship includes: a hull 1; a helium gas bag 2 and an air bag 3 disposed inside the hull 1 for adjusting the lifting and lowering of the hull 1; a power propeller 4 installed on the hull 1 for providing power for direction adjustment, and the power propeller 4 is composed of a propeller and an electric motor; a conduit 34 fixed on the helium gas bag 2 for passing through a gas flow channel, an integrated housing 35 is provided on the conduit 34, and a protective housing 13 is sleeved outside the integrated housing 35; an electric valve 36 disposed on the conduit 34 for adjusting the output of helium gas; an exhaust pipe 14 installed on the protective housing 13 and extending outside the hull 1 for outputting helium gas, and a control valve 15 for adjusting the opening and closing of the exhaust pipe 14 is provided on the exhaust pipe 14.

[0031] In this embodiment, the hull 1 serves as the main load-bearing structure of the entire airship emergency landing system, providing an installation basis for other components. The helium gas bag 2 and the air bag 3 are arranged inside to adjust the lifting and lowering of the hull 1. The helium gas bag 2 adjusts the buoyancy of the hull 1 by storing and releasing helium gas. During an emergency landing, it cooperates with the electric valve 36 to control the output of helium gas, changes the buoyancy state of the hull 1, and assists in the landing. The air bag 3 works in coordination with the helium gas bag 2 to assist in adjusting the lifting and lowering of the hull 1 by adjusting the air volume inside the hull 1, and jointly with the helium gas bag 2, realizes precise control of the buoyancy of the hull 1. During the emergency landing process, the power propeller 4 provides power for direction adjustment of the airship, ensuring that the airship can move in a predetermined direction during the landing process. The conduit 34 serves as a gas flow channel, enabling helium gas to be smoothly transported from the helium gas bag 2 to the exhaust pipe 14. The integrated housing 35 functions to integrate relevant control components such as the electric valve 36 (DZW series), etc., facilitating centralized control of the helium gas output. The protective housing 13 protects the integrated housing 35 and its internal components, preventing damage to the components caused by the external environment. By controlling the opening degree of the electric valve 36, the discharge speed of helium gas can be precisely controlled, thereby realizing rapid adjustment of the buoyancy of the hull 1 to meet the emergency landing requirements. The exhaust pipe 14 is used to output helium gas, discharging the helium gas in the helium gas bag 2 outside the hull 1 to reduce the buoyancy of the hull 1. The control valve 15 is used to adjust the opening and closing of the exhaust pipe 14. By controlling the on-off state of the control valve 15, the discharge timing of helium gas can be controlled, further enhancing the flexibility of the buoyancy adjustment of the hull 1. The airship emergency landing system adjusts the buoyancy of the hull 1 by setting the helium gas bag 2 and the air bag 3 in cooperation, precisely controls the discharge of helium gas by using the electric valve 36 and the control valve 15, and changes the traditional landing method of directly adjusting the air volume inside the hull 1 to adjust the lifting and lowering of the hull 1, which takes a long time. In an emergency, it can quickly reduce the buoyancy of the hull 1, realize the rapid landing of the airship, greatly shorten the landing time, improve the safety and response ability of the airship in an emergency, and meet the scenario requirements for emergency landing (the electric motor is a Siemens 1FT7 servo motor).

[0032] In a further preferred embodiment of the present invention, a valve stem 16 is rotatably installed inside the control valve 15. A valve core for adjusting the opening and closing of the control valve 15 is provided on the valve stem 16. The valve stem 16 extends outside the control valve 15. A handwheel 17 is provided on the valve stem 16. An adjusting plate 18 is installed on the handwheel 17. An electric telescopic rod 19 for adjusting the angle of the handwheel 17 is hinged on the outer wall of the hull 1. The output rod of the electric telescopic rod 19 is hinged to the adjusting plate 18.

