Aircraft provided with detachable hybrid power module

Abstract

The invention discloses an aircraft assembled with a detachable hybrid power module, relates to the technical field of unmanned aerial vehicles, and solves the problem that the unmanned aerial vehicle is difficult to realize quick response and operate in a complex environment for a long time under the influence of environmental factors, the oil-electricity hybrid power module comprises a starter, a fuel engine, a generator and a power supply device, the starter is used for starting the fuel engine, the fuel engine is used for driving the generator to operate, the generator is used for charging the power supply device, and the power supply device is used for supplying power to the aircraft body and the starter; the fuel engine is used for guaranteeing the working temperature of the four rotors; through waste heat utilization and multifunctional integration, the endurance mileage of the aircraft is increased, waste heat generated by emission of the fuel engine is used for providing a heat preservation function for the four rotor wings, the problem that the performance of the rotor wings of the aircraft is reduced in a low-temperature environment is effectively solved, and the flight safety and stability are guaranteed.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and particularly to an aircraft equipped with a detachable hybrid power module. Background Art

[0002] Long endurance is of high importance for multiple application scenarios. In emergency rescue scenarios, the aircraft needs to respond quickly and operate in complex environments for a long time. For example, during mountain earthquake rescue, it is necessary to quickly reach the disaster area, accurately deliver supplies, transfer the wounded, etc. Insufficient endurance will cause the aircraft to be unable to stay in the disaster area for a long time, affecting the rescue progress; unstable power may make it difficult for the aircraft to fly stably in a complex airflow environment and unable to accurately execute tasks. In the field of logistics distribution, especially for logistics transportation in remote areas, the aircraft needs to complete cargo transportation efficiently and stably. Long endurance can reduce the number of mid-course refueling times, improve distribution efficiency, and reduce operating costs; in addition, in scenarios such as geographical mapping and border patrol, the demand for long-term and large-scale stable flight of the aircraft also poses higher requirements on the power system. The specific requirements are as follows:

[0003] Power guarantee requirements in harsh environments: In scenarios such as emergency rescue and operations in remote areas, the aircraft often faces harsh environments, such as low temperature and strong wind. Traditional power systems are prone to power attenuation and unstable performance in such environments, making it difficult to ensure the stable operation of the aircraft.

[0004] The requirement of balancing endurance and environmental protection: With the increasing demand for environmental protection and the long-term operation of the aircraft, pure fuel power has high pollution, and pure electric power has short endurance. Existing single power forms are difficult to balance endurance and environmental protection requirements.

[0005] The requirement for flexible maintenance and upgrade of the power system: The power system of traditional aircraft is usually designed as an integral type. When a fault occurs, it is difficult to repair, with a long repair period, and it is also difficult to be flexibly upgraded according to mission requirements. In practical applications, to improve the utilization efficiency of the aircraft and reduce operating costs, the power system needs to have the characteristics of being easy to maintain and flexibly upgradeable.

[0006] The requirement for efficient energy utilization and multi-function: During the operation of the aircraft, efficient energy utilization is crucial. At the same time, the aircraft has diverse power requirements in different flight stages and mission scenarios. Existing power systems often have low energy utilization efficiency and single functions, unable to meet the diverse power requirements of the aircraft.

[0007] Limitations of the prior art: Refer to similar technical solutions such as CN106515705A, CN206394624U, etc.; Traditional fuel-powered systems rely solely on fuel engines as the power source, generating power by burning fuel to drive the aircraft. Its technology is relatively mature, with a relatively direct power output, and is widely used in some large aircraft. In the application of aircraft, traditional fuel-powered systems consume a large amount of fuel, resulting in high operating costs. At the same time, the pollutants emitted are not environmentally friendly, and their use is restricted in some areas with high environmental protection requirements. Moreover, fuel engines are difficult to start in special environments such as low temperature and high altitude, and the power output will be significantly attenuated, affecting the normal operation of the aircraft.

[0008] Pure electric power systems use batteries as the energy source, converting electrical energy into mechanical energy through electric motors to drive the aircraft. They have advantages such as environmental friendliness and low noise, and are widely used in the field of small unmanned aerial vehicles. Although pure electric power systems are environmentally friendly, their low energy density is a key shortcoming. This results in a short flight range of the aircraft, unable to meet the requirements of long-distance flight missions. Moreover, the charging time is long, making it difficult to achieve rapid turnover and having low efficiency in actual applications. In addition, the battery performance is greatly affected by temperature, with the battery power dropping rapidly in cold environments and even unable to work properly, severely limiting the usage scenarios of pure electric powered aircraft.

[0009] Lack of independent fuel and independent electric power solutions: In existing aircraft power systems, independent fuel-powered and independent electric-powered solutions generally lack comprehensive adaptability to various application scenarios. Independent fuel power is difficult to solve environmental protection and high-cost problems and cannot be used in some areas with strict environmental protection requirements; independent electric power, due to its short endurance and large temperature influence, cannot meet the mission requirements in long-distance and complex environments.

