CN117734935A - Short-distance helicopter - Google Patents
Short-distance helicopter Download PDFInfo
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- CN117734935A CN117734935A CN202311771689.3A CN202311771689A CN117734935A CN 117734935 A CN117734935 A CN 117734935A CN 202311771689 A CN202311771689 A CN 202311771689A CN 117734935 A CN117734935 A CN 117734935A
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- helicopter
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- fuselage
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- 239000000446 fuel Substances 0.000 claims abstract description 10
- 239000000463 material Substances 0.000 claims abstract description 10
- 239000003381 stabilizer Substances 0.000 claims description 13
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- 239000010959 steel Substances 0.000 claims description 3
- 239000011825 aerospace material Substances 0.000 claims 1
- 230000002787 reinforcement Effects 0.000 claims 1
- 230000006641 stabilisation Effects 0.000 claims 1
- 238000011105 stabilization Methods 0.000 claims 1
- 230000007246 mechanism Effects 0.000 abstract description 3
- 230000003628 erosive effect Effects 0.000 description 5
- 230000009471 action Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 230000003014 reinforcing effect Effects 0.000 description 2
- 230000000087 stabilizing effect Effects 0.000 description 2
- 241000272475 Haliaeetus Species 0.000 description 1
- 241000566150 Pandion haliaetus Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
Abstract
The invention discloses a short-distance helicopter, which belongs to the field of aircrafts and comprises a fuselage, wings, a propeller and a landing gear. The invention is mainly characterized in that the first frame is an aircraft which utilizes the horizontal thrust of a propeller to provide upward lift force for the aircraft by matching with a large-area aileron and a flap so as to realize vertical take-off and landing of the aircraft. A breakthrough of zero stall speed is achieved. In addition, in the aspect of the selection of the aviation materials, the invention adopts light civil aviation materials, and the invention also has a rapid wing dismounting mechanism, thereby being convenient for dismounting, assembling and transporting; in addition, when the engine fails, the engine has the capability of autonomous spiral landing, and finally, the piston engine is adopted on the selection of the engine, so that the common gas station can be filled with fuel, and civil fuel and gasoline are used on the fuel.
Description
Technical Field
The invention relates to the field of aircrafts, in particular to a short-distance helicopter.
Background
The short-distance helicopter is a fixed-wing aircraft with short-distance take-off, and can take-off in a short distance without depending on a runway, by virtue of the fact that when the aircraft moves at a low speed, when a front propeller rotates at a high speed, air flow can flow to the rear of the aircraft body at a higher speed under the action of the propeller, and the air flow can flow through a pneumatic surface (mainly an aileron and a flap), so that the capability of the pneumatic surface for operating the aircraft when the aircraft moves at the low speed is provided;
many airplanes capable of realizing short-distance vertical take-off and landing at present, such as F-35 developed in the United states, are used for realizing vertical take-off by using a vector engine, and another implementation mode is similar to U.S. osprey fighter V-22, and a tilting rotor wing mode is adopted for realizing short-distance or vertical take-off and landing;
however, the high-temperature jet flow at the tail of the vector engine can generate high-temperature erosion action on the runway and the airframe; control of tiltrotors such as V-22 is difficult. Compared with a tilting rotor type and a vector engine, the aircraft designed by the patent is greatly superior to the tilting rotor type and the vector engine in terms of control difficulty and technical complexity.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides the short-distance vertical lift aircraft, the short-distance vertical lift flight is effectively realized by using a simple and traditional structure, when a rotor at a nose rotates at a high speed, air flows can flow to the rear of a collective body at a higher speed under the action of a propeller, the air flows can act on the aerodynamic surface of the aircraft, (mainly an aileron and a flap), and the capability of the aerodynamic surface for controlling the aircraft when the aircraft moves at a low speed is also provided for providing the short-distance vertical lift take-off for the aircraft. The fixed wing aircraft can ascend and descend vertically.
