CN113044217A - Aircraft capable of carrying fixed-wing aircraft to take off and land vertically, carrying method, vertical takeoff method and vertical landing method - Google Patents
Aircraft capable of carrying fixed-wing aircraft to take off and land vertically, carrying method, vertical takeoff method and vertical landing method Download PDFInfo
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- CN113044217A CN113044217A CN201911383896.5A CN201911383896A CN113044217A CN 113044217 A CN113044217 A CN 113044217A CN 201911383896 A CN201911383896 A CN 201911383896A CN 113044217 A CN113044217 A CN 113044217A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D5/00—Aircraft transported by aircraft, e.g. for release or reberthing during flight
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Abstract
An aircraft capable of carrying a fixed-wing aircraft to take off and land vertically comprises a lift engine, a thrust power unit, a butt joint locking system, an aircraft body and wings; the lift force engines are arranged on two opposite sides of the machine body and are used for providing vertical lift force; the thrust power unit is a thrust vector engine or a thrust engine, is arranged at the tail part of the engine body and is used for providing horizontal thrust; the butt joint locking system is arranged at the back of the airplane body and used for being connected with the fixed-wing airplane; the wings are arranged on two opposite sides of the body and are used for providing lift force. The aircraft has the vertical takeoff function under the full-load state of the piggyback fixed wing aircraft, so that the traditional fixed wing aircraft has the functions of vertical takeoff and landing without large-scale change, and meanwhile, the fixed wing aircraft can vertically take off under the full-load state, and the maximum use efficiency of the fixed wing aircraft can be realized.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to an aircraft capable of carrying a fixed-wing aircraft to take off and land vertically, a carrying method, a vertical takeoff method and a vertical landing method.
Background
In order to enable the fixed-wing aircraft not to be limited by a runway, the vertical take-off and landing of the fixed-wing aircraft are always technical problems to be solved, the helicopter can realize the vertical take-off, but the helicopter has the defects of limited flying speed, incapability of flying quickly, limited carrying capacity and the like; the fixed-wing aircraft with the vertical take-off and landing function has the advantages that the oil carrying capacity is reduced due to the fact that the power assembly is added, the carrying capacity is reduced, and meanwhile, the oil consumption of the fixed-wing aircraft with the vertical take-off and landing function is too high in the process of realizing vertical take-off, so that the fixed-wing aircraft is not favorable for long-distance flight.
Disclosure of Invention
In view of the above, it is necessary to provide an aircraft capable of carrying a fixed-wing aircraft for vertical takeoff and landing, a carrying method, a vertical takeoff method and a vertical landing method.
An aircraft capable of carrying a fixed-wing aircraft to take off and land vertically comprises a lift engine, a thrust power unit, a butt joint locking system, an aircraft body and wings;
the lift force engines are arranged on two opposite sides of the body and are used for providing vertical lift force;
the thrust power unit is a thrust vector engine or a thrust engine, the thrust power unit is arranged at the tail part of the engine body, and the thrust power unit is used for providing horizontal thrust;
the butt joint locking system is arranged at the back of the airplane body and is used for being connected with the fixed-wing airplane;
the wings are arranged on two opposite sides of the body and are used for providing lift force.
In one embodiment, the lift engine is a rocket engine, a turbojet engine, a turbofan engine, a fan engine, a ducted engine, or a rotorcraft.
In one embodiment, the thrust power unit is further configured to provide vertical lift according to a vector angle.
In one embodiment, the butt-lock system is coupled to a landing gear of the fixed-wing aircraft at the back of the aircraft.
In one embodiment, the angle Ω between the mounting axis of the lift engine and the vertical axis of the body of the aircraft is within the range 0-20 °.
A method of an aircraft for piggybacking a fixed-wing aircraft, comprising the steps of: and connecting the fixed-wing aircraft with a butt-joint locking system at the back of the aircraft, wherein an included angle alpha between the horizontal axis of the aircraft and the horizontal axis under the ground coordinate system is controlled within +/-15 degrees, an included angle beta between the horizontal axis of the fixed-wing aircraft and the horizontal axis under the ground coordinate system is controlled within +/-25 degrees, and an included angle gamma between the horizontal axis of the aircraft and the horizontal axis of the fixed-wing aircraft is controlled within 0-40 degrees.