[0010] The simple fuel-electric hybrid solution only simply combines a fuel engine and an electric motor without in-depth optimization design. It lacks intelligent control in power distribution and usually relies on a single power source under a certain working condition, without achieving efficient coordination between the two. Some existing simple fuel-electric hybrid systems have low integration and poor collaborative working ability of each component. The power switching process is not smooth enough, prone to power interruption or fluctuation, affecting the flight stability of the aircraft. Its energy management strategy is not intelligent enough to accurately distribute the power output of the fuel engine and the electric motor according to the real-time state of the aircraft and mission requirements, resulting in low energy utilization efficiency and unable to fully utilize the advantages of fuel-electric hybrid. Lack of intelligent energy management and flexible switching solutions: Currently, most fuel-electric hybrid systems lack intelligent energy management mechanisms and flexible power switching strategies. They often cannot accurately and real-time distribute the power output of the fuel engine and the electric motor according to the real-time flight state of the aircraft (such as speed, altitude, load, etc.) and environmental conditions (such as temperature, wind speed, etc.). During power switching, power interruption or fluctuation is also prone to occur. Summary of the Invention

[0011] In view of the problem that it is difficult for the above-mentioned unmanned aerial vehicle to achieve rapid response and operate in a complex environment for a long time under the influence of environmental factors, the purpose of the present invention is to provide a modular power system with a hybrid fuel and electricity to meet the reliable operation requirements of the aircraft in a complex environment, achieve the balance between endurance and environmental protection, facilitate maintenance and upgrade, and improve energy utilization efficiency and versatility.

[0012] In order to achieve the above purpose, the technical solution adopted by the present invention is as follows:

[0013] An aircraft equipped with a detachable hybrid power module, which includes: an aircraft body, a connecting pipe 4, and a hybrid fuel and electricity power module 5. The hybrid fuel and electricity power module 5 is detachably installed on the aircraft body. The hybrid fuel and electricity power module 5 includes: a starter, a fuel engine 51, a generator 54, and a power supply device. The starter is used to start the fuel engine 51. The fuel engine 51 is used to drive the generator 54 to operate. The generator 54 is used to charge the power supply device. The power supply device is used to supply power to the aircraft body and the starter. The aircraft body includes: four rotors 6. The exhaust port of the fuel engine 51 is respectively communicated with the four rotors 6 through four connecting pipes 4. The fuel engine 51 is used to ensure the working temperature of the four rotors 6.

[0014] The above-mentioned aircraft equipped with a detachable hybrid power module, wherein the aircraft body includes: an upper fixed wing 1, a lower fixed wing 2, and four connecting rods 3. The four connecting rods 3 are divided into two front and rear connecting rod groups. The two connecting rods 3 of each connecting rod group are symmetrically arranged left and right. An upper fixed wing 1, a lower fixed wing 2, and the two connecting rod groups are hinged to form a parallelogram connecting rod mechanism.

[0015] The above-mentioned aircraft equipped with a detachable hybrid power module, wherein the upper wing surface 11 of the upper fixed wing 1 of the upper fixed wing 1 is an arc-shaped wing surface, the lower wing surface 12 of the upper fixed wing 1 of the upper fixed wing 1 is a streamlined wing surface, and four upper fixed wing hinge supports 13 are provided on the lower wing surface 12 of the upper fixed wing 1. The upper end of each upper fixed wing hinge support 13 and a connecting rod 3 are hinged through a hinge shaft.

[0016] The above-mentioned aircraft equipped with a detachable hybrid power module, wherein the upper wing surface 21 of the lower fixed wing 2 of the lower fixed wing 2 is an arc-shaped wing surface, the lower wing surface 22 of the lower fixed wing 2 of the lower fixed wing 2 is a streamlined wing surface, and four lower fixed wing hinge supports 23 are provided on the upper wing surface 21 of the lower fixed wing 2. The lower end of each lower fixed wing hinge support 23 and a connecting rod 3 are hinged through a hinge shaft.

[0017] The above-mentioned aircraft equipped with a detachable hybrid power module, further comprising: a bottom plate 8, the left and right ends of the bottom plate 8 are respectively connected to two link rods 3 of the rear link rod group, and the hybrid power module 5 is detachably mounted on the bottom plate 8.

[0018] The above-mentioned aircraft equipped with a detachable hybrid power module, wherein the hybrid power module 5 further comprises: a fuel tank 52, and the fuel tank 52 is used for supplying fuel to the fuel engine 51.

[0019] The above-mentioned aircraft equipped with a detachable hybrid power module, further comprising: a propeller 7, a power output shaft 53 is provided at the rear side of the fuel engine 51, the propeller 7 is mounted on the power output shaft 53, and the fuel engine 51 is used for driving the propeller 7 to rotate around the axis of the power output shaft 53.

[0020] The above-mentioned aircraft equipped with a detachable hybrid power module, wherein a plurality of connection pipe interfaces 55 communicating with the exhaust ports of the fuel engine 51 are provided on the hybrid power module 5, each connection pipe interface 55 is detachably connected to a connection pipe 4, and a switchable valve is mounted on each connection pipe interface 55.

