Modular multi-purpose aerial delivery drone and method of use

Abstract

The present invention relates to the technical field of aerospace vehicles, and specifically discloses a modular multi-purpose aerial delivery and air transportation unmanned aerial vehicle and a usage method thereof. The unmanned aerial vehicle adopts a canard layout with a "gong"-shaped double fuselage, double wings and double vertical tails. The core of it is that the front wing adopts a modular design, and the total wing area and aerodynamic center of the whole aircraft can be flexibly adjusted by replacing different components to adapt to different loads; a hanging area is provided under the front and rear central wings between the double fuselages, and a hoisting point with a winch is configured, so that a variety of loads can be quickly hoisted from the ground and released in the air. Through the modular design and innovative hanging and loading method, the single platform of the present invention can flexibly perform various functions such as cargo transportation, equipment aerial delivery (such as prototypes, rockets), mission payload carrying (such as communication base stations), etc., significantly improving the multi-functional adaptability and mission cost-effectiveness of the platform, and at the same time having the advantages of simple loading process and low deployment requirements.

Description

Technical Field

[0001] This application belongs to the field of aircraft technology, and specifically relates to a modular multi-purpose airdrop and airlift drone and its usage method. Background Technology

[0002] Currently, drones are widely used in the military for cargo transportation, reconnaissance, and airdropping supplies, while in the civilian sector they are widely used for surveying, photography, transportation, and communication relay. Traditional drones are often designed for single mission requirements, resulting in limited applicability and a narrow range of tasks they can perform. As the application scenarios for drones gradually expand, the approach of designing a single model for a single mission makes it impossible to effectively amortize the design and manufacturing costs of the aircraft through large-scale application, leading to a higher overall cost. Summary of the Invention

[0003] To address the aforementioned issues, this application provides a modular multi-purpose airdrop and airlift drone, comprising:

[0004] It adopts a canard aerodynamic layout with a U-shaped twin fuselage, twin wings, and twin vertical tails. The twin wings include a main wing and a canard wing.

[0005] The forewing adopts a modular design, including wing root components and wing surface components. By replacing the wing root components with different sweep angles and / or splicing different numbers of the wing surface components, the total wing area and aerodynamic focus position of the entire aircraft can be changed.

[0006] A front center wing and a rear center wing are respectively provided between the twin fuselages, in front of and behind the main wing, and a mounting area is formed below the front center wing and the rear center wing;

[0007] The lower surface of the front center wing and / or the rear center wing is provided with at least one lifting point, which is connected to a built-in winch structure for suspending and releasing ground loads located in the mounting area in mid-air.

[0008] Preferably, the wing root assembly has an installation end connected to the fuselage and an extension end connected to the wing surface assembly, and the wing root assembly has various sweep angle models; the wing surface assembly is a rectangular wing structure with universal interfaces at its left and right ends, which can achieve a fixed chord length and variable span through different numbers of continuous splicing.

[0009] Preferably, a set of lifting points is centrally arranged on the lower surface of the front central wing, and two sets of lifting points are arranged on the lower surface of the rear central wing.

[0010] Preferably, the lifting point has the ability to release the load in mid-air.

[0011] Preferably, the lifting point is equipped with a force measuring device for measuring the weight and center of gravity of the suspended load.

[0012] Preferably, each of the twin fuselages has a turboprop engine mounted at its nose.

[0013] Preferably, a four-point landing gear layout is adopted, with a set of nose landing gear and main landing gear arranged inside the left and right fuselages, respectively, with the nose landing gear retracting backward and the main landing gear retracting forward.

[0014] Preferably, the sling load includes: standard cargo holds, small test prototypes, airdropped supplies, small commercial rockets, communication base stations, and electro-optical / radar loads.

[0015] A collaborative disaster relief method based on modular unmanned aerial vehicles (UAVs), employing the aforementioned modular multi-purpose airdrop and airlift UAV, includes the following steps:

[0016] Form a disaster relief drone squadron, which includes at least three modular multi-purpose airdrop and airlift drones, of which:

[0017] The first UAV carries an electro-optical and / or radar detection payload as a reconnaissance and search unit;

[0018] The second UAV carries the payload of a mobile communication base station and serves as a communication relay unit;

[0019] The third drone carries a standard cargo hold and serves as a material delivery unit.

[0020] The modular multi-purpose airdrop and airlift drone has a dual-fuselage layout with a mounting area between the two fuselages, and can suspend and release loads through lifting points.