The invention is realized by the following technical scheme: a short-distance helicopter comprises a fuselage, a wing system, a fixed rotor wing and a landing gear;
the wing system comprises a main wing, an aileron and a flap; the main wing is positioned above the aircraft body, the ailerons and the flaps with larger areas are respectively positioned at the outer side and the inner side of the wing, and the specific area size is designed according to the size and the weight of the aircraft;
the fixed rotor wing is fixed at the machine head, accelerates airflow to flow backwards when rotating, is matched with the aileron and the flap, changes horizontal thrust into vertical upward lift force, and realizes quick short-distance vertical take-off when the ground speed is zero;
the landing gear is positioned at the bottom of the machine body and symmetrically distributed at two sides of the longitudinal axis of the machine body.
Further, the aircraft has large-area ailerons and flaps, when the aircraft takes off, the propellers rotate at a high speed as a power device to provide forward thrust for the aircraft taking off, the ailerons and the flaps of the aircraft are pressed down, and strong air flow driven by the high-speed rotation of the propellers acts on the aerodynamic surface to provide upward lift force for the aircraft in cooperation with the aerodynamic surface.
Further, the stationary rotor direction is along the fuselage axis, which provides upward lift for aircraft take-off, helping to achieve short-range lift power.
Further, the landing gear is provided with three wheels in total, two landing gear wheels symmetrically distributed along the longitudinal axis of the aircraft body are arranged at the front part of the bottom of the aircraft body, and one landing gear wheel along the longitudinal axis is arranged at the rear part of the bottom of the aircraft body.
Further, the wing system further comprises a vertical tail and a horizontal tail, the horizontal tail further comprises an elevator and a horizontal stabilizer, and the vertical tail comprises a vertical stabilizer and a rudder.
Further, the elevator, the rudder and the stabilizer are rotatably connected, and the steering engine arranged at the tail part of the machine body is used as an actuating mechanism to deflect at a certain angle.
Further, a plurality of support rods are arranged between the main wing and the fuselage to play a role in reinforcing and stabilizing the wing.
Further, the aircraft is provided with a flexible rearward hatch and an optional forward cabin cargo inlet.
Further, airplanes use lightweight civil aviation materials, including knitted materials and steel materials.
Further, the aircraft adopts a piston engine, and civil fuel oil and gasoline are used as fuel for the aircraft for filling.
The invention has the beneficial effects that:
at present, a vertical take-off and landing aircraft represented by an F-35 fighter realizes vertical take-off and landing by using a vector thrust jet engine, but the erosion of high-temperature hot waves to an aircraft runway and a deck is very serious, a V-22 fish-eagle fighter utilizes a tiltable rotor wing to realize the current vertical take-off and landing, but the operation difficulty is high, accidents are extremely easy to occur in the tilting process of the rotor wing, and the aircraft skillfully changes the horizontal thrust of a fixed rotor wing into the vertical upward lift force, does not have the erosion effect of the high-temperature hot waves to running, and also avoids the complex tilting rotor wing.
The invention relates to an aircraft, which utilizes the horizontal thrust of a propeller to provide upward lift force for an aircraft by matching with a large-area aileron and a flap so as to realize short-distance vertical lifting. Short take-off landing is achieved by appropriate proportions of pneumatic design and propulsion to the control surface. Breakthrough of stall speed zero is also achieved. The outdoor field short-distance lifting and lifting take-off with the radius of 10m can be realized. Compared with a tilting rotor type and a vector engine, the aircraft designed by the invention is greatly superior to the prior art in control difficulty and technical complexity.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a peripheral side view of the present invention.
Fig. 2 is a front view of the present invention.
Fig. 3 is a top view of the present invention.
In the figure: 1. a body; 2. a wing; 3. aileron; 4. a flap; 5. a horizontal stabilizer; 6. an elevator; 7. a vertical stabilizer; 8. a rudder; 9. a propeller; 10. landing gear; 11. and (5) supporting frames.
Detailed Description
In order to more clearly illustrate the present invention, the present invention will be further described with reference to preferred embodiments and the accompanying drawings. Like parts in the drawings are denoted by the same reference numerals. It is to be understood by persons skilled in the art that the following detailed description is illustrative and not restrictive, and that this invention is not limited to the details given herein.