[0021] The above-mentioned aircraft equipped with a detachable hybrid power module, wherein two rotors 6 symmetrically arranged left and right are mounted on the front side edges of the upper fixed wing 1 and the lower fixed wing 2, and each rotor 6 comprises: a rotor motor and a six-blade propeller, the rotor motor is mounted on the upper fixed wing 1 or the lower fixed wing 2, and each six-blade propeller is mounted on the output end of a rotor motor.

[0022] The above-mentioned aircraft equipped with a detachable hybrid power module, wherein a plurality of snap-in slots 56 are provided on the hybrid power module 5, each rotor motor is detachably electrically connected to a snap-in slot 56, and a power supply device is used for supplying power to the plurality of rotors 6.

[0023] Due to the adoption of the above-mentioned technology, the positive effects of the present invention compared with the prior art are:

[0024] (1) The present invention improves the endurance and environmental protection performance of the aircraft. The hybrid fuel and electric mode combines the advantages of long endurance of fuel power and cleanliness of electric power. Compared with the traditional pure fuel power, it reduces fuel consumption and pollutant emissions, and is more environmentally friendly; compared with pure electric power, it greatly improves the endurance mileage, enabling the aircraft to operate stably and durably in tasks such as remote area logistics distribution and long-distance emergency rescue, effectively expanding the application range of the aircraft.

[0025] (2) The present invention is convenient. It adopts a detachable modular design. In terms of maintenance, when a certain component fails, the corresponding module can be quickly disassembled and replaced, greatly shortening the maintenance time and reducing the maintenance cost. In terms of upgrading, the modules can be flexibly replaced or upgraded according to different task requirements, improving the versatility and maintainability of the power system, which is difficult to achieve for traditional integrated power systems.

[0026] (3) In the present invention, through waste heat utilization and multi-functional integration, the waste heat generated by the fuel engine emissions is innovatively used to provide a heat preservation function for the four rotors, effectively solving the problem of the decline in rotor performance of the aircraft in low-temperature environments and ensuring flight safety and stability. At the same time, the self-mounted propeller in the center of the hybrid fuel-electric module can provide auxiliary lift, enhancing the load capacity of the aircraft and realizing the efficient utilization of energy and the integrated expansion of functions. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a schematic structural view of an aircraft equipped with a detachable hybrid power module of the present invention.

[0028] Figure 2 It is a front view of an aircraft equipped with a detachable hybrid power module of the present invention.

[0029] Figure 3 It is a rear view of an aircraft equipped with a detachable hybrid power module of the present invention.

[0030] Figure 4 It is a top view of an aircraft equipped with a detachable hybrid power module of the present invention.

[0031] Figure 5 It is a right view of an aircraft equipped with a detachable hybrid power module of the present invention.

[0032] Figure 6 It is a schematic structural view of the upper fixed wing of an aircraft equipped with a detachable hybrid power module of the present invention.

[0033] Figure 7 It is Figure 6 a side view of

[0034] Figure 8 It is a schematic structural view of the lower fixed wing of an aircraft equipped with a detachable hybrid power module of the present invention.

[0035] Figure 9 It is Figure 8 a side view of

[0036] Figure 10 It is a schematic structural view of the hybrid fuel-electric module of an aircraft equipped with a detachable hybrid power module of the present invention.

[0037] Figure 11 is Figure 10 a side view of.

[0038] Figure 12 is a schematic structural view of a propeller of an aircraft equipped with a detachable hybrid power module of the present invention.

[0039] In the drawings: 1, upper fixed wing; 2, lower fixed wing; 3, connecting rod; 4, connecting pipe; 5, oil-electric hybrid power module; 6, rotor; 7, propeller; 8, bottom plate; 11, upper wing surface of upper fixed wing; 12, lower wing surface of upper fixed wing; 13, hinge support of upper fixed wing; 21, upper wing surface of lower fixed wing; 22, lower wing surface of lower fixed wing; 23, hinge support of lower fixed wing; 51, fuel engine; 52, fuel tank; 53, power output shaft; 54, generator; 55, connecting pipe interface; 56, snap-in slot; 57, clutch shifting transmission device. Specific embodiments

[0040] The present invention will be further described below with reference to the drawings and specific embodiments, but it is not limited to the present invention.

[0041] Please refer to Figures 1 to 12 as shown, an aircraft equipped with a detachable hybrid power module is shown, which includes: an aircraft body, a connecting pipe 4, and an oil-electric hybrid power module 5. The oil-electric hybrid power module 5 is detachably installed on the aircraft body. The oil-electric hybrid power module 5 includes: a starter, a fuel engine 51, a generator 54, and a power supply device. The starter is used to start the fuel engine 51. The fuel engine 51 is used to drive the generator 54 to operate. The generator 54 is used to charge the power supply device. The power supply device is used to supply power to the aircraft body and the starter; the aircraft body includes: four rotors 6. The exhaust ports of the fuel engine 51 are respectively communicated with the four rotors 6 through four connecting pipes 4. The fuel engine 51 is used to ensure the working temperature of the four rotors 6; the power supply device is a battery;

[0042] Furthermore, in a preferred embodiment, when the aircraft body needs to work for a long time, the battery may have a problem of insufficient power during long-term power supply. In the present invention, the control system controls the starter to start the fuel engine 51 to work, and then drives the generator 54 to work. The generator 54 charges the battery to maintain the power of the battery, so that the aircraft body can work for a long time;