[0021] Control the formation of disaster relief drones to fly to the disaster area and perform collaborative operations;

[0022] Control the communication relay unit to establish a temporary communication network over the disaster area;

[0023] With the support of the temporary communication network, the reconnaissance and search unit is controlled to conduct reconnaissance and search of the disaster area, and transmits the acquired disaster information and target location information back to the command center through the communication relay unit.

[0024] According to the instructions generated by the command center based on the feedback information, the material delivery unit is controlled to fly to the designated location and deliver the relief supplies in the standard cargo hold it is hoisted.

[0025] A method for launching a commercial rocket using a modular multi-purpose airdrop airlift drone, comprising:

[0026] The prepared commercial rocket is placed horizontally on the ground, with its longitudinal axis aligned with the drone's preset flight path.

[0027] Maneuver the drone to glide, so that the commercial rocket enters the hardpoint between its two fuselages and is positioned below the front and rear central wings;

[0028] The connection mechanisms for the lifting points under the front central wing and the two sets of lifting points under the rear central wing are respectively lowered and firmly connected to the corresponding interfaces on the commercial rocket body.

[0029] The drone was used to lift a commercial rocket off the ground, and the total weight and center of gravity of the rocket were measured by a force measuring device connected to the lifting point.

[0030] Based on the measured weight and center of gravity data, the forward wing root components with the corresponding sweep angle and the necessary number of wing surface components were replaced to adjust the overall aerodynamic layout of the aircraft and adapt it to the flight characteristics after the rocket was mounted.

[0031] The drone, carrying a rocket, took off from a taxiing runway and climbed to the designated launch airspace and altitude.

[0032] Upon arrival at the launch site, the UAV stabilizes its attitude, and the ground command center or airborne flight control system issues a release command. The hoisting point unlocks, and the commercial rocket separates from the UAV and ignites in mid-air.

[0033] A method for using the aforementioned modular multi-purpose airdrop and airlift drone includes the following steps:

[0034] Place the load to be mounted on the ground;

[0035] Maneuver the drone to enter from the front or rear of the load, so that the load is located in the mounting area between the two fuselages;

[0036] Lower the cable to the sling point and hook the load, then manipulate the drone to lift the load off the ground;

[0037] The load weight and center of gravity are automatically measured by the force measuring device on the lifting point, and the shape of the wing root component and the number of wing surface components to be replaced are calculated. The corresponding canard modular components are then replaced to adjust the aerodynamic layout.

[0038] The drone takes off from a taxiway and performs transport, airdrop, or cargo-carrying missions.

[0039] This invention achieves multi-functional reuse of the platform through modular replacement of payloads, wings, and other components, enabling takeoffs and landings at general aviation airports. It also simplifies design and manufacturing processes, reduces unit costs, and makes the mission cost-effectiveness higher than traditional single-function flight platforms. Attached Figure Description

[0040] Figure 1This is a schematic diagram of an airplane;

[0041] Figure 2 This is a schematic diagram of the modular replacement of the aircraft's forewing;

[0042] Figure 3 This is a schematic diagram of aircraft modular types;

[0043] Figure 4 This is a schematic diagram of the aircraft's mounted load.

[0044] like Figure 1 As shown, 1-fuselage, 2-main wing, 3-front wing, 4-front center wing, 5-rear center wing, 6-vertical tail, 7-propeller, 8-front landing gear, 9-main landing gear, 10-front elevator, 11-rear elevator, 12-aileron, 13-flaps, 14-rudder. Detailed Implementation

[0045] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0046] like Figures 1-4 As shown, the invention has a takeoff weight of 30,000 kg or more. Figure 1 As shown, it includes: fuselage 1, main wing 2, front wing 3, front center wing 4, rear center wing 5, vertical tail 6, propeller 7, front landing gear 8, main landing gear 9, front elevator 10, rear elevator 11, aileron 12, flaps 13, and rudder 14.