In one embodiment, after the fixed-wing aircraft is connected with the butt-lock system at the back of the aircraft, the distance H between the point of the center of gravity of the aircraft, which is connected with the upper back of the aircraft, and the point of the center of gravity of the fixed-wing aircraft, which is lower belly of the aircraft, is within 0.1-1.4 meters.
The method for the vertical takeoff of the aircraft carrying the fixed-wing aircraft comprises the following steps:
connecting the fixed-wing aircraft with a butt-lock system at the back of the aircraft;
the lift engine provides vertical lift to realize vertical takeoff of the aircraft carrying the fixed-wing aircraft;
the thrust power unit provides horizontal thrust to enable the aircraft and the fixed-wing aircraft to horizontally accelerate to a preset speed, and the butt joint locking system is opened;
the aircraft is separated from the fixed-wing aircraft, and vertical takeoff of the fixed-wing aircraft is realized.
In one embodiment, during vertical takeoff, the included angle alpha between the horizontal axis of the aircraft and the horizontal axis under the ground coordinate system is controlled within +/-15 degrees, the included angle beta between the horizontal axis of the fixed-wing aircraft and the horizontal axis under the ground coordinate system is controlled within +/-25 degrees, and the included angle gamma between the horizontal axis of the aircraft and the horizontal axis of the fixed-wing aircraft is controlled within 0-40 degrees.
The method for the vertical landing of the aircraft carrying the fixed-wing aircraft comprises the following steps:
before vertical landing, the fixed-wing aircraft and the aircraft are kept relatively static at a preset speed;
adopting the butt-joint locking system to butt-joint and lock the fixed-wing aircraft and the aircraft;
the fixed-wing aircraft and the aircraft decelerate together and then hover and vertically land in a designated area.
In one embodiment, during vertical landing, the included angle α between the horizontal axis of the aircraft and the horizontal axis of the ground coordinate system is controlled within ± 15 °, the included angle β between the horizontal axis of the fixed-wing aircraft and the horizontal axis of the ground coordinate system is controlled within ± 25 °, and the included angle γ between the horizontal axis of the aircraft and the horizontal axis of the fixed-wing aircraft is controlled within 0-40 °.
The aircraft has the vertical takeoff function under the full-load state of the piggyback fixed wing aircraft, so that the traditional fixed wing aircraft has the functions of vertical takeoff and landing without large-scale change, and meanwhile, the fixed wing aircraft can vertically take off under the full-load state, and the maximum use efficiency of the fixed wing aircraft can be realized.
Drawings
FIG. 1 is a schematic structural diagram of an aircraft according to one embodiment;
FIG. 2 is a schematic view of an aircraft lift engine mounting axis angle;
FIG. 3 is a view of the separation and docking attitude angles of the aircraft and the fixed-wing aircraft;
FIG. 4 is a flowchart of a method for a fixed wing aircraft to carry an aircraft for vertical takeoff;
fig. 5 is a flow chart of a method for the vertical landing of an aircraft carrying a fixed-wing aircraft.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be understood that the relation indicating the orientation or position such as "above" is based on the orientation or position relation shown in the drawings, or the orientation or position relation which the product of the present invention is usually put into use, or the orientation or position relation which is usually understood by those skilled in the art, and is only for convenience of describing the present invention and simplifying the description, but does not indicate or imply that the device or element to be referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, cannot be construed as limiting the present invention.
The following detailed description of embodiments of the invention refers to the accompanying drawings.
As shown in fig. 1, an embodiment of the aircraft capable of piggybacking a fixed-wing aircraft for vertical take-off and landing includes a lift engine 12, a thrust power unit 13, a butt-lock system 15, a body 14, and wings 11.
The thrust power unit 13 is a thrust vector engine or a thrust engine, the thrust power unit 13 is arranged at the tail of the machine body, and the thrust power unit 13 is used for providing horizontal thrust.
