A distributed power swarm unmanned mother-child aerial vehicle and method of use

Abstract

A distributed power cluster type unmanned mother-child aircraft and a use method, belong to aircraft aerodynamic layout design field, the present application solves the problem that the existing cluster type unmanned mother-child aircraft is not suitable for island, dense forest and other extreme environment take-off. The mother-child aircraft includes a carrier mother machine and a plurality of propeller type children, the carrier mother machine includes a fuselage, a horizontal tail is arranged at the tail of the fuselage through a vertical tail, both sides of the fuselage are provided with wings, the trailing edge of the wing is provided with an inside aileron, an outside aileron and ailerons, the leading edge of the wing is provided with a plurality of rotating shafts along the span direction, a plurality of propeller type children are one-to-one corresponding and can be separated from the rotating shafts, the propeller type children are provided with a signal receiving and control unit, and the wing tip is rotatably connected with a main propeller. In the take-off stage, the propeller type children are connected to the wing, and the main propeller and the propeller of the plurality of propeller type children are arranged vertically to the ground and upward, solving the problem that the unmanned mother-child aircraft is not convenient to take off in the extreme environment.

Description

Technical Field

[0001] This invention belongs to the field of aircraft aerodynamic layout design, and particularly relates to a distributed power cluster unmanned mother-daughter aircraft and its usage method. Background Technology

[0002] Currently, with the continuous development of drone technology, the types and numbers of drones are rapidly increasing, and the layout, functions, and application scenarios of drones are constantly breaking through. However, single-type drones often cannot meet the needs of multi-mission objectives, which has spurred the rapid development and multi-field application of swarm drones. In the military field, swarm drones are gradually becoming one of the most active elements on the battlefield. In the civilian field, the application of swarm drones is also becoming increasingly widespread, such as in logistics transportation, agricultural plant protection, and environmental monitoring, which requires drones to have higher levels of intelligence and swarm operation capabilities. It can be seen that swarm drones have huge application prospects in both the military and civilian fields. Therefore, it is necessary to conduct research on swarm drones, accumulate technical experience, empower advanced technologies such as artificial intelligence and directed energy, accelerate the transformation of scientific and technological achievements, and promote the leapfrog development of the swarm drone field.

[0003] Swarm drones are not suitable for long-distance flights, so they are often transported to the target area by a carrier aircraft before being released. Invention patent CN108216621A discloses a wingtip-connected parallel mother-daughter aircraft, and utility model patent CN207191430U discloses a maritime search unmanned aerial vehicle mother-daughter system. Both use a carrier aircraft to transport the swarm drones. However, existing carrier aircraft all use taxiing takeoff and landing, which is unsuitable for takeoff in extreme environments such as islands, reefs, and dense forests. Summary of the Invention

[0004] The purpose of this invention is to provide a distributed-powered swarm-type unmanned mother-and-child aircraft and its usage method, to solve the problem that existing swarm-type unmanned mother-and-child aircraft are unsuitable for takeoff in extreme environments such as islands, reefs, and dense forests. The technical solution adopted by this invention is as follows: A distributed-powered cluster-type unmanned mother-daughter aircraft includes a carrier aircraft, which includes a fuselage, a horizontal stabilizer mounted at the tail of the fuselage via a vertical stabilizer, wings on both sides of the fuselage, an inner flap, an outer flap and an aileron on the trailing edge of the wings, and several propeller-type daughter aircraft. Several shafts are spaced along the spanwise direction on the leading edge of the wings, and the several propeller-type daughter aircraft correspond one-to-one with the several shafts and can be detachably connected. The propeller-type daughter aircraft have built-in signal receiving and control units, and the wingtips of the wings are rotatably equipped with main propellers. During takeoff, the propeller-driven sub-engines are attached to the wings, with the main propeller and the propellers of the sub-engines all positioned vertically upwards. During cruise, the propeller-driven sub-engines are attached to the wings, with the main propeller and the propellers of the sub-engines all positioned horizontally forwards. During the mission phase, the propeller-driven sub-engines detach from the wings and form a mission group.

[0005] Furthermore, the rotating shaft is equipped with a slide rail seat, and the propeller-type submachine gun is equipped with a slider. When the propeller-type submachine gun is connected to the wing, the slider and the slide rail seat engage and lock mechanically.

