CN111392030A

CN111392030A - Retractable angle-adjustable helicopter short wing

Info

Publication number: CN111392030A
Application number: CN202010353455.7A
Authority: CN
Inventors: 李军
Original assignee: Mianyang Fu Lin Lan Technology Co ltd
Current assignee: Mianyang Fu Lin Lan Technology Co ltd
Priority date: 2020-04-29
Filing date: 2020-04-29
Publication date: 2020-07-10

Abstract

The invention discloses a retractable angle-adjustable helicopter short wing which comprises a fuselage, an empennage and a short wing, wherein an undercarriage is arranged below the fuselage, a main rotor wing is arranged at the top of the fuselage, the empennage is arranged at the tail end of the fuselage, the short wing is arranged on the outer side of the middle of the fuselage, a containing cavity positioned in the fuselage is arranged on the outer side of the short wing, a hinge is arranged at the tail end of the short wing, a driver is arranged in the containing cavity, and a central control box is arranged on the outer side of the driver. This but receive and release angle regulation formula helicopter stub has solved the drawback that telescopic helicopter stub can not expand in high-speed motion, has solved the fixed drawback that can not adjust of telescopic helicopter stub and fuselage contained angle, when flying before the helicopter high speed, when hovering maneuver flight, under hover, VTOL and low-speed flight state, when the rotation gliding, the homoenergetic is adjusted to the stub, can the at utmost use of carrying out power.

Description

Retractable angle-adjustable helicopter short wing

Technical Field

The invention relates to the field of overall design of helicopters, which is used for improving the flight speed of the helicopters or reducing the required power of the helicopters during forward flight, in particular to a retractable angle-adjustable helicopter short wing.

Background

Helicopters have features not found in fixed wing aircraft, such as: high-efficiency hovering, low-speed forward flight and the like, and has wide practical application in the military and civil fields. However, with the progress of science and technology and the rapid development of times, the demands for improving the flight speed of the helicopter, or reducing the power demand of the helicopter during forward flight and reducing the oil consumption rate of the helicopter are more and more urgent.

Gunships generally use short wing elements to suspend weapons from the aircraft, and generate lift during forward flight to unload the rotor. Especially during maneuvering, can increase the maximum flight overload of the helicopter. When the short wing is arranged on the fuselage, the longitudinal position of the aerodynamic center of the short wing should be located behind the center of gravity of the whole aircraft as much as possible, so that the short wing plays a role of a stabilizing surface to increase the longitudinal static stability of the whole aircraft.

In order to realize the conversion from the high-efficiency hovering state to the high-speed forward flying state and achieve the effect of unloading a main rotor of the helicopter in the high-speed forward flying state, a certain effect is achieved by adopting a fixed short wing mode for part of helicopters, but because the fixed short wing mode is adopted, the jamming influence is generated on the rotor induced wash-down flow in low-speed forward flying, vertical take-off and landing and air hovering flying, the required power of the fixed short wing helicopter in low-speed forward flying, vertical take-off and landing and air hovering flying is increased, and the technical application is more beneficial.

With the development of science and technology, retractable short wings of helicopters also appear, the flight speed of the helicopters is improved to a certain extent, the required power of the helicopters during forward flight is reduced, but the required power is higher, and the short wings can only be retracted in a low-speed state; the included angles between the fixed helicopter short wing and the telescopic helicopter short wing and the fuselage are fixed, and the lifting force requirement under the flying environment cannot be widely met.

Therefore, we propose a retractable adjustable angle helicopter winglet, in order to solve the problems set forth above.

Disclosure of Invention

In order to improve the flying efficiency of the helicopter when flying forward, the invention provides a retractable angle-adjustable helicopter short wing scheme aiming at the short wing part of the helicopter, solves the defect that the retractable helicopter short wing cannot be unfolded in high-speed motion, and solves the defect that the included angle between the retractable helicopter short wing and the helicopter body is fixed and cannot be adjusted.

In order to achieve the purpose, the invention provides the following technical scheme: the utility model provides a can receive and release adjustable angle formula helicopter stub, includes fuselage, fin and stub, the undercarriage is installed to the below of fuselage, and the top of fuselage installs main rotor, the end of fuselage is provided with the fin, and the middle part outside of fuselage is provided with the stub, the outside of stub is provided with the chamber of accomodating that is located the inside of fuselage, and the end of stub installs the hinge, the internally mounted who accomodates the chamber has the driver, and the outside of driver is provided with well accuse box.

Preferably, the short wings are provided with 2 groups, and the short wings are respectively positioned on two sides of the fuselage.