[0033] In this embodiment, the control valve 15 is a key control component of the helium discharge channel. Through the cooperation of the internal valve stem 16 and the valve core, the opening and closing of the exhaust pipe 14 are adjusted, thereby controlling the discharge of helium. The valve stem 16 is the core transmission component of the control valve 15. A valve core is provided on it. By rotating the valve stem 16, the valve core can be driven to move, realizing the adjustment of the opening and closing of the control valve 15. The valve core is used to directly adjust the opening and closing state of the control valve 15, controlling the flow rate and discharge of helium. The handwheel 17 provides an operating point for manually operating the control valve 15. The operator can drive the valve stem 16 to rotate by rotating the handwheel 17, thereby adjusting the control valve 15. The adjusting plate 18, as a connecting component between the electric telescopic rod 19 (Delke LT30 electric push rod) and the handwheel 17, transmits the output force of the electric telescopic rod 19 to the handwheel 17, realizing the adjustment of the angle of the handwheel 17. The electric telescopic rod 19 pushes the adjusting plate 18 through telescopic movement, thereby driving the handwheel 17 to rotate, realizing the automatic adjustment of the control valve 15. In an emergency, the discharge of helium can be controlled quickly and accurately. In the emergency landing scenario, the electric telescopic rod 19 can respond quickly, push the adjusting plate 18 to drive the handwheel 17 to rotate, quickly adjust the opening and closing state of the control valve 15, enable the helium to be discharged in time, reduce the buoyancy of the hull 1, and realize the rapid landing of the airship, greatly shortening the landing time and improving the safety and response ability of the airship in an emergency.

[0034] In a further preferred embodiment of the present invention, a limiting block 21 is provided on the side of the valve stem 16 away from the handwheel 17. A second spring 23 is installed on the outer wall of the control valve 15 through a fixing plate 22. A limiting plate 24 that can be clamped outside the limiting block 21 for stabilizing the valve stem 16 is installed on the second spring 23. An adjusting assembly for adjusting the position of the limiting plate 24 is provided on the control valve 15.

[0035] In this embodiment, the limiting block 21 is used to cooperate with the limiting plate 24 to limit and stabilize the rotation position of the valve stem 16. When the valve stem 16 rotates to a specific position, the limiting block 21 will interact with the limiting plate 24 to prevent the valve stem 16 from rotating excessively, thereby stabilizing the position of the valve stem 16 and ensuring that the control valve 15 is in a stable open / closed state. The fixing plate 22 is used to fix the second spring 23 and provide an installation support point for the second spring 23, so that the second spring 23 can be stably installed on the control valve 15. In the natural state, the second spring 23 is in a certain compressed or stretched state, applying a force to the limiting plate 24 to enable the limiting plate 24 to be tightly clamped outside the limiting block 21, playing a role in stabilizing the valve stem 16. The setting of the adjustment component enables the position of the limiting plate 24 to be adjusted according to actual needs, thereby changing the rotation range of the valve stem 16 and achieving precise adjustment of the open / closed state of the control valve 15. During the emergency landing process, the helium discharge amount of the control valve 15 can be adjusted in a timely manner according to the landing state and requirements of the airship, improving the accuracy and stability of the airship landing.

[0036] In a further preferred embodiment of the present invention, the adjustment component includes an electromagnet 29 fixed on the control valve 15, a guide rod 27 installed on the limiting plate 24 and passing through the second spring 23, and an iron block 28 fixed on the guide rod 27 and capable of being adsorbed on the electromagnet 29.

