阅读说明：本技术 一种组合式垂直起降飞行器及其起降方法 (Combined vertical take-off and landing aircraft and take-off and landing method thereof ) 是由 周正光 王启 李悦立 李宇峰 李焦赞 于 2020-12-29 设计创作，主要内容包括：本发明属于飞行器设计领域,具体涉及一种组合式垂直起降飞行器及其起降方法。组合式垂直起降飞行器包括：任务飞行器(1)、拉索(2)和运载飞行器(3),其中,起飞和降落阶段,拉索(2)上端与运载飞行器(3)的机身(301)下的吊挂点连接,拉索(2)下端与任务飞行器(1)的吊挂点(111)连接,通过运载飞行器(3)带动任务飞行器(1)起飞和降落。能够在没有跑道的情况下,实现飞行器的垂直起飞、水平高速飞行和垂直降落；兼具直升机飞行器垂直起降和固定翼飞行器高速飞行的优点。(The invention belongs to the field of aircraft design, and particularly relates to a combined vertical take-off and landing aircraft and a take-off and landing method thereof. The combined vertical take-off and landing aircraft comprises: the aircraft comprises a task aircraft (1), a stay cable (2) and a carrier aircraft (3), wherein in the taking-off and landing stages, the upper end of the stay cable (2) is connected with a hanging point below an aircraft body (301) of the carrier aircraft (3), the lower end of the stay cable (2) is connected with a hanging point (111) of the task aircraft (1), and the task aircraft (1) is driven to take-off and land through the carrier aircraft (3). The vertical take-off, horizontal high-speed flight and vertical landing of the aircraft can be realized under the condition of no runway; the helicopter has the advantages of vertical take-off and landing of the helicopter and high-speed flight of the fixed wing aircraft.)

1. A modular vtol aerial vehicle, comprising: the aircraft comprises a task aircraft (1), a stay cable (2) and a carrier aircraft (3), wherein in the taking-off and landing stages, the upper end of the stay cable (2) is connected with a hanging point below an aircraft body (301) of the carrier aircraft (3), the lower end of the stay cable (2) is connected with a hanging point (111) of the task aircraft (1), and the task aircraft (1) is driven to take-off and land through the carrier aircraft (3).

2. The aircraft according to claim 1, characterized in that the vehicle (3) is a multi-rotor aircraft comprising a fuselage (301), at least four rotors (302) and at least four booms (303), wherein the at least four rotors (302) are distributed around the fuselage (301) and are connected to the fuselage (301) by the booms (303), respectively.

3. The aircraft according to claim 1, characterized in that a towing device 110 is arranged above the mission aircraft (1), wherein the towing device (110) comprises a pull rod (101), a rear pull cable (102), a left pull cable (103), a right pull lock (104) and a towing point (111), and the pull rod (101), the rear pull cable (102), the left pull cable (103) and the right pull lock (104) converge at the towing point (111).

4. The aircraft according to claim 3, characterized in that the lower intersection point of the tie rod (101) is mounted at a lifting point above the fuselage, which lifting point is located in front of the centre of gravity of the aircraft and about which lifting point the tie rod (101) can be rotated in the plane of symmetry of the aircraft; the lower intersection point of the rear guy cable (102) is arranged on a lifting point above the fuselage, the lifting point is positioned behind the gravity center of the aircraft, and on the symmetrical plane of the aircraft, the rear guy cable (102) can extend and contract around the lifting point; the lower intersection points of the left guy cable (103) and the right zipper (104) are respectively and symmetrically arranged on lifting points of wings on two sides, the heading position of the lifting point is positioned near the gravity center of the aircraft, and the left guy cable (103) and the right zipper (104) can extend and contract around the lifting points.

5. The aircraft according to claim 1, characterized in that the guy wires (2) are freely bendable ropes, the tensile load of the guy wires (2) being more than 1.5 times the weight of the mission aircraft (1).

