Low-altitude transportation method of exogenous power

Abstract

The invention discloses a low-altitude transportation method adopting external power, and belongs to the technical field of overall design of low-altitude transportation systems. According to the invention, the problems of low economical efficiency and high flight dead weight of the existing aircraft are solved by introducing external source power. The carrier parent body is connected with the power sub-machine through the connecting mechanism, the power sub-machine serves as a main power source, and flight power can be provided for different types of aircrafts through the customized connecting mechanism and the power sub-machine, including but not limited to fixed-wing aircrafts, hot-air balloons, airships and modified automobiles. The effective take-off weight, the flight speed and the like of the aircraft are related to the number of the power sub-aircrafts connected with the system and the overall aerodynamic configuration, and the access and flight requirements of any type of carriers can be theoretically met.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of overall design of low-altitude transportation system, and particularly relates to a low-altitude transportation method of external power. BACKGROUND

[0002] At present, the world is developing low-altitude economy, and various low-altitude aircrafts are being created. The low-altitude aircrafts can be mainly classified into rotary wings, fixed wings and hybrid wings. Although various aerospace vehicles have created various aircrafts at present, such as emerging multi-rotor aircrafts, hybrid wings, tilt rotors and tilt wing aircrafts. However, there are almost no aircrafts or schemes that can truly realize sufficient economy and benefit most ordinary people. For example, the price of a manned aircraft is equal to the income level of an ordinary person with medium income for more than 10 years, and the use cost per kilometer is about 1 / 4 of the average hourly wage of the aforementioned group, while the cost per kilometer of a train is less than 1 / 20 of the cost of a manned aircraft. The use cost and relative income threshold will be the biggest economic obstacle to the development of low-altitude aircrafts. In addition, there are still many problems in the research and development of related aircrafts, systems and methods that need to be focused on and considered.

[0003] 1. The existing multi-rotor manned aircraft scheme relies on multiple rotors to realize flight, but the energy is mainly used to overcome gravity, the flight speed is slow, and the application scene is suitable for short-distance sightseeing.

[0004] 2. The existing fixed-wing aircraft has relatively low use cost per kilometer and good endurance, but can only take off by sliding, which greatly limits the use flexibility in cities.

[0005] 3. The existing hybrid wing, tilt rotor and tilt wing aircraft rely on fixed wings to provide cruising lift, and rotors to provide cruising drag and vertical lift. However, the additional tilt mechanism or stopped propeller in the cruising state is dead weight in the corresponding working condition. If the battery power supply mode is adopted, the consumed battery also becomes dead weight, which increases flexibility while reducing economy and reliability compared with fixed wings.

[0006] 4. From the cost point of view, lightweight materials and batteries increase the one-time investment cost, and fuel and complex mechanisms increase the subsequent use cost. For the EVTOL with vertical take-off and landing function, the battery cost accounts for about 30% of the total cost, but the subsequent use cost is mainly the electricity cost, which is more economical than fuel.

[0007] 5. Considering the background of the current development of low-altitude economy and the main problems of technical bottlenecks and economy of various aircrafts, and the future development and improvement of emerging disciplines, the application proposes a low-altitude transportation method of external power to solve the above problems. SUMMARY

[0008] The present invention is developed to solve the problems of the low-altitude aircraft transportation efficiency being limited and the economy being insufficient. A brief summary of the present invention is given below to provide a basic understanding of some aspects of the present invention. It should be understood that this summary is not an exhaustive overview of the present invention. It is not intended to identify key or important parts of the present invention nor to define the scope of the present invention.

[0009] Technical solutions of the present invention: Solution one: a low-altitude transportation method with external power, mainly including a power sub-machine, a connecting mechanism, and a carrier parent body, and other necessary components.

[0010] Further, the power sub-machine provides external power for the carrier parent body through the connecting mechanism as the main power source of flight movement.

[0011] Further, the power sub-machine is self-powered and energy-stored.

[0012] Further, the connecting mechanism determines the connection site and method of the power sub-machine and the carrier parent body according to the characteristics of the mass, aerodynamic shape, and cruising speed of the carrier parent body, and further customizes its own shape.