The butt-joint locking system is arranged at the back of the airframe 14 and is used for being connected with a fixed-wing aircraft.
Wings 11 are provided on opposite sides of the body 14 for providing lift.
In one embodiment, lift engine 12 is a rocket engine, a turbojet engine, a turbofan engine, a fan engine, a ducted engine, or a rotorcraft.
In one embodiment, thrust power unit 13 is also used to provide vertical lift according to vector angle. That is, in one embodiment, thrust power unit 13 is also configured to provide vertical lift and horizontal thrust according to vector angles.
In one embodiment, the butt lock system 15 is connected to the landing gear of a fixed wing aircraft at the back of the aircraft.
Referring to fig. 2, the lift engine 21 has a lift engine intake 24 and a lift engine exhaust 25. In one embodiment, the mounting axis 22 of the lift engine 21 is at an angle Ω in the range of 0-20 ° to the vertical axis 23 of the body of the aircraft. The aerodynamic influence is prevented, and the vertical take-off of the fixed-wing aircraft carried by the aircraft can not be realized.
Referring to fig. 1, the aircraft described above realizes vertical takeoff of the piggyback fixed-wing aircraft by the vertical lift provided by the lift engine 12, the thrust power unit 13 provides horizontal thrust to make the aircraft and the fixed-wing aircraft horizontally accelerate to a certain speed and then the docking locking system 15 is opened, the aircraft is separated from the fixed-wing aircraft, and vertical takeoff of the fixed-wing aircraft is realized. Before the fixed-wing aircraft vertically lands, the fixed-wing aircraft is firstly in a state of keeping relative rest with the aircraft at a certain speed, is in butt joint locking with the fixed-wing aircraft by using a butt joint locking system 15 of the aircraft, and hovers after being decelerated together to vertically land in a designated area.
The aircraft has the vertical takeoff function under the full-load state of the piggyback fixed wing aircraft, so that the traditional fixed wing aircraft has the functions of vertical takeoff and landing without large-scale change, and meanwhile, the fixed wing aircraft can vertically take off under the full-load state, and the maximum use efficiency of the fixed wing aircraft can be realized.
Referring to fig. 3, the present application further provides a method for a fixed-wing aircraft carried by an aircraft, including the following steps: the fixed-wing aircraft 32 is connected with the butt-lock system of the back of the aircraft 31, wherein the included angle alpha between the horizontal axis 39 of the aircraft and the horizontal axis 37 under the ground coordinate system is controlled within +/-15 degrees, the included angle beta between the horizontal axis 38 of the fixed-wing aircraft and the horizontal axis 37 under the ground coordinate system is controlled within +/-25 degrees, and the included angle gamma between the horizontal axis 39 of the aircraft and the horizontal axis 38 of the fixed-wing aircraft is controlled within 0-40 degrees. The aircraft and the fixed wing aircraft can be separated without collision when reaching a certain speed. The collision-free butt joint of the aircraft and the fixed-wing aircraft can be realized when the aircraft and the fixed-wing aircraft reach a certain speed.
Further, referring to fig. 3, after the fixed-wing aircraft 32 is connected to the docking and locking system at the back of the aircraft 31, the distance H between the point at the center of gravity of the aircraft 31 connected to the upper aircraft back and the point at the lower aircraft belly of the center of gravity of the fixed-wing aircraft 32 is within 0.1-1.4 m. The locking mechanism and the double-machine pneumatic influence cannot cause collision when the aircraft 31 is separated from the fixed-wing aircraft 32.
Referring to fig. 4, the present application further provides a method for the aircraft to carry a fixed-wing aircraft for vertical takeoff, which includes the following steps:
and S12, connecting the fixed-wing aircraft with a butt locking system at the back of the aircraft.
S14, the lift engine provides vertical lift to realize vertical take-off of the aircraft carrying the fixed-wing aircraft.
And S16, providing horizontal thrust by the thrust power unit to enable the aircraft and the fixed-wing aircraft to horizontally accelerate to a preset speed, and opening the butt joint locking system.
And S18, separating the aircraft from the fixed-wing aircraft, and realizing vertical takeoff of the fixed-wing aircraft.