[0043] Further, in a preferred embodiment, when the aircraft body needs to operate in a low-temperature environment, under the influence of low temperature, the chemical reaction of the battery slows down, resulting in a decline in battery performance. The low-temperature environment also reduces the power output of the rotor motor, leading to an extended startup time of the rotor 6. In the present invention, the control system can control the starter to start the fuel engine 51. During the operation of the fuel engine 51, heat is generated, which increases the working temperature of the battery environment and preheats the rotor 6, raising the working temperature of the rotor 6. This ensures that the battery can be stably charged and discharged, guarantees the stable startup of the four rotors 6, and maintains the stable operation of the aircraft body. After the aircraft is in flight, the fuel engine 51 can still ensure that the battery and the four rotors 6 are within a reasonable working temperature range.

[0044] Further, in a preferred embodiment, the aircraft body includes: an upper fixed wing 1, a lower fixed wing 2, and four connecting rods 3. The four connecting rods 3 are divided into two front and rear connecting rod groups. The two connecting rods 3 of each connecting rod group are symmetrically arranged left and right. An upper fixed wing 1, a lower fixed wing 2, and the two connecting rod groups are hinged to form a parallelogram connecting rod mechanism.

[0045] Further, in a preferred embodiment, the upper wing surface 11 of the upper fixed wing 1 is an arc-shaped wing surface, and the lower wing surface 12 of the upper fixed wing 1 is a streamlined wing surface. Four upper fixed wing hinge supports 13 are provided on the lower wing surface 12 of the upper fixed wing. The upper end of each upper fixed wing hinge support 13 and a connecting rod 3 are hinged by a hinge shaft. The use of an arc-shaped wing surface and a streamlined wing surface can reduce the resistance of the aircraft body during operation and increase the lift of the aircraft body during operation.

[0046] Further, in a preferred embodiment, the upper wing surface 21 of the lower fixed wing 2 is an arc-shaped wing surface, and the lower wing surface 22 of the lower fixed wing 2 is a streamlined wing surface. Four lower fixed wing hinge supports 23 are provided on the upper wing surface 21 of the lower fixed wing. The lower end of each lower fixed wing hinge support 23 and a connecting rod 3 are hinged by a hinge shaft. The use of an arc-shaped wing surface and a streamlined wing surface can reduce the resistance of the aircraft body during operation and increase the lift of the aircraft body during operation.

[0047] Further, in a preferred embodiment, it further includes: a bottom plate 8. The left and right ends of the bottom plate 8 are respectively connected to the two connecting rods 3 of the rear connecting rod group. The hybrid power module 5 is detachably mounted on the bottom plate 8. The detachable structural design facilitates the disassembly, maintenance, replacement, and upgrade of the hybrid power module 5.

[0048] Furthermore, in a preferred embodiment, it also includes: a propeller 7. A power output shaft 53 is provided at the rear side of the fuel engine 51. The propeller 7 is installed on the power output shaft 53. The fuel engine 51 is used to drive the propeller 7 to rotate around the axis of the power output shaft 53. The structural design of adding a propeller 7 separately to the oil-electric hybrid power module 5 can provide lift for the aircraft body and improve the maximum load capacity of the aircraft body. When the propeller 7 is installed on the rear side of the fuel engine 51, the fuel engine 51 is connected with the propeller 7 and the generator 54 through a clutch shift transmission device 57. By switching the working gear of the clutch shift transmission device 57, the fuel engine 51 can drive the propeller 7 or the generator 54. When the power supply device is fully charged, the fuel engine 51 drives the propeller 7 to rotate, thereby improving the maximum load capacity of the aircraft body. When the UAV needs to perform long-term and large-scale operations, the power supply device is difficult to supply the aircraft operation. Then, by changing the working gear of the clutch shift transmission device 57, the propeller 7 stops rotating, and the fuel engine 51 drives the generator 54 to work and charge the power supply device.

[0049] Furthermore, in a preferred embodiment, the hybrid power module 5 is provided with a plurality of connecting pipe interfaces 55 connected to the exhaust port of the fuel engine 51, each connecting pipe interface 55 is detachably connected to a connecting pipe 4, and each connecting pipe interface 55 is installed with an openable and closable valve. The detachable connection between the connecting pipe interface 55 and the connecting pipe 4 is adopted in conjunction with the detachable structure of the hybrid power module 5 on the base plate 8 to achieve rapid disassembly and assembly of the hybrid power module 5.