[0037] In this embodiment, the electromagnet 29 serves as the power source of the adjustment component. When the electromagnet 29 is energized, it will generate a magnetic force to attract the iron block 28, thereby driving the limiting plate 24 to move and realizing the adjustment of the position of the limiting plate 24. The guide rod 27 plays a role in guiding and supporting. On the one hand, it ensures that the limiting plate 24 maintains a stable movement trajectory during the movement. On the other hand, it enables the second spring 23 to be stably installed between the limiting plate 24 and the fixing plate 22, ensuring that the second spring 23 applies a stable elastic force to the limiting plate 24. When the electromagnet 29 is energized to generate a magnetic force, the iron block 28 will be attracted to move towards the electromagnet 29, driving the guide rod 27 and the limiting plate 24 to move together, changing the relative position between the limiting plate 24 and the limiting block 21, thereby realizing the adjustment of the rotation range of the valve stem 16. The electromagnet 29 has the characteristic of fast response speed. When it is necessary to adjust the position of the limiting plate 24, only by energizing or de-energizing the electromagnet 29, the iron block 28 can be quickly adsorbed or detached from the electromagnet 29, driving the limiting plate 24 to move, and achieving rapid adjustment of the rotation range of the valve stem 16 to meet the rapid response requirement for the adjustment of the control valve 15 during the emergency landing process of the airship.

[0038] In a further preferred embodiment of the present invention, the electromagnet 29 is composed of a connecting plate 30 mounted on the outer wall of the control valve 15, a metal rod 31 mounted on the connecting plate 30, a coil 32 sleeved outside the metal rod 31 for conducting electricity, and a clamping plate 33 fixed on the outer wall of the control valve 15 and sleeved outside the metal rod 31. An insulating sleeve is sleeved outside the coil 32.

[0039] In this embodiment, the electromagnet 29 is a key power component of the adjustment assembly. As a whole, it is composed of a connecting plate 30, a metal rod 31, a coil 32 and a clamping plate 33. By passing an electric current, it generates a magnetic force to attract the iron block 28 and drive the limiting plate 24 to move, so as to realize the adjustment of the rotation range of the valve stem 16. The connecting plate 30 is used to fix one end of the metal rod 31, providing installation support for the electromagnet 29 to ensure that the electromagnet 29 can be stably installed on the control valve 15. The metal rod 31 is the magnetic core part of the electromagnet 29. When the coil 32 is energized, the metal rod 31 will generate a magnetic field and interact with the iron block 28 to realize the attraction function. The coil 32 is used for conducting electricity. When an electric current passes through the coil 32, a magnetic field will be generated around the metal rod 31, making the electromagnet 29 magnetic. An insulating sleeve is sleeved outside the coil 32, playing an insulating and protective role to prevent current leakage and short circuit, ensuring the safe operation of the electromagnet 29. The clamping plate 33 is used to fix and support the other end of the metal rod 31, preventing the metal rod 31 from shaking or shifting under the action of electromagnetic force, and ensuring the structural stability and working reliability of the electromagnet 29.

[0040] In a further preferred embodiment of the present invention, a mesh cover 20 for isolating impurities is installed on the top of the hull 1 and sleeved outside the exhaust pipe 14. The mesh cover 20 is provided with mesh holes allowing air to pass through. A control cabin 5 is provided at the bottom of the hull 1. A radar speedometer for monitoring the speed of the hull 1 is provided in the control cabin 5, and the speed of the hull 1 is monitored to adjust the helium output.

[0041] In this embodiment, the main function of the mesh cover 20 is to isolate external impurities, prevent impurities from entering the inside of the exhaust pipe 14, affect the normal operation of the control valve 15 and the discharge of helium, and ensure the stable operation of the airship emergency landing system. The exhaust pipe 14 is a key component for realizing the helium discharge in the airship emergency landing system. Various control devices and monitoring instruments are installed inside the control cabin 5, which is the control center of the airship. The radar speedometer (Yunjing Tianhe TH-CS5H type radar speedometer) is used to monitor the speed of the hull 1 in real time. By measuring the speed of the hull 1, it can provide data support for subsequent adjustment of the helium output, ensure that the airship can land at a predetermined speed and attitude, improve the safety and stability of the airship flight. When the landing speed of the hull 1 is too fast, the helium discharge speed can be reduced.