[0047] Adopt a "common" - shaped double - fuselage, single - double - wing, and double - vertical - tail canard layout. The main wing 2 adopts an upper - wing layout, the front wing 3 adopts a middle - wing layout, and the front and rear sets of central wings between the double fuselages 1 adopt an upper - wing layout. The double vertical tails 6 are respectively arranged at the tails of the double fuselages 1. A turboprop engine 7 is arranged at the head of each of the double fuselages 1, with a single - engine power of the 3000kW level. Adopt a four - point landing - gear layout. Inside the left and right fuselages 1, a set of nose landing - gear 8 and main landing - gear 9 systems are respectively arranged. The nose landing - gear retracts backward and the main landing - gear retracts forward. Inside the fuselage 1, electro - mechanical systems such as hydraulic, fuel, and wire harness, as well as flight - management systems such as navigation and computers, are installed. Fuel tanks are arranged in the middle of the fuselage 1 and inside the main wing 2. The whole aircraft has 8 control surfaces. There is a set of front elevators 10 and rear elevators 11 for controlling pitch on the front and rear central wings respectively; there is a set of ailerons 12 and flaps 13 on each of the left and right main wings 2 for controlling roll and increasing lift; a set of rudders 14 is arranged on each of the double vertical tails 6.

[0048] The front wing adopts a modular design and is divided into two components: the wing root and the wing surface. As Figure 2 shown, the two ends of the wing - root component have the same shape and have multiple sweep angles, and the wing can be swept by changing the installation. The wing - surface component is a rectangular - wing - surface structure, and the left and right ends are in the form of universal interfaces. By splicing different numbers continuously, the wing can be made to have a constant chord length and variable span. Through different combinations of the two components, the total wing area and the position of the aerodynamic center of the whole aircraft's aerodynamic layout can be changed. According to different load weights and centers of gravity, the aircraft layout can be adjusted to adapt, ensuring sufficient flight capabilities.

[0049] There are two sets of central wings, including the front central wing 4 and the rear central wing 5. Below and between the double fuselages 1 is the hanging area. The central wings are in an arch structure to ensure sufficient space in the hanging area. There is a set of hanging points arranged in the middle of the lower surface of the front central wing 4, and two sets of hanging points are arranged on the lower surface of the rear central wing 5. The hanging points can lift the load placed on the ground through a winch structure built into the central wing and have the ability to release in the air. It can carry standard cargo boxes of 8t and 80 cubic meters or special - shaped loads of 5t, with a length not greater than 18m, a width not greater than 5m, and a height not greater than 3m, including small flight - test prototypes, airdropped supplies, light vehicles, commercial rockets, communication base stations, detection loads, etc., as Figure 3 shown.

[0050] During the use of the present invention, place the load to be hung on the airport ground. The ground crew operates the aircraft to drive in from the front and rear directions of the load and place the load between the double fuselages 1; lower the cable of the hanging point to hook the load, and then operate the aircraft to lift the load; after the weighing device on the hanging point measures the weight and center of gravity of the load, it automatically calculates the required shape of the wing root and the number of wing surfaces, and the ground crew conducts modular replacement; the aircraft meets the 2B flight - area standard and can take off by taxiing at a general - aviation airport to perform designated tasks.

[0051] This implementation provides the following modular multi-purpose airdrop and airlift drone, enabling the following multiple applications:

[0052] 1. Transportation: The standard cargo hold can be hoisted into the aircraft for internal loading and transport. Compared with the lengthy loading process of traditional transport aircraft, the cargo hold that has been pre-loaded on the ground can be quickly hoisted onto the aircraft, which significantly simplifies the ground crew's workload.

[0053] 2. Airdrop: Small aircraft can be used as test flight verification platforms. The aircraft to be verified can be launched and released by airdrop, eliminating the need for takeoff runways and a certain amount of fuel, thus saving costs and improving verification efficiency. Various irregularly shaped payloads, such as light vehicles and airdropped supplies, can be slinged on to achieve support or rapid transportation. Small space rockets can be slinged on and released in the air to provide initial altitude and initial velocity, saving rocket fuel weight and increasing the payload ratio.

[0054] 3. Carry mission payloads, such as communication base stations, optoelectronic devices, and radar, to achieve multiple purposes such as communication relay and reconnaissance detection.

[0055] By adopting a modular and multi-purpose design approach, the functionality of a single platform can be expanded and the cost-effectiveness improved.

[0056] A collaborative disaster relief method based on modular unmanned aerial vehicles (UAVs), employing the aforementioned modular multi-purpose airdrop and airlift UAV, includes the following steps:

[0057] Form a disaster relief drone squadron, which includes at least three modular multi-purpose airdrop and airlift drones, of which:

[0058] The first UAV carries an electro-optical and / or radar detection payload as a reconnaissance and search unit;

[0059] The second UAV carries the payload of a mobile communication base station and serves as a communication relay unit;

[0060] The third drone carries a standard cargo hold and serves as a material delivery unit.