Further, during vertical takeoff, an included angle alpha between the horizontal axis of the aircraft and the horizontal axis under the ground coordinate system is controlled within +/-15 degrees, an included angle beta between the horizontal axis of the fixed-wing aircraft and the horizontal axis under the ground coordinate system is controlled within +/-25 degrees, and an included angle gamma between the horizontal axis of the aircraft and the horizontal axis of the fixed-wing aircraft is controlled within 0-40 degrees. The aircraft and the fixed wing aircraft can be separated without collision when reaching a certain speed.
Referring to fig. 5, the present application further provides a method for the aircraft to carry a fixed-wing aircraft for vertical landing, which includes the following steps:
and S22, before vertical landing, the fixed-wing aircraft and the aircraft keep relatively static at a preset speed.
And S24, adopting a butt-joint locking system to butt-joint and lock the fixed-wing aircraft and the aircraft.
And S26, the fixed-wing aircraft and the aircraft decelerate together, hover and vertically land in the designated area.
Further, during vertical landing, the included angle alpha between the horizontal axis of the aircraft and the horizontal axis under the ground coordinate system is controlled within +/-15 degrees, the included angle beta between the horizontal axis of the fixed-wing aircraft and the horizontal axis under the ground coordinate system is controlled within +/-25 degrees, and the included angle gamma between the horizontal axis of the aircraft and the horizontal axis of the fixed-wing aircraft is controlled within 0-40 degrees. The collision-free butt joint of the aircraft and the fixed-wing aircraft can be realized when the aircraft and the fixed-wing aircraft reach a certain speed.
The aircraft carries the fixed-wing aircraft, can realize vertical take-off of carrying, horizontal acceleration separation fly-off, butt joint locking with the air, horizontal deceleration and vertical landing of carrying.
According to the method for the vertical takeoff of the aircraft carrying the fixed wing aircraft, the aircraft has the vertical takeoff function under the full-load state of the carrying fixed wing aircraft, so that the traditional fixed wing aircraft has the vertical takeoff function without large-scale change, and meanwhile, the fixed wing aircraft can vertically takeoff under the full-load condition, and the maximum use efficiency of the fixed wing aircraft can be realized.
According to the method for the aircraft to carry the fixed-wing aircraft to vertically land, the aircraft has the function of carrying the fixed-wing aircraft to vertically land, so that the traditional fixed-wing aircraft has the function of vertically land without large-scale change.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, various modifications and decorations can be made without departing from the principle of the present invention, and these modifications and decorations should also be regarded as the protection scope of the present invention.
Claims (11)
1. An aircraft capable of carrying a fixed-wing aircraft to take off and land vertically is characterized by comprising a lift force engine, a thrust power unit, a butt joint locking system, an aircraft body and wings;
the lift force engines are arranged on two opposite sides of the body and are used for providing vertical lift force;
the thrust power unit is a thrust vector engine or a thrust engine, the thrust power unit is arranged at the tail part of the engine body, and the thrust power unit is used for providing horizontal thrust;
the butt joint locking system is arranged at the back of the airplane body and is used for being connected with the fixed-wing airplane;
the wings are arranged on two opposite sides of the body and are used for providing lift force.
2. The aircraft capable of piggybacking a fixed-wing aircraft for vertical take-off and landing of claim 1, wherein said lift engine is a rocket engine, a turbojet engine, a turbofan engine, a fan engine, a ducted engine, or a rotorcraft.
3. The aircraft capable of piggybacking a fixed-wing aircraft for vertical take-off and landing of claim 1, wherein said thrust power unit is further adapted to provide vertical lift according to vector angle.
4. The aircraft capable of vertical takeoff and landing a fixed-wing aircraft according to claim 1, wherein said butt-lock system is connected to the landing gear of said fixed-wing aircraft at the back of said aircraft.
5. The aircraft capable of piggybacking a fixed-wing aircraft for vertical take-off and landing of claim 1, wherein the angle Ω between the axis of installation of said lift engine and the vertical axis of said body of said aircraft is within the range of 0-20 °.
