Heavy-load and high-stability composite aircraft

Abstract

The invention discloses a high-load and high-stability composite aircraft, relates to the technical field of aircrafts, and aims to overcome the technical defects that an existing multi-rotor aircraft is low in load capacity, and a lifting body aircraft is poor in wind resistance and prone to unbalance during unloading. The composite aircraft comprises a lifting body, a multi-rotor system and a connecting structure, the lifting body and the multi-rotor system are in flexible connection, and net lifting force provided by the lifting body corresponds to 80%-100% of the weight (after loads are removed) of a multi-rotor empty aircraft; the multi-rotor system adopts a scene-divided power dynamic adjusting mechanism, the multi-rotor system provides lift force accounting for 0%-20% of the weight of the multi-rotor air aircraft to maintain balance in the no-load state, the multi-rotor system bears all the load weight in the heavy load state, and the balance of the whole composite aircraft system is maintained by rapidly reducing the power to 0%-20% of the weight of the multi-rotor air aircraft in the unloading state. By means of the three-in-one collaborative design of the structure, the strategy and the mechanism, the loading capacity of the multiple rotors is improved by 50%-150%, the large load, the control flexibility and the wind resistance stability are all considered, the multi-rotor multi-rotor unmanned aerial vehicle can be widely applied to large-load hoisting scenes such as plateau material transportation and mountainous area engineering hoisting, and the market blank is filled.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of aircraft, and particularly relates to a composite aircraft for large-load hoisting scenes, which is suitable for plateau material transportation, mountainous area engineering hoisting, emergency rescue material delivery and other scenes requiring large-load hoisting and high-precision hoisting. BACKGROUND

[0002] In the field of large-load hoisting, multi-rotor aircraft has become one of the mainstream choices due to the advantages of vertical take-off, fixed-point hovering and precise walking. However, due to the performance limitation of the power system, the load capacity of the multi-rotor aircraft is generally low, and the load ratio (load / flying vehicle take-off total weight) can usually only be maintained at 30%-50%, which is difficult to meet the large-scale and heavy-load hoisting demand.

[0003] In order to improve the load capacity, a composite aircraft scheme combining multi-rotor aircraft with helium balloon, helium airship and other lifting bodies has appeared in the prior art. The additional lift provided by the lifting body assists the multi-rotor to bear the weight, thereby improving the upper limit of the load capacity. However, this kind of scheme has two core technical defects: one is weak wind resistance, the lifting body and the multi-rotor system are usually rigidly connected, the attitude adjustment is limited, and the positioning deviation or instability is easily caused by wind force; the other is unbalanced unloading, there is no clear logic and proportion rule for the lift distribution of the lifting body and the multi-rotor, and the lift redundancy generated by the lifting body after unloading cannot be quickly offset, resulting in system imbalance and attitude out of control.

[0004] Therefore, the existing composite aircraft cannot balance large load, flexible control and running stability, and there is an obvious technical bottleneck. Therefore, a technical scheme is needed to break through the above defects and fill the market gap. SUMMARY

[0005] 1. Invention purpose The present application aims to solve the technical problems of insufficient load capacity, weak wind resistance and unbalanced unloading of the existing multi-rotor-lifting body composite aircraft, and provides a composite aircraft with precise lift distribution, stable unloading, large load and flexible control, which improves the load ratio to more than 80% and meets the actual needs of large-load hoisting scenes.

[0006] To achieve the above purpose, the present application provides a large-load and high-stability composite aircraft, and the core technical scheme is as follows: The composite aircraft mainly comprises a lifting body, a multi-rotor system and a flexible connection structure, and the three form a three-in-one coordination system of "structure + strategy + mechanism", which is as follows: (1) Flexible connection structure design: replace the traditional rigid connection with flexible connection, the connection structure can be selected from high-strength flexible rigging, flexible hinge or flexible composite material connecting piece, so that the multi-rotor system can independently adjust the attitude and output power, and is not affected by the attitude of the lifting body, and the wind resistance and positioning accuracy of the system in complex wind field are improved through autonomous attitude compensation of the multi-rotor.

[0007] (2) Precise lift distribution strategy: the lift range provided by the lifting body is limited to 80%-100% of the empty weight of the compound aircraft (after removing the load), and the lifting body only bears the empty weight and does not participate in load bearing, so as to avoid confusion in lift distribution. The ratio design provides a core basis for subsequent working state switching and balance maintenance, and is the key to significantly improve the load ratio.

[0008] (3) Scene-based power dynamic adjustment mechanism: the multi-rotor system realizes precise regulation and control of three working states through control module and sensor feedback: when empty, output 0%-20% of the empty weight of the lifting body with small power, and cooperate with the lifting body to maintain balance; when heavy, output the same amount of lift as the load weight with large power, and specially bear the load; when unloaded, quickly reduce the power to return to the empty power range, and realize balance transition without adjusting the lifting body, thereby solving the problem of unbalanced unloading.