[0050] Further, in a preferred embodiment, two rotors 6 which are symmetrically arranged left and right are installed on the front side edges of the upper fixed wing 1 and the lower fixed wing 2. Each rotor 6 includes a rotor motor and a six-blade propeller. The rotor motor is installed on the upper fixed wing 1 or the lower fixed wing 2, and each six-blade propeller is installed at the output end of a rotor motor. When the aircraft body operates in a low-temperature environment, the low-temperature environment will cause an increase in the internal resistance and resistance of the motor. This is because the decrease in temperature causes an increase in the resistance of the internal components of the motor, such as materials like copper wire and iron core. This will lead to a decrease in the efficiency of the motor, thereby reducing the power output of the motor. The low-temperature environment will also cause the mechanical components of the motor to become more fragile. At low temperatures, the strength of metal materials will decrease, thereby increasing the mechanical resistance of the motor. This will not only increase the friction of the motor but also further reduce the power output of the motor. The startup time of the motor in a low-temperature environment will be significantly prolonged because the motor requires more time and energy to overcome the increase in internal resistance and resistance and the fragility of the mechanical components. At the same time, this also means that in a low-temperature environment, more energy will be required for the startup and operation of the motor, thereby increasing the power loss. The fuel engine 51 generates heat during operation. The exhaust port of the fuel engine 51 is respectively connected to the four rotors 6 through four connecting pipes 4. The heat emitted by the fuel engine 51 can be transmitted to the rotors 6 through the connecting pipes 4, improving the working environment temperature of the four rotors 6 and ensuring the stable operation of the four rotors 6.

[0051] Further, in a preferred embodiment, the oil-electric hybrid module 5 is provided with a plurality of snap-in slots 56. Each rotor motor is detachably electrically connected to a snap-in slot 56. The power supply device is used to supply power to the plurality of rotors 6. By adopting the structural design of detachably electrically connecting the rotor motor to the snap-in slot 56 and cooperating with the detachable structure of the oil-electric hybrid module 5 on the bottom plate 8, the rapid disassembly and assembly of the oil-electric hybrid module 5 are realized.

[0052] Further, in a preferred embodiment, the starter is an electric motor powered by the power supply device and is used to drive the propeller 7 to rotate.

[0053] The above are only preferred embodiments of the present invention, and thus do not limit the implementation manners and protection scope of the present invention.

[0054] The present invention further has the following implementation manners on the above basis:

[0055] In a further embodiment of the present invention, the hybrid fuel - electric power module 5 includes a starter, a fuel engine 51, a generator 54, and a power supply device. The starter is used to start the fuel engine 51. The fuel engine 51 is used to drive the generator 54 to operate. The generator 54 is used to charge the power supply device. The power supply device is used to supply power to the aircraft body and the starter. The aircraft body includes four rotors 6. The exhaust port of the fuel engine 51 is respectively connected to the four rotors 6 through four connecting pipes 4. The fuel engine 51 is used to ensure the working temperature of the four rotors 6. The power supply device is a battery. With this structural design, the generator 54 is used to charge the power supply device. At the same time, the fuel engine 51 is used to ensure the working environmental temperature of the rotors 6 and the power supply device, which can provide continuous and stable power to the aircraft body in harsh environments, solve the problems of large pollution of pure fuel power and short endurance of pure electric power, achieve a balance between the two, meet the reliable operation requirements of the aircraft in complex environments, realize the balance between endurance and environmental protection, facilitate maintenance and upgrade, and improve energy utilization efficiency and versatility. By combining the two power forms, the deficiencies of a single power are effectively compensated, and it can adapt to various scenarios.

[0056] In a further embodiment of the present invention, the hybrid fuel - electric power module 5 effectively improves the endurance and power stability of the aircraft, greatly enhances the practicality of the aircraft in emergency rescue, and saves precious time for saving lives and reducing losses.

[0057] In a further embodiment of the present invention, the aircraft equipped with the hybrid fuel - electric power module 5 has good endurance and power performance. The hybrid fuel - electric power module 5 can ensure the stable flight of the aircraft under various weather conditions, ensure the timely and safe delivery of goods, and is of great significance for expanding the logistics distribution range and improving service quality.

[0058] In a further embodiment of the present invention, the hybrid fuel - electric power module 5 can achieve high - efficiency power output and long endurance for the aircraft, which will strongly support the work in fields such as geographical mapping and border patrol, improve work efficiency and data accuracy.

[0059] In a further embodiment of the present invention, multiple groups of sensors are installed on the aircraft body. The sensors are electrically connected to the control system. The sensors are used to monitor the environmental temperature, wind direction and wind force magnitude, and the working environmental temperature of the battery and the rotors 6. The generator 54 is used to charge the power supply device. At the same time, based on the monitoring data of the sensors, the control system ensures the working environmental temperature of the rotors 6 and the power supply device through the fuel engine 51. When the power is switched, the situation of power interruption or fluctuation is avoided. At the same time, the power distribution is dynamically adjusted according to the actual situation to achieve seamless and smooth switching between the two powers, ensuring the stable operation of the aircraft.

[0060] In a further embodiment of the present invention, a detachable modular design is adopted between the hybrid power module 5 and the aircraft body. The hybrid power module 5 is detachably installed in the middle of the aircraft and connected to the four rotors 6. This design improves the versatility and maintainability of the power system. When a component of the power system fails, the corresponding module can be quickly disassembled and replaced, reducing the maintenance cost and time, and facilitating the flexible adjustment or upgrade of the power system according to different mission requirements.

[0061] In a further embodiment of the present invention, a structural design of waste heat utilization and heat control is adopted. The waste heat generated by the emission of the fuel engine 51 is effectively utilized to provide a heat preservation function for the four rotors 6. When flying in a cold environment, it can prevent the performance of the rotors 6 from decreasing or even malfunctioning due to low temperature, ensuring the flight safety and stability of the aircraft. At the same time, reasonable heat control is realized, and the comprehensive energy utilization rate is improved.