[0042] In a further preferred embodiment of the present invention, a damping spring 7 for reducing the impact of the airship landing is installed at the bottom of the control cabin 5, a support frame 8 for supporting the device is installed at the bottom of the damping spring 7, a limit telescopic rod 9 is installed between the support frame 8 and the control cabin 5, and the limit telescopic rod 9 penetrates through the damping spring 7.

[0043] In this embodiment, when the airship lands, the weight and impact force of the airship act on the control cabin 5. The damping spring 7 can undergo elastic deformation to absorb and buffer part of the impact energy, thereby reducing the impact force generated during the airship landing, protecting the equipment in the control cabin 5 and the overall structure of the airship from damage. The support frame 8 is a component that contacts the ground and supports the overall weight of the airship, providing a stable support foundation for the airship to ensure that the airship can be placed stably on the ground after landing. The main function of the limit telescopic rod 9 is to limit and guide the up and down movement of the control cabin 5, prevent the control cabin 5 from shaking or deviating excessively under the action of the damping spring 7, ensure the stable movement trajectory of the control cabin 5, and at the same time ensure that the damping spring 7 maintains vertical movement during compression and rebound, improving the damping effect. The impact energy is converted into the elastic potential energy of the spring through the elastic deformation of the spring and then gradually released, thus greatly reducing the direct action of the impact force on the airship structure and internal equipment, extending the service life of the airship, and ensuring the safety and reliability of the airship. The damping spring 7, the support frame 8, and the limit telescopic rod 9 cooperate with each other to form a complete damping support system. This system can not only effectively reduce the impact during the airship landing but also provide stable support and ensure movement stability, thereby improving the overall performance of the airship emergency landing system and enabling the airship to complete the landing task safely and reliably in various complex environments.

[0044] In a further preferred embodiment of the present invention, a material bin 6 for storing materials is installed on one side of the control cabin 5. A discharge port is provided at the bottom of the material bin 6. A bottom plate 11 for closing the discharge port is hinged at the bottom of the material bin 6. An oil cylinder 10 for adjusting the opening and closing of the bottom plate 11 is hinged on the support frame 8, and the output rod of the oil cylinder 10 is hinged to the bottom plate 11.

[0045] In this embodiment, the material bin 6 is used to store materials, which can be supplies that the airship may need to use during an emergency landing, such as rescue equipment, maintenance tools, etc. The discharge port is the channel for discharging materials. When the descending speed of the airship is too fast to ensure safety, materials can be discharged to slow down the landing speed. Under normal circumstances, the bottom plate 11 is in a closed state to prevent materials from leaking out of the discharge port. When materials need to be discharged, the bottom plate 11 can be opened to allow the materials to be discharged smoothly. The oil cylinder 10 (atos hydraulic cylinder ck40) is the power device for adjusting the opening and closing of the bottom plate 11. By controlling the telescopic movement of the oil cylinder 10, the bottom plate 11 can be driven to rotate around the hinge point to achieve the opening and closing of the discharge port.

[0046] In a further preferred embodiment of the present invention, the support frame 8 is made of carbon fiber composite material. An empty bin 12 for reducing weight is provided inside the support frame 8. A rubber block for assisting in shock absorption is provided at the bottom of the support frame 8, and the rubber block is also used to increase the friction between the equipment and the ground.

[0047] In this embodiment, the support frame 8 is a key component for the airship to contact the ground and support the overall weight of the airship. In this embodiment, it is made of carbon fiber composite material. Carbon fiber composite material has the characteristics of high strength and low density, which can effectively reduce the overall weight of the airship while ensuring the structural strength of the support frame 8, improving the flight performance and load capacity of the airship. The purpose of the empty bin 12 is to further reduce the weight of the support frame 8. By removing some materials to form a hollow structure, without affecting the overall strength and stability of the support frame 8, the load of the airship is reduced, making the airship more lightweight and flexible. The rubber block has a dual function of assisting in shock absorption and increasing the friction between the equipment and the ground. When the airship lands, the rubber block can undergo elastic deformation, absorb and buffer part of the impact energy, and work together with the shock-absorbing spring 7 to further reduce the impact force generated during the airship's landing, protecting the structure and equipment of the airship. At the same time, when the rubber block contacts the ground, the rough texture on its surface can increase the friction with the ground, preventing the airship from sliding or displacing due to wet ground or external forces after landing, improving the stability of the airship after landing. The rubber block increases the friction between the support frame 8 and the ground, enabling the airship to be placed more stably on the ground after landing. Whether on a flat ground or a ground with a certain slope, the rubber block can provide sufficient friction to prevent the airship from sliding or tipping over, improving the stability and safety of the airship after landing, and providing guarantee for the subsequent operation and maintenance of the airship.