As shown in fig. 1-3, a short-range helicopter includes a fuselage 1, a wing system, a stationary rotor, and landing gear. The wing system comprises a main wing 2, an aileron 3, a flap 4 and an H-shaped tail wing. The flap 4 is arranged on the inner side of the main wing, the aileron 3 is arranged on the outer side of the main wing, and the main wing 2 can rotate around the vertical shaft of the airplane, so that the rapid wing folding can be realized, and the cargo storage and transportation are convenient. A plurality of support rods are arranged between the wing and the fuselage to play a role in reinforcing and stabilizing the wing. The H-shaped tail fin of the aircraft is positioned at the tail part of the fuselage and consists of a horizontal tail fin and a vertical tail fin, wherein the horizontal tail fin comprises a horizontal stabilizer 5 and an elevator 6, the elevator is connected with the horizontal stabilizer, and the elevator can rotate around the axis of the horizontal stabilizer. The vertical tail includes a vertical stabilizer and a rudder rotatable about an axis of the vertical stabilizer. The elevator and the rudder are deflected by a certain angle by taking a steering engine arranged at the tail part of the machine body as an actuating mechanism. As an improvement, the tail fin can be of a T shape, a V shape, an inverted V shape or an inverted T shape.
The power device is a propeller positioned at the head of the aircraft, and not only can provide forward thrust for the take-off of the aircraft, but also can be matched with a pneumatic surface to provide upward lifting force for the aircraft.
The fixed rotor is a power device of the aircraft, the direction of the fixed rotor is along the axis of the aircraft body, the fixed rotor provides upward lift force for the take-off of the aircraft, and the fixed rotor is helpful for realizing short-distance vertical lifting power. The landing gear of the airplane is positioned at the bottom of the airplane body and symmetrically distributed at two sides of the longitudinal axis of the airplane body; the landing gear has three wheels, two landing gear wheels symmetrically distributed along the longitudinal axis of the aircraft body are arranged at the front part of the bottom of the aircraft body, and one landing gear wheel along the longitudinal axis is arranged at the rear part of the bottom of the aircraft body.
As shown in fig. 1-3, during take-off, the high-speed airflow discharged to the rear of the aircraft body when the fixed rotor (propeller) at the aircraft nose rotates at a high speed accelerates the airflow to flow backwards, and is matched with the ailerons and the flaps, the aerodynamic surfaces (the ailerons 3 and the flaps 4) have the capability of changing the horizontal thrust into the vertical upward lift force under the low-speed take-off state of the aircraft, and provide larger lift force for the aircraft, so that in order to strengthen the capability, the area of the ailerons and the flaps of the aircraft can be designed to be larger (more than 8% of the traditional aileron flaps) according to the size and the weight of the aircraft, so that larger control authority and lift force size are provided, and the aircraft can realize quick short-distance vertical take-off when the ground speed is zero, has the characteristic of lifting and straight lifting, and can realize the landing of an apron with a radius of 10 m.
The vertical take-off and landing mode of the aircraft is different from other types of vertical take-off and landing modes, the vertical take-off and landing aircraft represented by an F-35 fighter at present realizes vertical take-off and landing by using a vector thrust jet engine, but the erosion of high-temperature hot waves to an aircraft runway and a deck can be very serious, the V-22 hawk fighter utilizes a tiltable rotor wing to realize the vertical take-off and landing at present, but the operation difficulty is high, accidents are easy to occur in the tilting process of the rotor wing, the aircraft skillfully changes the horizontal thrust of a fixed rotor wing into the vertical upward lift force, the erosion effect of the high-temperature hot waves to running is not existed, and the complex tilting rotor wing is avoided. The invention realizes the breakthrough of stall speed of 0 of the airplane, and no airplane can realize stall speed of 0.
The main wing 2 is located above the fuselage and the ailerons 3 and flaps 4 and located outside and inside the main wing 2, respectively, are intended to have a larger area than conventional ailerons and flaps in order for the aircraft to have a vertical lift characteristic.
As shown in fig. 1-3, when the aircraft takes off, the aircraft adjusts the positions of the ailerons and the flaps to the lower side, which brings great lift to the aircraft taking off, and wheels behind the landing gear of the aircraft leave the ground at first during the taking off process.