[0061] The modular multi-purpose airdrop and airlift drone has a dual-fuselage layout with a mounting area between the two fuselages, and can suspend and release loads through lifting points.

[0062] Control the formation of disaster relief drones to fly to the disaster area and perform collaborative operations;

[0063] Control the communication relay unit to establish a temporary communication network over the disaster area;

[0064] With the support of the temporary communication network, the reconnaissance and search unit is controlled to conduct reconnaissance and search of the disaster area, and transmits the acquired disaster information and target location information back to the command center through the communication relay unit.

[0065] According to the instructions generated by the command center based on the feedback information, the material delivery unit is controlled to fly to the designated location and deliver the relief supplies in the standard cargo hold it is hoisted.

[0066] A method for launching a commercial rocket using a modular multi-purpose airdrop and airlift drone, employing the aforementioned modular multi-purpose airdrop and airlift drone.

[0067] The prepared commercial rocket is placed horizontally on the ground, with its longitudinal axis aligned with the drone's preset flight path.

[0068] Maneuver the drone to glide, so that the commercial rocket enters the hardpoint between its two fuselages and is positioned below the front central wing 4 and the rear central wing 5;

[0069] The connection mechanisms for the lifting points below the front central wing 4 and the two sets of lifting points below the rear central wing 5 are respectively lowered and firmly connected to the corresponding interfaces on the commercial rocket body.

[0070] The drone was used to lift a commercial rocket off the ground, and the total weight and center of gravity of the rocket were measured by a force measuring device connected to the lifting point.

[0071] Based on the measured weight and center of gravity data, the forward wing root components with the corresponding sweep angle and the necessary number of wing surface components were replaced to adjust the overall aerodynamic layout of the aircraft and adapt it to the flight characteristics after the rocket was mounted.

[0072] The drone, carrying a rocket, took off from a taxiing runway and climbed to the designated launch airspace and altitude.

[0073] Upon arrival at the launch site, the UAV stabilizes its attitude, and the ground command center or airborne flight control system issues a release command. The hoisting point unlocks, and the commercial rocket separates from the UAV and ignites in mid-air.

[0074] A method for using the aforementioned modular multi-purpose airdrop and airlift drone includes the following steps:

[0075] Place the load to be mounted on the ground;

[0076] Maneuver the drone to enter from the front or rear of the load, so that the load is located in the mounting area between the two fuselages;

[0077] Lower the cable to the sling point and hook the load, then manipulate the drone to lift the load off the ground;

[0078] The load weight and center of gravity are automatically measured by the force measuring device on the lifting point, and the shape of the wing root component and the number of wing surface components to be replaced are calculated. The corresponding canard 3 modular components are replaced to adjust the aerodynamic layout.

[0079] The drone takes off from a taxiway and performs transport, airdrop, or cargo-carrying missions.

[0080] This invention achieves multi-functional reuse of the platform by modularly replacing payloads, wings, and other components. This simplifies the design and manufacturing process, reduces the cost per unit, and makes the mission cost-effectiveness higher than that of traditional single-function flight platforms.

[0081] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A modular multi-purpose airdrop and airlift drone, characterized in that, include: It adopts a canard aerodynamic layout with a double fuselage, double wings, and double vertical tail. The double wings include the main wing (2) and the front wing (3). The forewing (3) adopts a modular design, including wing root components and wing surface components. By replacing the wing root components with different sweep angles and / or splicing different numbers of the wing surface components, the total wing area and aerodynamic focus position of the entire aircraft can be changed. Between the twin fuselages, in front of and behind the main wing (2), a front central wing (4) and a rear central wing (5) are respectively provided, and a mounting area is formed below the front central wing (4) and the rear central wing (5); The lower surface of the front central wing (4) and / or the rear central wing (5) is provided with at least one lifting point, which is connected to a built-in winch structure for suspending and releasing the ground load located in the mounting area in mid-air.

2. The modular multi-purpose airdrop and airlift drone as described in claim 1, characterized in that, The wing root assembly has an installation end that connects to the fuselage and an extension end that connects to the wing surface assembly. The wing root assembly has various models with sweep angles. The wing surface assembly is a rectangular wing structure with universal interfaces at both ends, which can achieve a fixed chord length and variable span by continuously splicing different numbers of components.