[0048] In a further preferred embodiment of the present invention, a flow meter for monitoring the helium discharge speed is provided on the exhaust pipe 14. A chute 25 is provided on the control valve 15. A slider 26 connected to the limit plate 24 is slidably installed in the chute 25, and the chute 25 cooperates with the slider 26 to define the movement path of the limit plate 24.

[0049] In this embodiment, the exhaust pipe 14 serves as the channel for helium discharge in the airship emergency landing system. In this embodiment, a flow meter (RGF series) is installed on the exhaust pipe 14. The main function of the flow meter is to monitor the helium discharge speed in real time, providing key data support for the flight control and emergency landing of the airship. According to the monitoring data of the flow meter, the control system can precisely adjust the helium discharge volume, thereby controlling the landing speed and attitude of the airship. The control valve 15 is an important component in the airship emergency landing system. A sliding groove 25 is provided on the control valve 15. The sliding groove 25 provides a track for the sliding of the slider 26. The function of the sliding groove 25 is to limit the moving direction and range of the slider 26, thereby indirectly limiting the moving path of the limiting plate 24 connected to the slider 26. The sliding of the slider 26 in the sliding groove 25 drives the limiting plate 24 to move. At the same time, the limiting effect of the sliding groove 25 on the slider 26 also ensures the moving accuracy and stability of the limiting plate 24.

[0050] In summary, compared with the related technologies, this device adjusts the buoyancy of the hull 1 by setting the helium gas bag 2 and the air bag 3 in cooperation, precisely controls the helium discharge by using the electric valve 36 and the control valve 15, and changes the traditional way of directly adjusting the air volume inside the hull 1 to adjust the lifting and lowering of the hull 1, which takes a long time for landing. In an emergency, it can quickly reduce the buoyancy of the hull 1, achieve the rapid landing of the airship, greatly shorten the landing time, and improve the safety and response ability of the airship in an emergency. By controlling the opening degree of the electric valve 36, the helium discharge speed can be precisely controlled, thereby realizing the rapid adjustment of the buoyancy of the hull 1. At the same time, the control valve 15 is provided with a valve stem 16 and a valve core. By rotating the valve stem 16, the valve core can be driven to move, realizing the precise adjustment of the opening and closing of the control valve 15. When the airship lands, the damping spring 7 can undergo elastic deformation, absorbing and buffering part of the impact energy, thereby reducing the impact force generated during the landing of the airship. At the same time, the limiting telescopic rod 9 limits and guides the up and down movement of the control cabin 5, preventing the control cabin 5 from shaking or deviating excessively under the action of the damping spring 7. The integrated design is adopted, which is convenient for centralized control of helium output.

[0051] In several embodiments provided by this application, it should be understood that the disclosed device can be implemented in other ways.

[0052] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than limiting the protection scope of the invention. Obviously, the described embodiments are only partial embodiments of the present invention, rather than all embodiments. Based on these embodiments, all other embodiments obtained by those of ordinary skill in the art without creative efforts belong to the scope of protection of the present invention. Although the present invention has been described in detail with reference to the above embodiments, those of ordinary skill in the art can still, without conflict and without creative efforts, combine, add, delete or make other adjustments to the features in the embodiments of the present invention according to the circumstances, so as to obtain different technical solutions that essentially do not deviate from the concept of the present invention, and these technical solutions also belong to the scope of protection of the present invention.