[0006] Furthermore, eight propeller-driven sub-engines are symmetrically arranged, with four propeller-driven sub-engines on each wing.

[0007] Furthermore, the wings are high-wing monoplanes.

[0008] Furthermore, the leading edge of the wing is not swept.

[0009] Furthermore, the main propeller is connected to the power system via a pivoting mechanism.

[0010] This invention also provides a method for using a distributed-powered swarm unmanned mother-daughter aircraft, which is based on the aforementioned distributed-powered swarm unmanned mother-daughter aircraft and includes the following steps: Step 1, takeoff phase: The main propeller and the propellers of each propeller-type sub-machine serve as power units, deflecting vertically upwards to enable the unmanned mother-daughter aircraft to take off vertically. Step 2: When the unmanned mother-daughter aircraft exceeds the height of the takeoff obstacle, it enters the transition phase. The main propeller and the propellers of each propeller-type daughter aircraft gradually deflect forward from vertical upward. The transition phase ends when the cruise altitude is reached. Step 3, cruise phase: The main propeller and the propellers of each propeller-type sub-machine serve as power units, deflecting forward to provide the thrust required for the unmanned mother-daughter aircraft to cruise at high speed. At the same time, the unmanned mother-daughter aircraft is maneuvered by relying on the inner flaps, outer flaps and ailerons to efficiently reach the designated area, and the high-speed cruise phase ends. Step 4, Airborne Separation Phase: The propellers of each propeller-driven sub-unit rotate vertically upwards, causing the unmanned mother-daughter aircraft to hover in the air. The slider is unlocked from the slide rail via signal control. Each propeller-driven sub-unit uses its own power to detach the slider from the slide rail. After each propeller-driven sub-unit separates from the wings, it is used as a small swarm of unmanned aerial vehicles to independently carry out the mission phase. The built-in signal receiving and control unit of the propeller-driven sub-unit is activated, and it completes heading control by receiving signals from the base to reach the work area. Step 5, the return phase: The main propeller serves as the power unit, and the mother aircraft is maneuvered using the inner flaps, outer flaps, and ailerons to return to base. After returning, the mother aircraft undergoes maintenance to prepare for the next mission.

[0011] Compared with the prior art, the beneficial effects of the present invention are as follows: In the takeoff phase, the main propeller and several propeller-type sub-machines of this invention rotate vertically upward to provide upward thrust, facilitating takeoff and mission completion in extreme environments such as islands, reefs, and dense forests. This saves on runway costs and improves operational mobility. In the cruise phase, the main propeller and several propeller-type sub-machines rotate horizontally forward to provide forward thrust. By rotating the main propeller and several propeller-type sub-machines, the invention solves the problems of inconvenient takeoff in extreme environments and slow flight speed during the cruise phase. Attached Figure Description

[0012] Figure 1 This is an isometric view of the vertical takeoff phase of the unmanned mother-daughter aircraft of the present invention; Figure 2 This is a top view of the vertical takeoff phase of the unmanned mother-daughter aircraft of the present invention; Figure 3 This is a front view of the vertical takeoff phase of the unmanned mother-daughter aircraft of the present invention; Figure 4 This is a schematic diagram of the transition phase state of the unmanned mother-daughter aircraft of the present invention; Figure 5 This is a schematic diagram of the cruise phase status of the unmanned mother-daughter aircraft of the present invention; Figure 6 This is a schematic diagram of the return phase after the mother aircraft releases the propeller-driven daughter aircraft. Figure 7 This is a schematic diagram of a drone swarm formed by several propeller-driven sub-machines after separation from the airborne aircraft. Figure 8 This is a schematic diagram of the connection between the slide rail base and the slider.

[0013] In the diagram, 1. horizontal stabilizer, 2. vertical stabilizer, 3. fuselage, 4. inner flap, 5. outer flap, 6. aileron, 7. main propeller, 8. propeller-driven sub-engine, 9. wing, 10. slide rail, 11. slider, 12. pivot. Detailed Implementation

[0014] To make the objectives, technical solutions, and advantages of this invention clearer, the invention is described below with reference to specific embodiments shown in the accompanying drawings. However, it should be understood that these descriptions are merely exemplary and not intended to limit the scope of the invention. Furthermore, descriptions of well-known structures and technologies are omitted in the following description to avoid unnecessarily obscuring the concept of the invention.