[0013] Further, the carrier parent body serves as an aircraft parent body and acts as the main carrier or cargo of low-altitude transportation.

[0014] Further, the power sub-machine can stay in a sub-machine airport platform or hangar for energy replenishment and current performance reliability analysis in the non-working state.

[0015] Further, the carrier parent body serves as an aircraft parent body and acts as the main carrier or cargo, and is connected with the power sub-machine through the connecting mechanism, and the main power is provided by the power sub-machine. The carrier parent body can also be equipped with a backup power to cope with special scenarios.

[0016] Further, when the power sub-machine receives the power demand issued by the carrier parent body, it is dispatched nearby and flies to the carrier parent body, and is connected through the connecting mechanism to provide flight power.

[0017] Further, when the self-powered energy of the power sub-machine is exhausted, a new batch of energy-loaded power sub-machines are dispatched from the ground to replace the power sub-machines with exhausted energy one by one.

[0018] By the foregoing description, the application scenarios are exemplified, including but not limited to: providing vertical take-off and main power for cruise flight for an aircraft with an air dynamic shape, providing space movement power in all directions for a self-lifting aircraft such as a hot air balloon and an airship, and providing a pulling force mainly used for lifting and accelerating and decelerating for a traditional car after modification and installation of a related connecting mechanism.

[0019] Scheme II: A low-altitude transportation method of an external power source, which is implemented based on the low-altitude transportation method of an external power source in claim 1, and characterized by comprising the following steps: Step I: A fixed-wing aircraft, a hot air balloon, an airship or a modified traditional car as a carrier matrix sends a route demand at a corresponding airport or parking lot; Step II: After the power sub-machine staying on the sub-machine airport platform or hangar completes energy supplement and performance reliability analysis, and receives the corresponding route demand, the power sub-machine is dispatched from a non-working state to a working state; Step III: The power sub-machine flies to the carrier matrix, and realizes connection through the connecting mechanism to provide flight power for the carrier matrix; Step IV: For the modified car in the parking lot and the VTOL, the hot air balloon and the airship in the vertical take-off airport, vertical take-off lift and flight power after take-off are provided, and for the fixed-wing aircraft on the runway, a taxiing pulling force and a cruising pulling force are provided; Step V: For the carrier matrix flying in the air, multiple power sub-machines provide power, for the power sub-machine with an independent energy source about to be exhausted, the power sub-machine can be separated from the carrier matrix through the connecting mechanism, and can be supplemented with energy at a nearby airport or platform, and a new batch of power sub-machines with full energy can be dispatched to replace the old batch of power sub-machines.

[0020] 1. The low-altitude transportation method of an external power source can select appropriate power sub-machines and connecting mechanisms according to the mass, aerodynamic shape and cruising speed of the carrier matrix, and provide a power source by the power sub-machines, thereby reducing the dead weight of the carrier matrix and lowering the one-time purchase cost, converting the cost of the power unit and the battery cost into a purchase service, so as to maximize the economic benefit and match greater flight market demand.

[0021] 2. The low-altitude transportation method of an external power source can use vertical take-off, runway take-off, catapult take-off and arresting landing according to the type and flight characteristics of the carrier matrix, to provide take-off and landing conditions for the carrier matrix as a whole, and achieve a relatively good flight state.

[0022] 3、The low-altitude transport method of the external power source of the application can match the corresponding power sub-machine and the distribution of the sub-machine airport platform according to the hardware such as the carrier matrix and the connecting mechanism and the corresponding flight market demand, so as to meet the actual flight task needs of different flight modes and different flight conditions.

[0023] 4、The low-altitude transport method of the external power source of the application can obtain the information of the corresponding route according to the flight task demand, flexibly arrange the ground sub-machine airport platform, and adjust the distribution density, so as to meet the flight task needs of different busy degrees, and ensure that there is no idle power sub-machine and ground airport platform for a long time. BRIEF DESCRIPTION OF DRAWINGS

[0024] In order to more clearly illustrate the technical solutions of the embodiments of the application, the following will briefly introduce the drawings needed to be used in the embodiments of the application or the prior art description. Obviously, the drawings in the following description are some embodiments of the application. Those skilled in the art can obtain other drawings according to these drawings without creative labor.