6. A method for an aircraft to carry a fixed-wing aircraft, comprising the steps of: and connecting the fixed-wing aircraft with a butt-joint locking system at the back of the aircraft, wherein an included angle alpha between the horizontal axis of the aircraft and the horizontal axis under the ground coordinate system is controlled within +/-15 degrees, an included angle beta between the horizontal axis of the fixed-wing aircraft and the horizontal axis under the ground coordinate system is controlled within +/-25 degrees, and an included angle gamma between the horizontal axis of the aircraft and the horizontal axis of the fixed-wing aircraft is controlled within 0-40 degrees.
7. The method of claim 6 wherein after said fixed-wing aircraft is connected to said docking and deadlocking system on the back of the aircraft, the separation H between the point of the center of gravity of the aircraft that connects the upper back of the aircraft to the point of the belly below the center of gravity of the fixed-wing aircraft is within 0.1-1.4 meters.
8. A method for the vertical take-off of an aircraft carrying a fixed wing aircraft according to any one of claims 1 to 5, comprising the steps of:
connecting the fixed-wing aircraft with a butt-lock system at the back of the aircraft;
the lift engine provides vertical lift to realize vertical takeoff of the aircraft carrying the fixed-wing aircraft;
the thrust power unit provides horizontal thrust to enable the aircraft and the fixed-wing aircraft to horizontally accelerate to a preset speed, and the butt joint locking system is opened;
the aircraft is separated from the fixed-wing aircraft, and vertical takeoff of the fixed-wing aircraft is realized.
9. The method for vertical takeoff of an aircraft carrying a fixed-wing aircraft as claimed in claim 8, wherein during vertical takeoff, the included angle α between the horizontal axis of the aircraft and the horizontal axis under the ground coordinate system is controlled within ± 15 °, the included angle β between the horizontal axis of the fixed-wing aircraft and the horizontal axis under the ground coordinate system is controlled within ± 25 °, and the included angle γ between the horizontal axis of the aircraft and the horizontal axis of the fixed-wing aircraft is controlled within 0-40 °.
10. A method of landing a fixed-wing aircraft vertically carried by an aircraft according to any of claims 1 to 5, comprising the steps of:
before vertical landing, the fixed-wing aircraft and the aircraft are kept relatively static at a preset speed;
adopting the butt-joint locking system to butt-joint and lock the fixed-wing aircraft and the aircraft;
the fixed-wing aircraft and the aircraft decelerate together and then hover and vertically land in a designated area.
11. The method for vertical landing of an aircraft carrying a fixed-wing aircraft according to claim 10, wherein during vertical landing, the included angle α between the horizontal axis of the aircraft and the horizontal axis of the ground coordinate system is controlled within ± 15 °, the included angle β between the horizontal axis of the fixed-wing aircraft and the horizontal axis of the ground coordinate system is controlled within ± 25 °, and the included angle γ between the horizontal axis of the aircraft and the horizontal axis of the fixed-wing aircraft is controlled within 0-40 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911383896.5A CN113044217A (en) | 2019-12-28 | 2019-12-28 | Aircraft capable of carrying fixed-wing aircraft to take off and land vertically, carrying method, vertical takeoff method and vertical landing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911383896.5A CN113044217A (en) | 2019-12-28 | 2019-12-28 | Aircraft capable of carrying fixed-wing aircraft to take off and land vertically, carrying method, vertical takeoff method and vertical landing method |
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| Publication Number | Publication Date |
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| CN113044217A true CN113044217A (en) | 2021-06-29 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201911383896.5A Pending CN113044217A (en) | 2019-12-28 | 2019-12-28 | Aircraft capable of carrying fixed-wing aircraft to take off and land vertically, carrying method, vertical takeoff method and vertical landing method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114194387A (en) * | 2022-01-05 | 2022-03-18 | 骈学超 | Coaxial reverse-propeller double-rotor type air moving runway |
-
2019
- 2019-12-28 CN CN201911383896.5A patent/CN113044217A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114194387A (en) * | 2022-01-05 | 2022-03-18 | 骈学超 | Coaxial reverse-propeller double-rotor type air moving runway |
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