[0015] The connections mentioned in this invention are divided into fixed connections and detachable connections. Fixed connections, also known as non-detachable connections, include but are not limited to conventional fixed connection methods such as folded connections, riveted connections, adhesive connections, and welded connections. Detachable connections include but are not limited to conventional disassembly methods such as bolted connections, snap-fit ​​connections, pin connections, and hinged connections. When a specific connection method is not explicitly defined, it is assumed that at least one existing connection method can be found to achieve this function, and those skilled in the art can choose according to their needs. For example, a welded connection can be chosen for fixed connections, and a bolted connection can be chosen for detachable connections.

[0016] The present invention will be further described in detail below with reference to the accompanying drawings. The following embodiments are explanations of the present invention, but the present invention is not limited to the following embodiments.

[0017] Example 1: As Figures 1 to 8 As shown, a distributed-powered cluster-type unmanned mother-daughter aircraft includes a carrier aircraft, which includes a fuselage 3, a horizontal stabilizer 1 and a vertical stabilizer 2 at the tail of the fuselage 3, wings 9 on both sides of the fuselage 3, an inner flap 4, an outer flap 5 and an aileron 6 on the trailing edge of the wings 9, and several propeller-type daughter aircraft 8. Several rotating shafts 12 are arranged at intervals along the span of the leading edge of the wings 9. The several propeller-type daughter aircraft 8 are detachably connected to the several rotating shafts 12 in a one-to-one correspondence. The propeller-type daughter aircraft 8 have built-in signal receiving and control units. The wingtips of the wings 9 are rotatably equipped with main propellers 7. During takeoff, the propeller-driven sub-units 8 are connected to the wing 9, and the propellers of the main propeller 7 and the propellers of the several propeller-driven sub-units 8 are all set vertically upward. During cruise, the propeller-driven sub-units 8 are connected to the wing 9, and the propellers of the main propeller 7 and the several propeller-driven sub-units 8 are all set horizontally forward. During the mission phase, the several propeller-driven sub-units 8 detach from the wing 9 and form a mission group. The mission phase refers to the phase in which the several propeller-driven sub-units 8 detach from the carrier aircraft and independently perform operational tasks.

[0018] In the takeoff phase, the main propeller 7 and several propeller-type sub-machines 8 of this invention rotate vertically upward to provide upward thrust, facilitating takeoff and completion of operational tasks in extreme environments such as islands, reefs, and dense forests. This saves on runway costs and improves operational maneuverability. In the cruise phase, the main propeller 7 and several propeller-type sub-machines 8 rotate horizontally forward to provide forward thrust. By rotating the main propeller 7 and several propeller-type sub-machines 8, the problems of inconvenient takeoff in extreme environments and slow flight speed during the cruise phase of the unmanned mother-daughter aircraft are solved.

[0019] Eight propeller-type sub-engines 8 are symmetrically arranged, with four propeller-type sub-engines 8 on each wing 9.

[0020] The main propeller 7 is connected to the power system via a pivoting mechanism.

[0021] Wing 9 is a high-wing monoplane, which increases stability during cruise.

[0022] The leading edge of wing 9 has no swept wing, which facilitates the arrangement of distributed leading edge propellers 8.

[0023] The rotating shaft 12 is equipped with a slide rail seat 10, and the propeller-type sub-machine 8 is equipped with a slider 11. When the propeller-type sub-machine 8 is connected to the wing 9, the slider 11 engages with the slide rail seat 10 and is mechanically locked in place. Figure 8 As shown.