6. A takeoff method of a combined vertical take-off and landing aircraft is characterized by comprising the following steps:

connecting the mission aircraft (1) and the carrier aircraft (3) together through a guy cable (2);

enabling the carrier aircraft (3) to take off, and when the carrier aircraft (3) flies above the mission aircraft (1), hanging the mission aircraft (1) off the ground through the guy cable (2) to enter a hovering state;

after the mission aircraft (1) is lifted off the ground and enters a hovering state, the carrier aircraft (3) is enabled to tilt forward, and the mission aircraft (1) is dragged to fly forward in an accelerating manner;

when the mission aircraft (1) reaches the minimum forward flight speed of the aircraft, starting a power device (131) of the mission aircraft (1);

after a power device (131) of the mission aircraft (1) is started, the mission aircraft (1) is disconnected from the inhaul cable (2).

7. The method of claim 6, further comprising: after the mission aircraft (1) is disconnected with the guy cable (2), the carrying aircraft (3) returns to the ground.

8. A method of landing a combined vtol aircraft, comprising:

the carrier aircraft (3) maintains a forward flight state at the minimum forward flight speed of the mission aircraft (1);

the mission aircraft (1) approaches the carrier aircraft (3) from the right rear part of the carrier aircraft (3), and a hanging point (111) is connected with the inhaul cable (2);

after the mission aircraft (1) and the carrier aircraft (3) are connected through the guy cable (2), the carrier aircraft (3) flies before increasing horsepower, meanwhile, a power device (131) of the mission aircraft (1) is shut down, and the mission aircraft (1) is dragged by the carrier aircraft (3) to fly before decelerating;

after the mission aircraft (1) decelerates to a hovering state, the carrier aircraft (3) vertically descends until the mission aircraft (1) lands on the ground.

Technical Field

The invention belongs to the field of aircraft design, and particularly relates to a combined vertical take-off and landing aircraft and a take-off and landing method thereof.

Background

Conventional VTOL aerial vehicles such as helicopters and tiltrotor aircraft. The helicopter takes off by the lift that rotor produced, and through controlling rotor small-amplitude slope after the flight, produces the pulling force of flight forward, realizes that the helicopter flies forward, but receives the influence of rotor aerodynamic efficiency, and the preceding flying speed that can reach is low. A tilt rotor aircraft, the rotors of which can tilt in the vertical and horizontal ranges; during taking off, the rotor wing is in a vertical state to generate upward lift force, so that the airplane can take off vertically; after taking off, the rotor wing tilts to the horizontal state to generate forward pulling force, so that the forward flying of the airplane is realized; the tilting mechanism of the aircraft is very complex and heavy, so that the weight efficiency of the effective task load is low; the rotor wing needs to take two working conditions of vertical takeoff and forward flight into consideration, so that the rotor wing is low in efficiency; and the power during takeoff is far larger than that required by forward flight, so that great difficulty is brought to the design and the service life of the engine.

Disclosure of Invention

The purpose of the invention is as follows: a combined vertical take-off and landing aircraft and a take-off and landing method thereof are provided to realize high-speed flight of a mission aircraft without a runway.

The technical scheme is as follows:

in a first aspect, a combined vertical take-off and landing aircraft is provided, comprising: the aircraft comprises a task aircraft 1, a guy cable 2 and a carrier aircraft 3, wherein in the taking-off and landing stages, the upper end of the guy cable 2 is connected with a hanging point under an aircraft body 301 of the carrier aircraft 3, the lower end of the guy cable 2 is connected with a hanging point 111 of the task aircraft 1, and the task aircraft 1 is driven to take-off and land through the carrier aircraft 3.

Further, the carrier vehicle 3 is a multi-rotor vehicle, and includes a fuselage 301, at least four rotors 302, and at least four booms 303, wherein the at least four rotors 302 are dispersedly disposed around the fuselage 301, and are respectively connected to the fuselage 301 through the booms 303.