Claims

1. An emergency landing system for an airship, characterized in that, Including: The hull; A helium gas bag and an air bag arranged inside the hull for adjusting the lifting of the hull; A power paddle installed on the hull for providing power for direction adjustment, which consists of a propeller and an electric motor; A conduit fixed on the helium gas bag for passing through the gas flow channel, an integrated shell is provided on the conduit, and a protective shell is sleeved outside the integrated shell; An electric valve arranged on the conduit for adjusting the output of helium; An exhaust pipe installed on the protective shell and extending outside the hull for outputting helium, and a control valve for adjusting the opening and closing of the exhaust pipe is provided on the exhaust pipe.

2. The emergency landing system for an airship according to claim 1, characterized in that, A valve rod is rotatably installed inside the control valve, a valve core for adjusting the opening and closing of the control valve is provided on the valve rod, the valve rod extends outside the control valve, a handwheel is provided on the valve rod, an adjusting plate is installed on the handwheel, and an electric telescopic rod for adjusting the angle of the handwheel is hinged on the outer wall of the hull, and the output rod of the electric telescopic rod is hinged to the adjusting plate.

3. The emergency landing system for an airship according to claim 2, wherein, A limiting block is provided on one side of the valve rod away from the handwheel, a second spring is installed on the outer wall of the control valve through a fixing plate, a limiting plate that can be clamped outside the limiting block for stabilizing the valve rod is installed on the second spring, and an adjusting component for adjusting the position of the limiting plate is provided on the control valve.

4. The emergency landing system for an airship according to claim 3, characterized in that, The adjusting component includes an electromagnet fixed on the control valve, a guide rod installed on the limiting plate and passing through the second spring, and an iron block fixed on the guide rod and capable of being adsorbed on the electromagnet.

5. The emergency landing system for an airship according to claim 4, characterized in that, The electromagnet consists of a connecting plate installed on the outer wall of the control valve, a metal rod installed on the connecting plate, a coil sleeved outside the metal rod for conducting electricity, and a clamping plate fixed on the outer wall of the control valve and sleeved outside the metal rod, and an insulating sleeve is sleeved outside the coil.

6. The emergency landing system for an airship according to claim 2, characterized in that, A mesh cover for isolating impurities is installed on the top of the hull and sleeved outside the exhaust pipe, the mesh cover is provided with mesh holes allowing air to pass through, a control cabin is provided at the bottom of the hull, and a radar speedometer for monitoring the speed of the hull is provided inside the control cabin, and the speed of the hull is monitored to adjust the output amount of helium.

7. The emergency landing system for an airship according to claim 6, characterized in that, A damping spring for reducing the impact of the airship landing is installed at the bottom of the control cabin, a support frame for the device is installed at the bottom of the damping spring, and a limiting telescopic rod is installed between the support frame and the control cabin, and the limiting telescopic rod penetrates through the damping spring.

8. The emergency landing system for an airship according to claim 7, characterized in that, A material bin for storing materials is installed on one side of the control cabin, a discharge port is provided at the bottom of the material bin, a bottom plate for closing the discharge port is hinged at the bottom of the material bin, and an oil cylinder for adjusting the opening and closing of the bottom plate is hinged on the support frame, and the output rod of the oil cylinder is hinged to the bottom plate.

9. The emergency landing system for an airship according to claim 7, wherein, The support frame is made of carbon fiber composite material, an empty bin for reducing weight is provided inside the support frame, a rubber block for assisting in shock absorption is provided at the bottom of the support frame, and the rubber block is also used to increase the friction between the device and the ground.

10. The emergency landing system for an airship according to claim 3, characterized in that, A flowmeter for monitoring the helium emission rate is provided on the exhaust pipe. A sliding groove is provided on the control valve, and a slider connected to the limiting plate is slidably installed in the sliding groove. The sliding groove cooperates with the slider to define the movement path of the limiting plate.

Images