[0024] Example 2: Figures 1 to 8 As shown, a method for using a distributed-powered swarm unmanned mother-daughter aircraft, based on the distributed-powered swarm unmanned mother-daughter aircraft described in Embodiment 1, includes the following steps: Step 1, Takeoff Phase: The main propeller 7 and the propellers of each propeller-type sub-machine 8 serve as power units, deflecting vertically upwards to allow the unmanned mother-daughter aircraft to take off vertically. Figures 1-3 As shown; Step 2: When the unmanned mother-daughter aircraft exceeds the height of the takeoff obstacle, it enters the transition phase. The propellers of the main propeller 7 and each propeller-type daughter aircraft 8 gradually deflect forward from vertically upward, as shown below. Figure 4 As shown, during this phase, the thrust of the power system is directed diagonally upward, providing both forward and upward thrust simultaneously. The transition phase ends when the cruising altitude is reached. Step 3, Cruise Phase: The main propeller 7 and the propellers of each propeller-type sub-machine 8 serve as power units, deflecting forward to provide the thrust required for the unmanned mother-daughter aircraft to cruise at high speed. Figure 5 As shown, the unmanned mother-daughter aircraft is maneuvered by relying on the inner flap 4, the outer flap 5 and the aileron 6 to efficiently reach the designated area, and the cruise phase ends. Step 4, Airborne Separation Phase: The propellers of each propeller-driven sub-unit 8 rotate vertically upwards, causing the unmanned mother-daughter aircraft to hover in the air. The slider 11 is unlocked from the slide rail 10 via signal control. Each propeller-driven sub-unit 8 uses its own power to detach the slider 11 from the slide rail 10. After separating from the wings 9, each propeller-driven sub-unit 8 functions as a small swarm of unmanned aerial vehicles, independently performing its mission. The built-in signal receiving and control units of the propeller-driven sub-unit 8 are activated, receiving signals from the base to control its course and reach the operational area. Figure 7 As shown, swarm drones can form a formation according to the mission objective and can complete tasks such as environmental surveying and logistics transportation. Step 5, the return phase: The main propeller 7 serves as the power unit, and the mother aircraft is maneuvered using the inner flaps 4, outer flaps 5, and ailerons 6 to return to its starting position. Figure 6 As shown, the carrier aircraft undergoes maintenance after returning to base to prepare for the next mission.

[0025] The fuselage 3 of the carrier aircraft is 8.32 meters long, has a volume of 10.50 cubic meters, a top-view projected area of ​​5.28 square meters, and a side-view projected area of ​​5.55 square meters. The wing 9 has a GAW-1 airfoil, a span of 15.75 meters, a wingtip chord of 0.87 meters, a root chord of 1.16 meters, a leading-edge sweep angle of 5.50°, and a top-view projected area of ​​7.19 square meters. The horizontal stabilizer 1 uses a NACA0012 airfoil, with a span of 1.55 meters, a wingtip chord of 0.76 meters, a root chord of 0.91 meters, a leading-edge sweep angle of 8.62°, a trailing-edge sweep angle of 4.50°, and a top-view projected area of ​​1.06 square meters. The vertical stabilizer 2 has an airfoil of NACA0012, a height of 1.38 meters, a leading-edge sweep angle of 14.78°, and no trailing-edge sweep. A simple aerodynamic design is used at the junction of the vertical stabilizer 2 and fuselage 3 to ensure a smooth transition and improve aerodynamic performance. The inner flap 4 extends from 15% to 40% of the wingspan, with a chord length of 26% relative to the local chord. The outer flap 5 extends from 40% to 65% of the wingspan, with a chord length equivalent to 26% of the local chord. The inner flap 4 and outer flap 5 can be integrated and operated simultaneously or separately, with a flap deflection of ±30 degrees. The aileron 6 extends from 65% to 80% of the wingspan, with a chord length of 26% relative to the local chord, and a deflection of ±20 degrees. The main propeller 7 has an airfoil of SC1095, a blade angle of 43.75°, a disk diameter of 2.15 meters, and a hub length of 2.68 meters. The main propeller 7 is connected to the wingtip of the wing 9 via a pivot mechanism, allowing it to rotate from a horizontal to a vertical position. The propeller-type sub-engine 8 also has an airfoil of SC1095, a blade angle of 43.75°, a disk diameter of 1.08 meters, and a hub length of 0.87 meters. The propeller-type sub-engine 8 is connected to the leading edge of the wing 9 via a pivot shaft 1210, allowing each propeller-type sub-engine 8 to rotate from a horizontal to a vertical position.

[0026] The above embodiments are merely illustrative examples of the present invention and do not limit its scope of protection. Those skilled in the art can make partial changes to them, as long as they do not exceed the spirit and essence of the present invention, they are all within the scope of protection of the present invention.