Furthermore, a hanging device 110 is arranged above the mission aircraft 1, wherein the hanging device 110 comprises a pull rod 101, a rear pull cable 102, a left pull cable 103, a right pull lock 104 and a hanging point 111, and the pull rod 101, the rear pull cable 102, the left pull cable 103 and the right pull lock 104 are converged at the hanging point 111.

Furthermore, the lower intersection point of the pull rod 101 is installed on a lifting point above the fuselage, the lifting point is positioned in front of the center of gravity of the aircraft, and the pull rod 101 can rotate around the lifting point on the symmetrical plane of the aircraft; the lower intersection point of the rear guy cable 102 is arranged on a lifting point above the fuselage, the lifting point is positioned behind the gravity center of the aircraft, and on the symmetrical plane of the aircraft, the rear guy cable 102 can extend and contract around the lifting point; the lower intersection points of the left guy cable 103 and the right zipper 104 are respectively and symmetrically arranged on the lifting points of the wings on two sides, the heading position of the lifting point is positioned near the gravity center of the aircraft, and the left guy cable 103 and the right zipper 104 can extend and contract around the lifting points.

Further, the guy cable 2 is a rope capable of freely bending, and the tensile load of the guy cable 2 is more than 1.5 times of the weight of the mission aircraft 1.

In a second aspect, a takeoff method for a combined vertical take-off and landing aircraft is provided, which includes:

connecting the mission aircraft 1 and the carrier aircraft 3 together through a guy cable 2;

enabling the carrier aircraft 3 to take off, and when the carrier aircraft 3 flies above the task aircraft 1, hanging the task aircraft 1 off the ground through the guy cable 2 to enter a hovering state;

after the mission aircraft 1 is lifted off the ground and enters a hovering state, the carrier aircraft 3 is inclined forward, and the mission aircraft 1 is dragged to fly forward in an accelerated manner;

when the mission aircraft 1 reaches the minimum forward flight speed of the aircraft, starting the power device 131 of the mission aircraft 1;

after the power device 131 of the mission aircraft 1 is started, the mission aircraft 1 is disconnected with the inhaul cable 2;

further, still include: after the mission aircraft 1 is disconnected from the guy cable 2, the carrier aircraft 3 returns to the ground.

In a third aspect, there is provided a landing method for a combined vertical take-off and landing aircraft, comprising:

the carrier vehicle 3 maintains the forward flight state at the minimum forward flight speed of the mission vehicle 1;

the mission aircraft 1 approaches the carrier aircraft 3 from the right back of the carrier aircraft 3, and a hanging point 111 is connected with the inhaul cable 2;

after the cable 2 connects the mission aircraft 1 and the carrier aircraft 3, the carrier aircraft 3 flies before increasing horsepower, and meanwhile, the power device 131 of the mission aircraft 1 is shut down, and the mission aircraft 1 is dragged by the carrier aircraft 3 to fly before decelerating;

after the mission aircraft 1 decelerates to the hovering state, the carrier aircraft 3 is vertically descended until the mission aircraft 1 lands on the ground.

Has the advantages that:

the combined vertical take-off and landing aircraft can realize vertical take-off, horizontal high-speed flight and vertical landing of the aircraft under the condition of no runway; the helicopter has the advantages of vertical take-off and landing of the helicopter aircraft and high-speed flight of the fixed wing aircraft; after the carrier aircraft and the task aircraft are separated, the task aircraft independently executes tasks, and compared with the traditional vertical take-off and landing aircraft, the vertical take-off and landing module is separated, so that the task aircraft can be designed more ingeniously, the weight of an air machine is reduced, and the service efficiency of the task aircraft is improved.

Drawings

FIG. 1 is a schematic structural view of a modular VTOL aerial vehicle of the present invention;

fig. 2 is a schematic structural diagram of a mission aircraft.

FIG. 3 is a schematic view of the combined VTOL aircraft during an initial takeoff phase.