[0062] In a further embodiment of the present invention, an auxiliary lift providing design is adopted. A self-mounted propeller 7 is installed at the center of the hybrid power module 5, which can provide auxiliary lift for the aircraft during flight. This helps to improve the load capacity of the aircraft, enabling it to carry more equipment or supplies when performing tasks and enhancing the practicality of the aircraft.

[0063] In a further embodiment of the present invention, the hybrid power module 5 adopts a three-in-one integrated design, integrating the starter, the generator 54, and the engine. The starter is used to start the engine. After the engine works, it drives the generator 54 to work and charge the power supply device, and the power supply device powers the four rotors 6. The starter is an electric motor, which can be connected to the fuel engine 51 by coaxial transmission or coupling to achieve rapid kinetic energy transfer. The generator 54 is connected to the fuel engine 51 by a clutch shifting device. The power output shaft 53 is installed at the output end of the clutch shifting device, and the propeller 7 is installed on the power output shaft 53. The clutch shifting device can realize the independent drive of the fuel engine 51 for the generator 54 or the propeller 7, for realizing the charging and endurance of the power supply device or improving the maximum load capacity of the aircraft, and realizing the power distribution between the two. This highly integrated design reduces the number of components of the power system, simplifies the system structure, reduces the system complexity and failure risk, and improves the reliability and compactness of the power system.

[0064] In a further embodiment of the present invention, a modular design can also be adopted between the starter, the generator 54, and the engine of the hybrid power module 5. The power transmission shafts are quickly assembled and connected by couplings, and are connected to the overall frame of the hybrid power module 5 in a snap-fit mode, realizing the quick replacement of the starter, the generator 54, and the engine.

[0065] In a further embodiment of the present invention, the endurance and environmental performance of the aircraft are improved. The fuel-electric hybrid mode combines the advantages of long endurance of fuel power and cleanness of electric power. Compared with traditional pure fuel power, it reduces fuel consumption and pollutant emissions, being more environmentally friendly; compared with pure electric power, it greatly improves the endurance mileage, enabling the aircraft to operate stably and durably in tasks such as logistics distribution in remote areas and long-distance emergency rescue, effectively expanding the application scope of the aircraft.

[0066] In a further embodiment of the present invention, it has convenience. It adopts a detachable modular design. In terms of maintenance, when a certain component fails, the corresponding module can be quickly disassembled and replaced, greatly shortening the maintenance time and reducing the maintenance cost; in terms of upgrading, the modules can be flexibly replaced or upgraded according to different task requirements, improving the versatility and maintainability of the power system, which is difficult to achieve for traditional integrated power systems.

[0067] In a further embodiment of the present invention, through waste heat utilization and multi-functional integration, it innovatively uses the waste heat generated by the fuel engine emissions to provide a heat preservation function for the four rotors, effectively solving the problem of performance degradation of the rotor 6 of the aircraft in low-temperature environments, and ensuring flight safety and stability. At the same time, the self-mounted propeller 7 in the center of the fuel-electric hybrid module 5 can provide auxiliary lift, enhancing the load capacity of the aircraft and realizing the efficient utilization of energy and the integrated expansion of functions.

[0068] In a further embodiment of the present invention, a control system is used in cooperation with a sensor component to achieve intelligent and efficient power management. It can real-time monitor the flight state of the aircraft (such as speed, altitude, load, etc.) and environmental conditions (such as temperature, wind speed, etc.), and accurately and dynamically allocate the power output of the fuel engine 51 and the electric motor. It realizes seamless and smooth switching between the two powers, ensuring the stable operation of the aircraft while improving the energy utilization efficiency, and has obvious advantages compared with most existing fuel-electric hybrid systems lacking intelligent management.

[0069] In a further embodiment of the present invention, the unmanned aircraft equipped with the fuel-electric hybrid module 5 has a wide range of application scenarios. It is not only applicable to the field of emergency rescue. In terms of logistics distribution, it can achieve efficient cargo transportation in remote areas; in geographical mapping, the fuel-electric hybrid module 5 can support the aircraft to fly stably for a long time to obtain accurate data; it also has great uses in scenarios such as environmental monitoring and border patrol. Its excellent endurance, stability and environmental adaptability enable it to meet the needs of various industries and complex tasks, promoting the development of related fields.

[0070] In a further embodiment of the present invention, with the continuous expansion of the aviation application field and the increasing requirements for aircraft performance, the market demand for high-performance power systems continues to grow. The unmanned aerial vehicle (UAV) equipped with the hybrid fuel-electric power module 5 has broad market prospects in both the civilian market, such as e-commerce logistics, agricultural plant protection and other fields, and some specific professional fields due to its outstanding advantages.

[0071] In a further embodiment of the present invention, in view of the power requirements of the aircraft in complex application scenarios, an innovative hybrid fuel-electric modular power system solution is proposed. This solution not only solves many pain points of the existing power systems, but also has strong market potential and broad application prospects. Through continuous technological innovation and market promotion, the present invention is expected to take a leading position in the field of aircraft power technology.

