Hybrid energy power low-altitude airship for pipe network line patrol

Abstract

The utility model relates to the technical field of low-altitude aircrafts, and provides a hybrid energy power low-altitude airship for pipe network line patrol, comprising: a capsule system comprising a main capsule; the energy system comprises a solar cell panel arranged at the top of the main capsule body, and a battery pack and / or a fuel generator arranged in a pod at the bottom of the main capsule body; the load system is arranged on the front side abdomen of the main capsule body and comprises a self-stabilizing holder and a task load; the flight control system and the communication system are both installed in the pod. The solar panel and the battery pack / fuel generator can continuously supply energy under the conditions of sufficient and insufficient illumination, the capsule system has high buoyancy, different loads can be carried, the routing inspection of the loads is controlled through the self-stabilizing holder, and in addition, the carried communication system can communicate in real time. The hybrid energy power low-altitude airship has the advantages of high load, high endurance continuous operation and suitability for multi-region scenes.

Description

Technical Field

[0001] The present application relates to a low-altitude aircraft, and in particular to a hybrid energy-powered low-altitude airship used for pipeline network inspection. Background Art

[0002] In order to ensure the safety of natural gas and oil pipelines, daily inspections are required along the pipelines to prevent illegal construction or natural disasters that may damage or expose the pipelines, thereby causing safety risks.

[0003] At present, the main methods of pipeline inspection include manual inspection, fiber optic vibration detection, elevated electronic fence monitoring and drone inspection. Manual inspection is slow, has blind spots in time and space, and is difficult to inspect pipelines in remote areas such as mountains; fiber optic vibration detection has a high false alarm rate, and it is impossible to clarify the specific risk situation of the pipeline on site; elevated electronic fence monitoring relies on the existing elevated layout near the pipeline, and is limited by the location of the elevated point and the monitoring distance, so the monitoring range is limited; the poor energy storage capacity of drones leads to low effective operation time throughout the day, and the limited load capacity, and it is impossible to carry multiple loads such as visible light, infrared, and laser at the same time to achieve all-weather monitoring, and can only carry light 4G communication equipment, resulting in poor communication quality and poor data timeliness. Some drones also have the disadvantages of not being able to take off and land vertically and having strict requirements on terrain.

[0004] In summary, the existing means of pipeline inspection are insufficient, and there are technical problems such as poor timeliness, limited detection range, limited load capacity, poor continuous operation capability, and terrain restrictions. Utility Model Content

[0005] In order to solve or partially solve the problems existing in the related technology, the present application provides a hybrid energy powered low-altitude airship for pipeline inspection, which can be used in multiple scene areas, carry multiple mission payloads, maintain long-term endurance, and ensure good real-time communication.

[0006] The utility model provides a hybrid energy powered low altitude airship for pipeline network inspection, comprising:

[0007] The capsule system includes a main capsule;

[0008] An energy system, including a solar panel arranged on the top of the main capsule, and a battery pack and / or a fuel generator arranged in a pod at the bottom of the main capsule;

[0009] A load system is arranged on the front belly of the main bag body, and the load system includes a self-stabilizing gimbal and a mission load;

[0010] A flight control system, installed in the pod, for achieving flight control;

[0011] A communication system is installed in the pod.

[0012] Optionally, the balloon system includes a main balloon and at least one auxiliary airbag.

[0013] Optionally, the solar cell panel adopts a flexible structure.

[0014] Optionally, the fuel generator is installed on the center of buoyancy / center of gravity axis of the entire airship.

[0015] Optionally, the mission payload includes an optoelectronic payload, a lighting payload and / or a broadcasting payload.

[0016] Optionally, the communication system includes: 4 / 5G communication equipment, microwave communication equipment and / or high-bandwidth satellite communication equipment.

[0017] Optionally, it also includes a propulsion system;

[0018] The propulsion system includes a power support, a propulsion motor, a propeller and a vector servo; the root of the power support is fixedly connected to the main capsule; the propulsion motor is fixedly connected to the top of the power support through the vector servo; and the propeller is connected to the propulsion motor.

[0019] Optionally, the tail system of the airship is installed at the tail of the main capsule, and the tail system includes two vertical tails and two horizontal tails forming a cross configuration.

[0020] Optionally, the structure of any of the vertical tails is the same as the structure of any of the horizontal tails.

[0021] Optionally, any vertical tail or horizontal tail in the tail system specifically includes: a stabilizer surface fixedly connected to the main bladder and a rudder surface movably connected to the stabilizer surface.

[0022] The hybrid energy-powered low-altitude airship for pipeline inspection provided by the present application adopts hybrid power. The solar panels and battery packs / fuel generators can continue to function in sufficient or insufficient light conditions, and can fly uninterruptedly for several months. Because the capsule system has strong buoyancy, it can carry different loads and control the inspection of the load through a self-stabilizing gimbal. In addition, the communication system carried can communicate in real time. The hybrid energy-powered low-altitude airship of the present application has the advantages of high load capacity, high flight time continuous operation, and is suitable for multi-regional scenarios.