When the aircraft is landing, the ailerons and flaps are opened to a lower position, the wheels behind the landing gear contact the ground first, and the front wheels contact the ground later.
The aircraft is provided with a flexible rearward hatch and an optional forward cabin cargo inlet; this allows the aircraft to be able to perform cargo transportation tasks.
The aircraft uses light civil aviation materials, including knitted materials and common steel materials.
The aircraft adopts the piston engine, the engine is allowed to be exceeded in a short time under the control of the excessive engine, and the common gas station can be filled with fuel, and civil fuel and gasoline can be used as the fuel of the aircraft because the military aviation fuel is not easy to obtain.
The above-described embodiments are intended to illustrate the present invention, not to limit it, and any modifications and variations made thereto are within the spirit of the invention and the scope of the appended claims.
Claims (10)
1. A short-distance helicopter is characterized by comprising a fuselage, a wing system, a fixed rotor wing and a landing gear;
the wing system comprises a main wing, an aileron and a flap; the main wing is positioned above the aircraft body, the ailerons and the flaps with larger areas are respectively positioned at the outer side and the inner side of the wing, and the specific area size is designed according to the size and the weight of the aircraft;
the fixed rotor wing is fixed at the machine head, accelerates airflow to flow backwards when rotating, is matched with the aileron and the flap, changes horizontal thrust into vertical upward lift force, and realizes quick short-distance vertical take-off when the ground speed is zero;
the landing gear is positioned at the bottom of the machine body and symmetrically distributed at two sides of the longitudinal axis of the machine body.
2. The short-range helicopter according to claim 1, wherein the helicopter has large-area ailerons and flaps, the propeller rotates at a high speed as a power device during the take-off of the helicopter, forward thrust is provided for the take-off of the helicopter, the ailerons and flaps of the helicopter are pressed down, and strong airflow driven by the high-speed rotation of the propeller acts on a pneumatic surface, and the pneumatic surface is matched with the ailerons and flaps to provide upward lift for the helicopter.
3. The short-range helicopter according to claim 1 wherein said stationary rotor direction is along a fuselage axis which provides upward lift for aircraft takeoff and assists in achieving short-range helicopter power.
4. A short lift helicopter according to claim 1 wherein the landing gear has three wheels in total, two landing gear wheels symmetrically disposed along the longitudinal axis of the fuselage in front of the bottom of the fuselage and one landing gear wheel along the longitudinal axis behind the bottom of the fuselage.
5. The short-range helicopter according to claim 1 wherein said wing system further comprises a vertical tail and a horizontal tail, said horizontal tail further comprising an elevator and a horizontal stabilizer, said vertical tail comprising a vertical stabilizer and a rudder.
6. The short-range helicopter according to claim 1, wherein the rotational connection between the elevators and the rudder and the stabilizer is an angular deflection by means of a steering engine mounted on the tail of the fuselage as an actuator.
7. The short-range helicopter according to claim 1, wherein a plurality of support rods are provided between the main wing and the fuselage to provide reinforcement and stabilization of the wing.
8. The short-range helicopter according to claim 1, characterized in that the aircraft is provided with a flexible backward hatch and an optional forward cabin cargo inlet.
9. The short-range helicopter according to claim 1, wherein the aircraft uses lightweight civilian aerospace materials, including knitted materials and steel materials.
10. The short-range helicopter according to claim 1, wherein the aircraft is filled with piston engines, both civil fuel and gasoline as fuel for the aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311771689.3A CN117734935A (en) | 2023-12-21 | 2023-12-21 | Short-distance helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311771689.3A CN117734935A (en) | 2023-12-21 | 2023-12-21 | Short-distance helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117734935A true CN117734935A (en) | 2024-03-22 |
Family
ID=90258990
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311771689.3A Pending CN117734935A (en) | 2023-12-21 | 2023-12-21 | Short-distance helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117734935A (en) |
-
2023
- 2023-12-21 CN CN202311771689.3A patent/CN117734935A/en active Pending
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