[0025] Figure 1 A schematic diagram of the vertical take-off and acceleration flight stage of the low-altitude transport method of the external power source of the embodiments of the application is provided. Figure 2 A schematic diagram of the power sub-machine connected to the separation state in the cruising stage of the embodiments of the application is provided. Figure 3 A schematic diagram of the power sub-machine connected to the separation state in the cruising stage of the embodiments of the application is provided. REFERENCE NUMERALS 1-power sub-machine, 2-connecting mechanism, 3-carrier matrix, all the above-mentioned mark graphics are only used as legend reference for understanding, not as design standardization,

[0026] Figure 1 The schematic diagram shows the docking process of the power sub-machine 1 and the carrier matrix 3 through the connecting mechanism 2, and the vertical take-off to the acceleration flight stage, Figure 2 The schematic diagram shows the state from the connecting state to the separation state of the power sub-machine 1 and the carrier matrix 3, which is used for replacing the power sub-machine in the air, Figure 3 The schematic diagram shows that the power sub-machine 1 and other unconventional carrier matrix 3 such as hot air balloon and modified car are connected through the connecting mechanism, which respectively provides horizontal flight power and vertical flight power, and the description terms of the above-mentioned states, hardware and working conditions are used for description, which can be understood by synonymous expansion in the technical field. DETAILED DESCRIPTION

[0027] In order to make the objects, technical solutions and advantages of the present application clearer and more comprehensible, the present application will be described below in detail through specific embodiments shown in the drawings. However, it should be understood that these descriptions are only exemplary and are not intended to limit the scope of the present application. In addition, in the following description, the description of well-known structures and technologies is omitted to avoid unnecessary confusion of the concept of the present application.

[0028] The connection mechanism mentioned in the present application can be designed into different styles and functions according to different flight task requirements and actual needs of the vehicle parent body and the power sub-machine. However, the core requirement of this structure is to meet the connection needs of the power sub-machine and the vehicle parent body, so that the three become a moving whole, the design strength of which can meet the flight needs of the whole under the most adverse conditions, ensure that the separation process and docking process of the power sub-machine and the vehicle parent body will not fail, and can be reused to meet the needs of the parent machine to replace different power sub-machines, and realize the flight needs of various types of vehicles and various working conditions. Those skilled in the art can select and design this part according to their needs to meet the function.

[0029] In the present application, unless otherwise explicitly specified and limited, the terms "standby", "separation", "connection", "vertical take-off and landing" and "cruise" and other terms should be understood broadly. For example, "connection" can be understood as physically contacting and mechanically analyzed as a whole, which can be fixed connection or detachable connection, or integrated; the connection can be the connection of necessary module systems such as power, fuel and communication, or mechanical mechanism connection; it can be directly connected, or indirectly connected through an intermediate medium, or the internal communication of two or more modules, or the interaction relationship between two or more modules. For those skilled in the art, the above-mentioned specific meanings in the present application can be understood according to the specific circumstances.

[0030] Embodiment 1, in combination Figure 1 and Figure 2 This embodiment is a low-altitude transportation method of an external power source, which includes a power sub-machine 1, a connection mechanism 2 and a vehicle parent body 3. The power sub-machine 1 provides external power for the vehicle parent body 3 through the connection mechanism 2 to provide power as the main power source of flight movement; the power sub-machine 1 is self-powered and has energy storage; the connection mechanism 2 determines the connection site and mode of the power sub-machine and the vehicle parent body according to the characteristics of the vehicle parent body 3 such as mass, aerodynamic shape and cruise speed, and then customizes its own shape; the vehicle parent body 3 serves as the main carrier or cargo of low-altitude transportation as the aircraft parent body.

[0031] The carrier matrix 3 usually takes off with several power sub-machines 1, the carrier matrix 3 can carry goods or itself as goods, can carry spare energy and spare power unit by itself, and can be connected with the power sub-machine 1 through the connecting mechanism 2, and the power sub-machine 1 is used as the main power source. The number and style of the power sub-machine are determined according to the carrier matrix 3 and the customized connecting mechanism 2.