[0072] In a further embodiment of the present invention, during the start-up and operation process of the UAV equipped with the hybrid fuel-electric power module 5, the working process of the UAV equipped with the hybrid fuel-electric power module 5 is divided into the following four stages:

[0073] Stage 1: Start-up preparation. The aircraft is in a ready-to-fly state, and each component of the hybrid fuel-electric power module 5 performs a self-check. The starter is ready for start-up, and the intake and fuel supply systems of the fuel engine 51 are on standby. The generator 54 and related circuits are also in a ready state. At the same time, the battery thermal management system starts to monitor the battery temperature to ensure that the battery is in a suitable working state.

[0074] Stage 2: Starter start. After the operator issues a start command, the starter starts first to provide initial power for the start of the fuel engine 51. The starter rotates rapidly, driving the crankshaft of the fuel engine 51 to rotate, enabling the fuel engine 51 to complete the cycle process of intake, compression, ignition, power generation, and exhaust, and starting successfully. At this time, the fuel engine 51 and the generator 54 start to work and generate electrical energy.

[0075] Stage 3: Rotor 6 rotation and power distribution. A part of the electrical energy generated by the generator 54 is supplied to the four rotor motors to drive the six-blade propellers to start rotating, providing lift and power for the aircraft.

[0076] Phase 4: Waste heat utilization and continuous operation. During the operation of the fuel engine 51, the waste heat generated by the emissions is transmitted through the connecting pipe 4 to the insulation systems of the four rotors 6. The insulation systems utilize this waste heat to provide insulation for the rotors 6, preventing the performance of the rotors 6 from degrading due to low temperature in a low-temperature environment. Meanwhile, the power system operates continuously, and the control system continuously adjusts the power distribution according to the flight state and environmental conditions to ensure the stable and efficient flight of the aircraft. During the whole process, if an abnormal situation occurs in a certain component, the modular oil-electric hybrid module 5 is convenient for quickly detecting and replacing the faulty module to ensure the reliability of the power supply of the aircraft.

[0077] In a further embodiment of the present invention, high-strength and wear-resistant metal connectors are adopted to connect the oil-electric hybrid module with the aircraft body and between various sub-components. Compared with the common ordinary connectors on the market, when bearing the flight conditions of high vibration and strong impact, it can effectively prevent loosening and fracture, ensuring the stability and reliability of power transmission. Through the structural design and material selection of the connectors, the long-term stable operation of the power system in a complex flight environment is ensured, reducing the risk of power interruption caused by the failure of the connecting components.

[0078] In a further embodiment of the present invention, the battery housing can adopt a composite material with high strength, flame retardancy and excellent insulation performance, which can protect the battery safety to the greatest extent in extreme situations such as external impact and short-circuit fire, preventing serious accidents such as battery explosion.

[0079] In a further embodiment of the present invention, a plurality of snap-in slots 56 are provided on the oil-electric hybrid module 5, and each rotor motor is detachably electrically connected to a snap-in slot 56. The snap-in slot type structural design ensures the sealing effect of the wiring part. While ensuring the connection strength and electrical connection stability, it can realize the quick plugging and replacing of the module in a short time, facilitating the quick repair and upgrade of the module under harsh conditions such as the wild.

[0080] In a further embodiment of the present invention, compared with the traditional fuel power scheme, the traditional fuel power system has high fuel consumption, high operating costs, and emits a large amount of pollutants, with poor environmental performance. In special environments such as low temperature and high altitude, it is difficult to start the fuel engine, and the power output attenuation is obvious. While the oil-electric hybrid system of the present invention combines the advantages of fuel power and electric power, and has better environmental adaptability and energy utilization efficiency.

[0081] In a further embodiment of the present invention, compared with the pure electric power solution, the pure electric power system is limited by the low battery energy density, resulting in a short flight range of the aircraft and being unable to meet the requirements of long-distance flight missions. Moreover, the battery charging time is long, making it difficult to achieve rapid turnover, and the battery performance will drop significantly or even fail to work in cold environments. The hybrid electric power system of the present invention effectively makes up for the problems of short endurance and poor environmental adaptability of pure electric power through the combination of fuel and electricity, and can operate stably in various environments.

[0082] In a further embodiment of the present invention, compared with the simple hybrid electric power solution, the simple hybrid electric power solution is prone to power interruption or fluctuation during the power switching process, affecting the flight stability of the aircraft. Its energy management strategy is not intelligent enough to accurately allocate power output according to the real-time state and mission requirements of the aircraft, and the energy utilization efficiency is relatively low. However, the power system of the present invention uses a control system to achieve seamless and smooth switching between the two powers, ensuring the stable operation of the aircraft and improving the energy utilization efficiency.

[0083] In a further embodiment of the present invention, in summary, although existing technical solutions (such as traditional fuel power, pure electric power, and simple hybrid electric power solutions, etc.) can provide power for the aircraft to a certain extent, they have limitations in terms of environmental protection performance, endurance, environmental adaptability, power switching stability, and energy utilization efficiency. In contrast, our hybrid electric power system realizes more efficient and stable power output through innovative technologies such as unique detachable modular design, intelligent energy management, waste heat utilization, and multi-functional integration, and has stronger comprehensive performance and a broader application prospect.