FIG. 4 is a schematic diagram of a vertical ascent preparation phase of the combination VTOL aircraft.

FIG. 5 is a schematic diagram of vertical ascent of a combined VTOL aerial vehicle.

Fig. 6 is a schematic view of the combined vertical take-off and landing aircraft in a forward flight state.

FIG. 7 is a schematic structural diagram of a hangar in a forward flight state of a mission aircraft.

Fig. 8 is a schematic view of the separation state of the mission aircraft and the carrier aircraft.

Fig. 9 is a schematic view of a mission aircraft approaching a carrier aircraft.

Wherein, the mission aircraft 1, the guy cable 2, the carrier aircraft 3, the pull rod 101, the rear guy cable 102, the left guy cable 103, the right zip 104, the wing 121, the power device 131, the hanging point 111, the hanging device 110, the fuselage 301, the rotor wing 302, the cantilever 303

Detailed Description

In order to achieve high-speed flight of mission aircraft without runways. The invention provides a combined vertical take-off and landing aircraft.

In a possible embodiment of the invention, the combined vertical take-off and landing aircraft is composed of a mission aircraft 1, a guy cable 2 and a carrier aircraft 3. Mission aircraft 1 is a fixed wing aircraft and carrier aircraft 3 is a multi-rotor aircraft. During taking off, the carrier aircraft and the mission aircraft are connected together to form an integral combined aircraft, and the rotor wing of the carrier aircraft provides lift force required by vertical taking off; after taking off, the combined aircraft leans forward to a forward flight state, and in the process, an engine of the mission aircraft is started, and the engine provide upward lift force and forward flight power at the same time; when the combined aircraft reaches the minimum flying speed of the fixed wing, the separation stage is started, the carrying aircraft and the combined aircraft are separated, two independent aircraft are formed, the carrying aircraft can return to an airport, and the mission aircraft independently executes missions; when the mission aircraft returns, the carrier aircraft enters an inclined forward flight state and reaches the minimum flying speed of the fixed wing, and the mission aircraft keeps the same speed and performs air butt joint; after docking, the combined aircraft tilts backwards to a vertical state, the mission aircraft shuts down, and the rotor wing of the carrier aircraft provides lift force to implement vertical landing.

The following detailed description is made with reference to the accompanying drawings.

Referring to fig. 1, the combined vertical take-off and landing aircraft is composed of a mission aircraft 1, a guy cable 2 and a carrier aircraft 3. Referring to fig. 2, the mission aircraft 1 is a fixed wing aircraft, which has the same basic composition as a conventional fixed wing aircraft, and comprises wings 121, a towing device 110 and a power device 131, wherein the towing device 110 comprises a pull rod 101, a rear pull cable 102, a left pull cable 103 and a right zipper 104. The pull rod 101, the rear pull rope 102, the left pull rope 103 and the right pull lock 104 are converged at a hanging point 111. The lower intersection of the drawbar 101 is mounted at a lifting point above the fuselage, which is located in front of the centre of gravity of the aircraft and about which the drawbar 101 is rotatable in the plane of symmetry of the aircraft. The lower intersection of the rear cable 102 is mounted at a lifting point above the fuselage, which is located behind the centre of gravity of the aircraft and about which the rear cable 102 can be lengthened or shortened in the plane of symmetry of the aircraft. The lower intersection points of the left guy cable 103 and the right zipper 104 are respectively and symmetrically arranged on the lifting points of the wings on two sides, the heading position of the lifting point is positioned near the gravity center of the aircraft, and the left guy cable 103 and the right zipper 104 can extend and contract around the lifting points.