[0032] As a fixed-wing aircraft as the carrier matrix 3, the route demand is sent at the corresponding airport or parking lot, the power sub-machine which is parked on the sub-machine airport platform or hangar completes the energy supplement and performance reliability analysis, and receives the corresponding route demand, and then the power sub-machine in the non-working state enters the working state. The power sub-machine flies to the carrier matrix, and is connected through the connecting mechanism to provide flight power for the carrier matrix.

[0033] For the fixed-wing aircraft and the VTOL of the vertical take-off and landing airport, the traditional aircraft provides taxiing pull, cruising pull and vertical take-off lift.

[0034] For the carrier matrix 3 flying in the air, multiple power sub-machines 1 provide power, and for the power sub-machine 1 with independent energy about to be exhausted, the power sub-machine 1 can be separated from the carrier matrix 3 through the connecting mechanism 2, and can be supplemented in the airport or platform, and the new batch of power sub-machines 1 with full energy can be dispatched to replace the old batch of power sub-machines 1.

[0035] Embodiment 2, in combination Figure 3 This embodiment is described, and the low-altitude transportation method of an external power source of this embodiment can be taken off according to the process of example 1 for unconventional aircraft such as hot air balloons, airships and modified cars as the carrier matrix 3. However, due to the special aerodynamic shape of such aircraft, the matched power sub-machine 1 and the connecting mechanism 2 will also have certain customization changes.

[0036] This embodiment is only an exemplary description of the invention, and does not limit the protection scope thereof. Those skilled in the art can also change and enrich it locally, as long as it does not exceed the spirit and essence of the invention, and is within the protection scope of the invention.

Claims

1. A method for low-altitude transportation powered by an external source, characterized in that: it includes... The power submachine (1) transmits power to the carrier body (3) through the connecting mechanism (2) to provide external power as the main power source for flight motion; The power sub-machine (1) has its own power unit and energy storage; The connection mechanism (2) determines the connection point and method between the power submachine and the vehicle mother body (3) based on the mass, aerodynamic shape and cruising speed of the vehicle mother body (3), thereby customizing its own shape. The carrier (3) serves as the mother of the aircraft and acts as the main carrier or cargo for low-altitude transportation.

2. The low-altitude transportation method powered by external energy according to claim 1, characterized in that: When the power submachine (1) is not in operation, it can stay on the submachine airport platform or hangar for recharging and current performance reliability analysis.

3. The low-altitude transportation method powered by external energy according to claim 1, characterized in that: The vehicle mother (2) serves as the aircraft mother and acts as the main vehicle or main cargo carrier. It is connected to the power sub-machine (1) through the connection mechanism (2) and is powered by the power sub-machine (1). It can also install its own backup power to cope with special scenarios.

4. The low-altitude transportation method powered by external energy according to claim 3, characterized in that: After receiving the power demand from the mother vehicle (3), the nearest power submachine (1) is dispatched to fly to the mother vehicle and connected through the connection mechanism (2) to provide flight power.

5. The low-altitude transportation method powered by external energy according to claim 4, characterized in that: When the power unit (1) is about to run out of its own energy, it will be rationally scheduled and allocated, and a new batch of fully loaded power units (1) will take off from the ground one by one to replace the power unit (1) that is about to run out of energy.

6. A low-altitude transportation method powered by an external source of energy according to claim 4, characterized in that: Examples of its application scenarios include, but are not limited to: providing the main lift for vertical take-off and landing and the main power for cruising level flight for aircraft with aerodynamic shape; providing the motion power in all directions in space for aircraft with their own lift, such as hot air balloons and airships; and providing the main pull for take-off, landing and acceleration / deceleration for traditional cars that have been modified and equipped with relevant connecting mechanisms (2).

7. The low-altitude transportation method powered by an external source of energy according to claim 3, characterized in that, When the vehicle mother body (3) has its own backup power or power module, it means that the system has at least two power modes. The energy flow path is as follows: the power sub-machine (1) directly transmits energy, such as electrical energy and oil and gas fuel, to the vehicle mother body (3) through the connecting mechanism (2) and then converts it into power. This is regarded as the power sub-machine (1) providing the main power source.

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