[0084] In a further embodiment of the present invention, for the hybrid electric power module 5 of the present invention in the low-temperature environment and for long-time and large-range operations, the hybrid electric power module 5 is detachably connected to the aircraft body in a modular manner. For example, if the aircraft body only needs to perform in-process operations in normal or high-temperature environments, the hybrid electric power module 5 can be disassembled and replaced with a single power supply device to supply power to the four rotors 6.

[0085] In a further embodiment of the present invention, when operating in a low-temperature environment, before the aircraft takes off, the hybrid electric power module 5 can preheat the four rotors 6 to ensure the smoothness of the aircraft takeoff process.

[0086] The above are only preferred embodiments of the present invention, and do not limit the implementation manners and protection scope of the present invention. For those skilled in the art, it should be realized that all equivalent replacements and obvious changes made by using the description and illustrations of the present invention should be included in the protection scope of the present invention.

Claims

1. An aircraft equipped with a detachable hybrid module, characterized in that, Comprising: An aircraft body, a connecting pipe (4), and a hybrid power module (5). The hybrid power module (5) is detachably mounted on the aircraft body. The hybrid power module (5) includes: a starter, a fuel engine (51), a generator (54), and a power supply device. The starter is used to start the fuel engine (51). The fuel engine (51) is used to drive the generator (54) to operate. The generator (54) is used to charge the power supply device. The power supply device is used to supply power to the aircraft body and the starter. The aircraft body includes: four rotors (6). The exhaust port of the fuel engine (51) is communicated with the four rotors (6) respectively through four connecting pipes (4). The fuel engine (51) is used to ensure the working temperature of the four rotors (6).

2. The aircraft equipped with a detachable hybrid module according to claim 1, characterized in that, The aircraft body includes: an upper fixed wing (1), a lower fixed wing (2), and four connecting rods (3). The four connecting rods (3) are divided into two front and rear connecting rod groups. The two connecting rods (3) of each connecting rod group are symmetrically arranged left and right. An upper fixed wing (1), a lower fixed wing (2), and the two connecting rod groups are hinged to form a parallelogram connecting rod mechanism.

3. The aircraft equipped with a detachable hybrid module according to claim 2, characterized in that, The upper wing surface (11) of the upper fixed wing (1) is an arc-shaped wing surface. The lower wing surface (12) of the upper fixed wing (1) is a streamlined wing surface. Four upper fixed wing hinge supports (13) are provided on the lower wing surface (12) of the upper fixed wing. The upper end of each upper fixed wing hinge support (13) and a connecting rod (3) are hinged by a hinge shaft.

4. The aircraft equipped with a detachable hybrid module according to claim 2, characterized in that, The upper wing surface (21) of the lower fixed wing (2) is an arc-shaped wing surface. The lower wing surface (22) of the lower fixed wing (2) is a streamlined wing surface. Four lower fixed wing hinge supports (23) are provided on the upper wing surface (21) of the lower fixed wing. The lower end of each lower fixed wing hinge support (23) and a connecting rod (3) are hinged by a hinge shaft.

5. The aircraft equipped with a detachable hybrid module according to claim 2, characterized in that, Further comprising: A bottom plate (8). The left and right ends of the bottom plate (8) are respectively connected to the two connecting rods (3) of the rear connecting rod group. The hybrid power module (5) is detachably mounted on the bottom plate (8).

6. The aircraft equipped with a detachable hybrid module according to claim 1, characterized in that, The hybrid power module (5) further includes: a fuel tank (52). The fuel tank (52) is used to supply fuel to the fuel engine (51).

7. The aircraft equipped with a detachable hybrid module according to claim 5, characterized in that, Further comprising: A propeller (7). A power output shaft (53) is provided at the rear side of the fuel engine (51). The propeller (7) is mounted on the power output shaft (53). The fuel engine (51) is used to drive the propeller (7) to rotate around the axis of the power output shaft (53).

8. The aircraft equipped with a detachable hybrid module according to claim 5, characterized in that, A plurality of connecting pipe interfaces (55) communicated with the exhaust port of the fuel engine (51) are provided on the hybrid power module (5). Each connecting pipe interface (55) is detachably connected to a connecting pipe (4). A switchable valve is mounted on each connecting pipe interface (55).

9. The aircraft equipped with a detachable hybrid module according to claim 2, characterized in that, Two rotors (6) which are symmetrically arranged left and right are installed on the front side edges of the upper fixed wing (1) and the lower fixed wing (2). Each rotor (6) includes: a rotor motor and a six-blade propeller. The rotor motor is installed on the upper fixed wing (1) or the lower fixed wing (2), and each six-blade propeller is installed at the output end of a rotor motor.

10. The aircraft equipped with a detachable hybrid module according to claim 9, characterized in that, The oil-electric hybrid power module (5) is provided with a plurality of snap-in slots (56). Each rotor motor is detachably electrically connected to a snap-in slot (56), and the power supply device is used to supply power to the plurality of rotors (6).

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