[0009] Compared with the prior art, the present application has the following remarkable beneficial effects: (1) The load capacity is greatly improved: the lifting body bears the entire empty weight, and the multi-rotor focuses on load bearing, so that the load ratio is improved from the existing 30%-50% to more than 80%, breaking through the load bottleneck in the industry; (2) The running stability is significantly enhanced: the combination of flexible connection structure and multi-rotor attitude adjustment capability solves the weakness of poor wind resistance; the scene-based power adjustment mechanism realizes stable switching of the whole process of emptying, heavy loading and unloading, and completely solves the problem of unbalanced unloading; (3) Flexible control and strong practicality: the advantages of vertical take-off and landing and precise walking of the multi-rotor are retained, and through simple control logic, the operation complexity is reduced, which can be adapted to various large-load lifting scenes, and the application range is wide; (4) Outstanding technological innovation: through the coordinated design of lift distribution ratio definition, flexible connection and dynamic regulation, the limitations of existing technology are broken through, and the market gap of "large load + high stability + strong control" compound aircraft is filled. DETAILED DESCRIPTION

[0010] The present application will be further described in detail below with reference to specific embodiments, so that those skilled in the art can reproduce the present application according to the description.

[0011] Example 1: The composite aircraft of this embodiment includes a lifting body, a multi-rotor system, a flexible connection structure, a control module, and a sensor array. The lifting body is a helium airship, designed to provide 80 kg of lift (80% of the empty weight) based on an empty weight (including the multi-rotor system, connection structure, and control module, excluding the load). The flexible connection structure uses four high-strength aramid fiber flexible riggings to evenly connect the bottom of the helium airship to the multi-rotor system frame. The rigging length is adjustable, achieving a non-rigid connection. The multi-rotor system uses an 8-rotor layout, powered by brushless motors and a lithium battery pack. The control module uses an STM32 microcontroller chip, and the sensor array includes an attitude sensor (MPU6050) and a weight sensor (pressure type) to collect attitude and load weight data in real time.

[0012] The work process is as follows: (1) No load: When there is no load, the multi-rotor system starts the low power mode and outputs 10kg of lift (10% of the empty weight), which works in conjunction with the 80kg lift of the helium airship to maintain the system's hovering balance. At this time, the attitude can be finely adjusted by the multi-rotor to achieve precise positioning and the wind resistance level can reach level 6. (2) Heavy load state: When hoisting a 400kg load (load ratio = 400 / (100+400) = 80%), the weight sensor detects the load weight, and the control module instructs the multi-rotor system to switch to high power mode, outputting 400kg of lift to fully bear the load weight. The helium airship still maintains 80kg of lift to bear the empty weight, and the system hovers stably and completes the hoisting operation. (3) Unloading state: After the load is deployed, the weight sensor reports that the load has disappeared. The control module quickly controls the multi-rotor system to reduce the power, the lift returns to 10kg, and the system instantly returns to the unloaded balance state without imbalance or swaying. The unloading response time is ≤0.5 seconds.

[0013] Example 2: The difference between this embodiment and Embodiment 1 is that the lifting body is designed to generate 100kg of lift (100% of the empty weight). When unloaded, the multi-rotor system outputs 0kg of lift and maintains balance only through the lifting body, thus reducing energy consumption when unloaded. The flexible connection structure uses flexible hinges to improve the flexibility of attitude adjustment and can withstand winds up to level 7. The remaining structure and control logic are the same as in Embodiment 1.

[0014] Those skilled in the art can adjust the type of lifting body, the specific form of the flexible connection structure, the multi-rotor layout, and the details of the lift ratio according to the actual scenario, all of which fall within the protection scope of this invention.

[0015] Attached diagram (illustrative) Figure 1 This is a schematic diagram of the overall structure of the composite aircraft of the present invention; Figure 2 Lift distribution and power regulation logic block diagram for the present invention.

Claims

1. A high-payload, high-stability composite aircraft, characterized in that, It includes a lifting body, a multi-rotor system, and a connecting structure. The lifting body is used to provide basic lift, the multi-rotor system is used to bear loads and adjust attitude, and the connecting structure is used to connect the lifting body and the multi-rotor system. The connection structure is a flexible connection structure, which allows the multi-rotor system to independently exert its power adjustment capability and attitude control advantages, thereby improving the system's wind resistance and positioning accuracy. The net lift provided by the lifting body is 80%-100% of the empty weight (after removing the load) of the multirotor system, and the core function of the lifting body is to bear most of the empty weight of the multirotor system.

2. The composite aircraft according to claim 1, characterized in that, The flexible connection structure uses high-strength flexible rigging, flexible hinges, or flexible composite material connectors to achieve a non-rigid connection between the lifting body and the multi-rotor system.

3. The composite aircraft according to claim 1, characterized in that, The scenario-specific dynamic power adjustment mechanism of the multi-rotor system is as follows: (1) No-load state: The multi-rotor system operates at low power, and the output lift is 0%-20% of the no-load weight of the multi-rotor system, which works in conjunction with the lifting body to achieve system balance; (2) Heavy load state: The multi-rotor system operates at high power, outputting lift to support the entire load weight and undertake the load-bearing task; (3) Unloading state: The multi-rotor system quickly reduces the power output, so that the output lift returns to the unloaded state range, and the system balance can be maintained without adjusting the lifting body.

4. The composite aircraft according to claim 1, characterized in that, The lifting body is a helium balloon, helium airship, or other lifting device lighter than air, and its volume and lift can be adjusted according to the empty weight of the aircraft.

5. The composite aircraft according to claim 1, characterized in that, The multi-rotor system includes multiple rotors, a power module, and a control module. The control module is used to monitor the working status in real time and adjust the power of the power module to achieve precise lift control.

6. The composite aircraft according to claim 5, characterized in that, The control module is connected to an attitude sensor and a weight sensor to collect system attitude information and load weight information, providing data support for power regulation.

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