[0023] It should be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The above and other objects, features and advantages of the present application will become more apparent by describing in more detail exemplary embodiments of the present application in conjunction with the accompanying drawings, wherein the same reference numerals generally represent the same components in the exemplary embodiments of the present application.

[0025] Figure 1 This is a schematic diagram of the structure of a hybrid energy-powered low-altitude airship for pipeline network inspection shown in an embodiment of the present application;

[0026] Figure 2 It is a schematic diagram of a capsule system of a hybrid energy-powered low-altitude airship for pipeline network inspection shown in an embodiment of the present application;

[0027] Figure 3 This is a schematic diagram of a tail system of a hybrid energy-powered low-altitude airship for pipeline network inspection in an embodiment of the present application;

[0028] Figure 4 is a schematic diagram of a propulsion system of a hybrid energy-powered low-altitude airship for pipeline network inspection according to an embodiment of the present application;

[0029] Figure 5 is a schematic diagram of a load system of a hybrid energy-powered low-altitude airship for pipeline network inspection in an embodiment of the present application;

[0030] In the figure: the capsule system 1, the main capsule 11, the auxiliary airbag 12; the tail system 2, the stabilizer 21, the control surface 22; the propulsion system 3, the power support 31, the vector steering gear 32, the propulsion motor 33, the propeller 34; the energy system 4; the flight control system 5; the communication system 6; the payload system 7, the gimbal 71, the mission payload 72. DETAILED DESCRIPTION

[0031] The embodiments of the present application will be described in more detail below with reference to the accompanying drawings. Although the embodiments of the present application are shown in the accompanying drawings, it should be understood that the present application can be implemented in various forms and should not be limited by the embodiments described herein. On the contrary, these embodiments are provided to make the present application more thorough and complete, and to fully convey the scope of the present application to those skilled in the art.

[0032] It should be understood that although the terms "first", "second", "third", etc. may be used in this application to describe various information, this information should not be limited to these terms. These terms are only used to distinguish the same type of information from each other. For example, without departing from the scope of this application, the first information may also be referred to as the second information, and similarly, the second information may also be referred to as the first information. Thus, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of this application, the meaning of "multiple" is two or more, unless otherwise clearly and specifically defined.

[0033] In the description of the present application, it should be understood that the terms "length", "width", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do 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 therefore should not be understood as a limitation on the present application.

[0034] Unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, or a detachable connection or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0035] The existing pipeline inspection methods have problems such as poor timeliness, limited detection range, limited load capacity, poor continuous operation capability, and terrain restrictions.

[0036] In response to the above problems, an embodiment of the present application provides a hybrid energy-powered low-altitude airship for pipeline inspection, which can achieve real-time communication, long-term endurance, and carry one or more payloads at the same time.

[0037] The technical solution of the embodiments of the present application is described in detail below with reference to the accompanying drawings.

[0038] like Figure 1 As shown, a hybrid energy powered low-altitude airship used for pipeline inspection includes a capsule system 1, a tail wing system 2, a propulsion system 3, an energy system 4, a flight control system 5, a communication system 6 and a payload system 7.

[0039] See also Figure 2 , Figure 2 It is a schematic diagram of the bladder system of a hybrid energy-powered low-altitude airship for pipeline inspection shown in an embodiment of the present application, wherein the bladder system 1 consists of an external main bladder 11 and an internal auxiliary airbag 21. The main bladder 11 is filled with helium to provide buoyancy; the main bladder adopts a low-resistance shape design, is 16m long, has a maximum diameter of 5m, and has a hull shape resistance coefficient of 0.03.

[0040] The internal auxiliary airbag 21 can be inflated and discharged to adjust the buoyancy when the airship changes in altitude and fuel. The internal auxiliary airbag is set in the abdomen of the main bladder body and consists of two front and rear airbags. During use, the buoyancy balance under different altitudes and fuel loss is adjusted by inflating and discharging air in the auxiliary airbag. The auxiliary airbag adopts a compartment design. The auxiliary airbag compartment and the abdominal main bladder skin form a closed space for the auxiliary airbag; the compartment adopts a 40μm thick TPU-PVDF-TPU co-extruded film, which is light in weight and has high helium barrier properties; it reduces the weight of the auxiliary airbag itself and improves the platform's effective load capacity.