3. The modular multi-purpose airdrop and airlift drone as described in claim 1, characterized in that, A set of lifting points is arranged in the center of the lower surface of the front central wing (4), and two sets of lifting points are arranged on the lower surface of the rear central wing (5); the lifting points have the ability to release loads in the air.

4. The modular multi-purpose airdrop and airlift drone as described in claim 1, characterized in that, The lifting point is equipped with a force measuring device to measure the weight and center of gravity of the suspended load.

5. The modular multi-purpose airdrop and airlift drone as described in claim 1, characterized in that, Each of the twin fuselages is equipped with a turboprop engine (7) at its nose.

6. The modular multi-purpose airdrop and airlift drone as described in claim 1, characterized in that, It adopts a four-point landing gear layout, with a front landing gear (8) and a main landing gear (9) arranged inside the left and right fuselages respectively. The front landing gear (8) retracts backward and the main landing gear (9) retracts forward.

7. The modular multi-purpose airdrop and airlift drone as described in claim 1, characterized in that, The payloads include: standard cargo holds, small test aircraft, airdropped supplies, commercial rockets, communication base stations, and electro-optical / radar payloads.

8. A method for carrying and launching a commercial rocket using a modular multi-purpose airdrop and airlift drone, employing the modular multi-purpose airdrop and airlift drone as described in any one of claims 1-7, characterized in that, The prepared commercial rocket is placed horizontally on the ground, with its longitudinal axis aligned with the drone's preset flight path. Maneuver the drone to glide, so that the commercial rocket enters the hardpoint between its two fuselages and is positioned below the front central wing (4) and the rear central wing (5); The connecting mechanisms of the two sets of lifting points under the front central wing (4) and the rear central wing (5) are respectively lowered and firmly connected to the corresponding interfaces on the commercial rocket body; The drone was used to lift a commercial rocket off the ground, and the total weight and center of gravity of the rocket were measured by a force measuring device connected to the lifting point. Based on the measured weight and center of gravity data, the forward wing root components with the corresponding sweep angle and the necessary number of wing surface components were replaced to adjust the overall aerodynamic layout of the aircraft and adapt it to the flight characteristics after the rocket was mounted. The drone, carrying a rocket, took off from a taxiing runway and climbed to the designated launch airspace and altitude. Upon arrival at the launch site, the UAV stabilizes its attitude, and the ground command center or airborne flight control system issues a release command. The hoisting point unlocks, and the commercial rocket separates from the UAV and ignites in mid-air.

9. A collaborative disaster relief method based on modular unmanned aerial vehicles (UAVs), employing a modular multi-purpose airdrop and airlift UAV as described in any one of claims 1-7, characterized in that, Includes the following steps: Form a disaster relief drone squadron, which includes at least three modular multi-purpose airdrop and airlift drones, of which: The first UAV carries an electro-optical and / or radar detection payload as a reconnaissance and search unit; The second UAV carries the payload of a mobile communication base station and serves as a communication relay unit; The third drone carries a standard cargo hold and serves as a material delivery unit. The modular multi-purpose airdrop and airlift drone has a dual-fuselage layout with a mounting area between the two fuselages, and can suspend and release loads through lifting points. Control the formation of disaster relief drones to fly to the disaster area and perform collaborative operations; Control the communication relay unit to establish a temporary communication network over the disaster area; With the support of the temporary communication network, the reconnaissance and search unit is controlled to conduct reconnaissance and search of the disaster area, and transmits the acquired disaster information and target location information back to the command center through the communication relay unit. According to the instructions generated by the command center based on the feedback information, the material delivery unit is controlled to fly to the designated location and deliver the relief supplies in the standard cargo hold it is hoisted.

10. A method for using a modular multi-purpose airdrop / airlift drone as described in any one of claims 1-7, characterized in that, Includes the following steps: Place the load to be mounted on the ground; Maneuver the drone to enter from the front or rear of the load, so that the load is located in the mounting area between the two fuselages; Lower the cable to the sling point and hook the load, then manipulate the drone to lift the load off the ground; The load weight and center of gravity are automatically measured by the force measuring device on the lifting point, and the shape of the wing root component and the number of wing surface components to be replaced are calculated. The corresponding front wing (3) modular components are replaced to adjust the aerodynamic layout. The drone takes off from a taxiway and performs transport, airdrop, or cargo-carrying missions.

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