Claims

1. A distributed-powered cluster-type unmanned mother-daughter aircraft, comprising a carrier aircraft, the carrier aircraft comprising a fuselage (3), a horizontal stabilizer (1) disposed at the tail of the fuselage (3) via a vertical stabilizer (2), and wings (9) provided on both sides of the fuselage (3), the trailing edges of the wings (9) being provided with inner flaps (4), outer flaps (5) and ailerons (6), characterized in that: It also includes several propeller-type submachines (8), and several rotating shafts (12) are arranged at spanwise intervals along the leading edge of the wing (9). The several propeller-type submachines (8) and several rotating shafts (12) correspond to each other and can be detached and connected. The propeller-type submachines (8) have built-in signal receiving and control units, and the wingtip of the wing (9) is equipped with a main propeller (7). During takeoff, the propeller-driven sub-machines (8) are connected to the wings (9), and the propellers of the main propeller (7) and several propeller-driven sub-machines (8) are all set vertically upward. During cruise, the propeller-driven sub-machines (8) are connected to the wings (9), and the propellers of the main propeller (7) and several propeller-driven sub-machines (8) are all set horizontally forward. During mission, several propeller-driven sub-machines (8) are detached from the wings (9) and form a mission group.

2. The distributed-powered cluster-type unmanned mother-daughter aircraft according to claim 1, characterized in that: The rotating shaft (12) is provided with a slide rail seat (10), and the propeller-type submachine (8) is provided with a slider (11). When the propeller-type submachine (8) is connected to the wing (9), the slider (11) and the slide rail seat (10) are engaged and mechanically locked.

3. The distributed-powered cluster-type unmanned mother-daughter aircraft according to claim 2, characterized in that: Eight propeller-type sub-engines (8) are symmetrically arranged, with four propeller-type sub-engines (8) on each wing (9).

4. The distributed-powered cluster-type unmanned mother-daughter aircraft according to claim 1, characterized in that: The wing (9) is a high-wing monoplane.

5. A distributed-powered cluster-type unmanned mother-daughter aircraft according to claim 1, characterized in that: The leading edge of the wing (9) is not swept.

6. A distributed-powered cluster-type unmanned mother-daughter aircraft according to any one of claims 1-5, characterized in that: The main propeller (7) is connected to the power system via a pivoting mechanism.

7. A method of using a distributed-powered swarm-type unmanned mother-daughter aircraft, implemented based on the distributed-powered swarm-type unmanned mother-daughter aircraft described in any one of claims 1-6, characterized in that, Includes the following steps: Step 1, takeoff phase: The propellers of the main propeller (7) and each propeller-type sub-machine (8) serve as power units and deflect to the vertical upward, so that the unmanned mother-daughter aircraft can take off vertically. Step 2: When the unmanned mother-daughter aircraft exceeds the height of the takeoff obstacle, it enters the transition phase. The propellers of the main propeller (7) and each propeller-type sub-machine (8) gradually deflect forward from vertical upward. The transition phase ends when the cruise altitude is reached. Step 3, cruise phase: The main propeller (7) and the propellers of each propeller-type submachine (8) serve as power units, deflecting forward to provide the thrust required for the unmanned mother-daughter aircraft to cruise at high speed. At the same time, the unmanned mother-daughter aircraft is maneuvered by relying on the inner flap (4), outer flap (5) and aileron (6) to efficiently reach the designated area, and the high-speed cruise phase ends. Step 4, the airborne separation stage: the propellers of each propeller-driven sub-unit (8) rotate vertically upward, causing the unmanned mother-daughter aircraft to hover in the air. The slider (11) is unlocked from the slide rail (10) by signal control. Each propeller-driven sub-unit (8) uses its own power to detach the slider (11) from the slide rail (10). After each propeller-driven sub-unit (8) separates from the wings (9), it is used as a small cluster of unmanned aerial vehicles to carry out the mission independently. The signal receiving and control unit built into the propeller-driven sub-unit (8) is activated. It completes the heading control by receiving the base signal and reaches the work area. Step 5, the return phase: The main propeller (7) serves as the power unit and is maneuvered by the inner flap (4), outer flap (5) and aileron (6) to return the carrier aircraft. After the carrier aircraft returns, it is repaired and prepared for the next mission.

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