[0041] Please continue to combine Figure 3 , Figure 3 This is a schematic diagram of the tail system of a hybrid energy-powered low-altitude airship for pipeline inspection in an embodiment of the present application. The tail system 2 is installed at the tail of the main capsule 11, and is composed of four tails, including two upper and lower vertical tails and two left and right horizontal tails, to maintain the pitch and yaw stability of the airship, perform pitch and heading control and adjustment of the airship, and enhance the pitch and yaw stability of the airship. The bottom of the tail stabilizer is fixed to the main capsule skin, and the pitch and heading adjustment of the airship is achieved through the control of the tail rudder surface.

[0042] The vertical tail and the horizontal tail adopt the same structure. Each tail surface is composed of a stabilizer 21 and a rudder 22. The bottom of the stabilizer 21 is fixedly connected to the main bladder 11. The rudder 22 can adjust the attitude of the airship by rotating left or right or up and down. The area of ​​the tail rudder accounts for more than 1 / 3 of the total area of ​​the tail. The large area of ​​the rudder enhances the attitude adjustment and control ability of the airship. The tail airfoil uses NACA0010, which has a low drag coefficient.

[0043] Please continue to combine Figure 4 , Figure 4 This is a schematic diagram of the propulsion system of a hybrid energy-powered low-altitude airship for pipeline inspection shown in an embodiment of the present application. The propulsion system 3 is installed on the side of the main capsule 11 and can be composed of four groups of propulsion devices. Each group of propulsion devices can include a power bracket 31, a vector steering gear 32, a propulsion motor 33, and a propeller 34. The root of the power bracket 31 is connected to the main capsule 11 and extends outward; the vector steering gear 32 is installed on the power bracket 31 and connected to the propulsion motor 33, which can drive the propulsion motor 33 to rotate around the horizontal power bracket 31, change the direction of the propulsion motor 33, and realize the adjustment of different flight thrust directions when the airship takes off, lands, and cruises. The vector steering gear can adjust the thrust direction of the motor and propeller. When the airship rises or descends, the vector steering gear adjusts the thrust to an upward or facing state. When the airship is cruising or staying against the wind, the vector steering gear adjusts the thrust to a horizontal direction.

[0044] The energy system 4 is composed of a solar panel, a battery pack and a fuel generator. The solar panel adopts a flexible structure and is arranged and installed close to the top of the main capsule 11. During the day, it can absorb solar energy to generate electricity to power various systems of the airship, and store excess electricity in the battery pack; the battery pack and the fuel generator are installed in the nacelle of the belly of the capsule, and the generator is installed on the buoyancy center (center of gravity) line of the airship to ensure the overall pitch stability of the airship when fuel is consumed. During the day, when there is sufficient sunshine, the power generated by the solar panel meets the power needs of the airship propulsion system and flight control system, and charges the battery pack for energy storage; at night, the battery pack provides the energy needs for flight control. In this way, the energy required by the airship is circulated day and night to achieve long-term uninterrupted flight. The fuel generator set is used for energy supply in rainy weather with insufficient sunlight. Under the condition of sufficient sunshine, uninterrupted continuous flight for several months can be achieved; when there is insufficient sunshine, the fuel generator set can also be used to achieve the flight time level of ordinary airships.

[0045] The solar panels adopt a flexible structure, with a power generation capacity of up to 200W / ㎡, and are laid on the top of the main airship capsule to ensure the power generation efficiency to the greatest extent. The battery pack adopts semi-solid batteries, which are installed in the pod at the bottom of the capsule and have an energy density of 260Wh / kg after packaging.

[0046] The flight control system 5 and the communication system 6 are installed in the pod at the belly of the capsule. The flight control system 5 can realize the automatic take-off, line patrol, fixed-point hovering and landing of the airship, and can also be remotely controlled manually through the communication system 6.

[0047] Communication system 6 consists of 4 / 5G communication equipment, microwave communication equipment and high-bandwidth satellite communication equipment, and has three communication methods, which can choose to switch communication links according to different mission scenarios. Among them, 4 / 5G communication is suitable for urban areas with good mobile signals, microwave communication is suitable for grasslands and Gobi deserts, and high-bandwidth satellite communication is suitable for remote and uninhabited mountainous areas, which can meet the needs of different usage environments.

[0048] The load system 7 consists of a pan-tilt platform 71 and a mission load 72. The pan-tilt platform 71 is installed on the front abdomen of the main capsule 11, and can realize the horizontal rotation and pitch rotation control of the mission load 72. The installation interface of the load system adopts a self-stabilizing pan-tilt design, which can be controlled by 360° horizontally and 90° downward in pitch, and has a self-stabilizing function, which is suitable for a variety of loads. The mission load can be equipped with one or more loads such as photoelectric loads, lighting loads, and shouting loads as needed to realize pipeline risk inspection, night risk point lighting, and timely handling of risk point shouting.

[0049] The working process of the utility model is introduced below.