The vehicle 3 is a multi-rotor aircraft, which in one possible embodiment consists of a fuselage 301, 8 rotors 302 and 8 booms 303. 8 rotors 302 are distributed around the fuselage 301 and connected to the fuselage 301 by cantilevers 303. The 8 rotors 302 generate lift force to realize vertical ascending, hovering and forward flying of the carrier vehicle 3. The inhaul cable 2 is a flexible high-strength steel wire rope, and the tensile load of the inhaul cable 2 is 1.5 times of the weight of the mission aircraft 1; the upper end of the guy cable 2 is connected with a hanging point under the fuselage 301 of the carrier aircraft 3, and the lower end of the guy cable 2 is connected with a hanging point 111 of the mission aircraft 1.

The take-off process of the combined vertical take-off and landing aircraft can be divided into 5 stages:

takeoff stage 1: under the ground state, the mission aircraft 1 and the carrier aircraft 3 are connected together through a guy cable 2, as shown in FIG. 3;

a takeoff stage 2: after taking off, the carrier aircraft 3 flies above the task aircraft 1, as shown in fig. 4, and the task aircraft 1 is lifted off the ground by the guy cable 2 to enter a hovering state, as shown in fig. 5;

takeoff stage 3: the carrier aircraft 3 inclines forwards, and the mission aircraft 1 is dragged to accelerate to fly forwards, as shown in fig. 6 and 7, at this stage, the mission aircraft 1 has low forward flying speed, the wings 121 generate insufficient lift force, and cannot completely overcome the gravity of the aircraft, and the pull force provided by the guy cable 2 overcomes the gravity of the aircraft and the resistance suffered by the forward flying;

a takeoff stage 4: when the mission aircraft 1 reaches the minimum forward flight speed of the aircraft, the power device 131 of the mission aircraft 1 is started to generate forward pulling force so as to overcome the resistance on the forward flight of the aircraft;

a takeoff stage 5: after the power device 131 of the mission aircraft 1 is started, the guy cable 2 is separated from the hanging point 111, the mission aircraft 1 continues flying forward to execute a flight mission, and the carrier aircraft 3 returns to the ground as shown in fig. 8.

The landing process of the combined vertical take-off and landing aircraft can be divided into 5 stages:

a landing stage 1: when the mission aircraft 1 finishes the flight mission and returns to the flight, the carrier aircraft 3 takes off for standby and maintains the forward flight state at the minimum forward flight speed of the mission aircraft 1;

a falling stage 2: the mission aircraft 1 approaches the carrier aircraft 3 from right behind the carrier aircraft 3 at the minimum forward flying speed, as shown in fig. 9, and connects the suspension point 111 with the guy cable 2;

a falling stage 3: after the mission aircraft 1 and the carrier aircraft 3 are connected by the guy cable 2, the carrier aircraft 3 flies before increasing horsepower, and meanwhile, the power device 131 of the mission aircraft 1 is shut down, and the mission aircraft 1 is dragged by the carrier aircraft 3 to fly before decelerating;

and (4) a falling stage: when the mission aircraft 1 flies forwards at a reduced speed, the mission aircraft 1 flies forwards at a low speed, the wings 121 generate insufficient lift force, the gravity of the aircraft cannot be completely overcome, and the pull force provided by the guy cable 2 overcomes the gravity of the aircraft and the resistance on the forward flight;

a falling stage 5: after the mission aircraft 1 decelerates to the hovering state, the carrier aircraft 3 slowly descends vertically, the mission aircraft 1 lands on the ground, and then the carrier aircraft 3 lands on the ground near the mission aircraft 1.

The combined vertical take-off and landing aircraft provided by the invention can realize vertical take-off, horizontal high-speed flight and vertical landing of the aircraft under the condition of no runway; the helicopter has the advantages of vertical take-off and landing of the helicopter aircraft and high-speed flight of the fixed wing aircraft; after the carrier aircraft and the task aircraft are separated, the task aircraft independently executes tasks, and compared with the traditional vertical take-off and landing aircraft, the vertical take-off and landing module is separated, so that the task aircraft can be designed more ingeniously, the weight of an air machine is reduced, and the service efficiency of the task aircraft is improved.