[0050] According to the patrol mission, the flight route is set, and the flight control system controls the airship to perform the mission according to the input route. During the launch phase, the vector servo rotates the propulsion motor to the upward direction, and the motor drives the propeller to rotate to generate upward lift, and the airship takes off; during the launch process, as the airship rises in altitude, the gas inside the main capsule expands, and the auxiliary airbag discharges air to maintain the pressure of the airship capsule; after the airship reaches the patrol altitude, the vector servo rotates the propulsion motor to the horizontal direction, and the motor drives the propeller to rotate to generate horizontal thrust, so as to achieve the patrol flight of the airship; when the airship lands, the vector servo rotates the propulsion motor to the downward direction, generating downward thrust, and as the altitude decreases, the gas inside the main capsule contracts, and the auxiliary airbag is filled with air to maintain the shape of the main capsule of the airship.

[0051] The solar panels on top of the capsule generate electricity during daytime cruising, providing energy consumption for propulsion, control and communication, and fully storing energy in the battery pack; the battery pack provides power for nighttime cruising; in the event of insufficient sunlight such as cloudy and rainy weather, the fuel generator can generate electricity for emergency energy supply.

[0052] The airship platform carries multiple payloads at the same time. During the line inspection process, the airship can use the optoelectronic payload to transmit the images taken near the pipeline to the ground monitoring hall in real time through the communication system, and rely on the automatic identification function to detect and report risk points such as construction vehicles. Therefore, ground monitoring personnel can manually control the airship and payload to conduct airborne inspections of risk points based on the reported risks. During the night line inspection process, after the airship detects safety risks through the infrared optoelectronic payload, it illuminates the risk points through the lighting payload to conduct risk inspections. If risks are detected, they can be remotely shouted or directed through the shouting payload to stop risky behaviors on site in time.

[0053] The scheme of the present application has been described in detail above with reference to the accompanying drawings. In the above embodiments, the descriptions of the various embodiments have their own emphasis. For parts that are not described in detail in a certain embodiment, reference can be made to the relevant descriptions of other embodiments. Those skilled in the art should also be aware that the actions and modules involved in the specification are not necessarily required for the present application. In addition, it can be understood that the steps in the method of the embodiment of the present application can be adjusted in order, merged and deleted according to actual needs, and the modules in the device of the embodiment of the present application can be merged, divided and deleted according to actual needs.

[0054] The embodiments of the present application have been described above, and the above description is exemplary, not exhaustive, and is not limited to the disclosed embodiments. Many modifications and changes will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments. The selection of terms used herein is intended to best explain the principles of the embodiments, practical applications, or improvements to the technology in the market, or to enable other persons of ordinary skill in the art to understand the embodiments disclosed herein.

Claims

1. A hybrid energy powered low altitude airship for pipeline inspection, characterized in that: include: The capsule system includes a main capsule; An energy system, including a solar panel arranged on the top of the main capsule, and a battery pack and / or a fuel generator arranged in a pod at the bottom of the main capsule; A load system is arranged on the front belly of the main bag body, and the load system includes a self-stabilizing gimbal and a mission load; A flight control system, installed in the pod, for achieving flight control; A communication system is installed in the pod.

2. The hybrid energy powered low altitude airship according to claim 1, characterized in that: The balloon system further includes at least one auxiliary airbag.

3. The hybrid energy powered low altitude airship according to claim 1, characterized in that: The solar cell panel adopts a flexible structure.

4. The hybrid energy powered low altitude airship according to claim 1, characterized in that: The fuel generator is installed on the buoyancy center line / gravity center line of the entire airship.

5. The hybrid energy powered low altitude airship according to claim 1, characterized in that: The mission payload includes an optoelectronic payload, a lighting payload and / or a broadcasting payload.

6. The hybrid energy powered low altitude airship according to claim 1, characterized in that: The communication system includes: 4 / 5G communication equipment, microwave communication equipment and / or high-bandwidth satellite communication equipment.

7. The hybrid energy powered low altitude airship according to claim 1, characterized in that: It also includes the propulsion system; The propulsion system includes a power support, a propulsion motor, a propeller and a vector servo; the root of the power support is fixedly connected to the main capsule; the propulsion motor is fixedly connected to the top of the power support through the vector servo; and the propeller is connected to the propulsion motor.

8. The hybrid energy powered low altitude airship according to claim 1, characterized in that: The tail system of the airship is installed at the tail of the main capsule, and the tail system includes two vertical tails and two horizontal tails forming a cross configuration.

9. The hybrid energy powered low altitude airship according to claim 8, characterized in that: The structure of any of the vertical tails is the same as the structure of any of the horizontal tails.

10. The hybrid energy powered low altitude airship according to claim 8, characterized in that: Any vertical tail or horizontal tail in the tail system specifically includes: a stabilizer surface fixedly connected to the main bladder and a rudder surface movably connected to the stabilizer surface.

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