Preferably, the short wing longitudinal position is located behind and below the main rotor.

Preferably, the short wing is arranged at the position behind the center of gravity of the fuselage in a manner of rotating connection through a hinge.

Preferably, one end of the short wing, which is far away from the fuselage, is convexly arranged on the outer side of the containing cavity.

Preferably, the containing cavities and the short wings are arranged in a one-to-one correspondence mode, and the short wings are in containing structures in the containing cavities.

Preferably, the head and the tail of the driver are respectively hinged to the tail end of the short wing and the inside of the containing cavity, and a linkage structure is formed between the driver and the containing cavity.

Compared with the prior art, the invention has the beneficial effects that: when the helicopter flies forward at a high speed, the short wing arranged behind the center of the helicopter body extends out of the helicopter body to generate a certain lift force to unload the rotor wing, so that the load of the rotor wing is reduced, the aerodynamic efficiency is improved, the stabilizing surface is played, and the longitudinal static stability of the whole helicopter is enhanced; when the aircraft is in hover and flying maneuver, the short wings are utilized to increase the lift force of the whole aircraft, reduce the load of the rotor blades and improve the maximum flying overload.

Under the states of hovering, vertical take-off and landing and low-speed flight, the short wing is retracted into the aircraft body, the downward washing flow of the rotor wing is not influenced, and the extra required power is not increased; when the helicopter glides in rotation, the short wings which are taken in the helicopter body cannot additionally and obviously increase the resistance of the helicopter body, and the gliding capability of the helicopter in rotation cannot be obviously influenced.

Drawings

FIG. 1 is a front view of the short wing of the present invention in an undeployed state;

FIG. 2 is a schematic side view of the non-deployed state of the short wing of the present invention;

FIG. 3 is a schematic view of the plane of the wing of the present invention in an undeployed state;

FIG. 4 is a schematic view of the installation plane of the wing of the present invention;

FIG. 5 is a front view of the short wing of the present invention in the unfolded state;

FIG. 6 is a schematic side view of the deployed state of the short wing according to the present invention;

FIG. 7 is a schematic view of the plane of the wing of the present invention in the extended state.

In the figure: 1. a body; 2. a landing gear; 3. a main rotor; 4. a tail wing; 5. short wings; 6. a receiving cavity; 7. a hinge; 8. a driver; 9. and (4) a central control box.

Detailed Description

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, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. 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.

Referring to fig. 1-7, the present invention provides a technical solution: the utility model provides a can receive and release adjustable angle formula helicopter stub, which comprises a fuselage 1, undercarriage 2, main rotor 3, fin 4, the stub 5, accomodate chamber 6, hinge 7, driver 8 and well accuse box 9, undercarriage 2 is installed to the below of fuselage 1, and main rotor 3 is installed at the top of fuselage 1, the end of fuselage 1 is provided with fin 4, and the middle part outside of fuselage 1 is provided with stub 5, the outside of stub 5 is provided with the chamber 6 of accomodating that is located the inside of fuselage 1, and the hinge 7 is installed to the end of stub 5, the internally mounted who accomodates chamber 6 has driver 8, and the outside of driver 8 is provided with well accuse box 9.

As shown in fig. 1, 2 and 3, the short wings 5 are provided with 2 groups, the short wings 5 are respectively positioned at two sides of the helicopter body 1, and the longitudinal position of the short wings 5 is positioned behind and below the main rotor 3, so that the helicopter can be assisted to fly.

As shown in figure 4, the short wing 5 is rotatably connected with the rear position of the center of gravity of the fuselage 1 through a hinge 7, one end of the short wing 5 far away from the fuselage 1 is convexly arranged outside the containing cavity 6, so that the short wing 5 can be extended and retracted.

As shown in fig. 1, 2, 4 and 5, the housing cavities 6 are in one-to-one correspondence with the short wings 5, and the short wings 5 are in a housing structure inside the housing cavities 6, so that the telescopic amount of the short wings 5 can be conveniently adjusted.

Like the inside of articulated connection in the terminal of short wing 5 and storage chamber 6 respectively in the head and the tail both ends of driver 8 in fig. 4, and driver 8 and storage chamber 6 between constitute linkage structure, be convenient for adjust the use.

The working principle is as follows: when the retractable angle-adjustable helicopter short wing is used, as shown in fig. 4, the short wing 5 can rotate in the containing cavity 6 through the hinge joint of the head and the tail of the driver 8 and the extension and contraction of the driver 8, so that the lift effect of the short wing 5 on the helicopter body 1 is not obvious and the strong downwash airflow generated by the main rotor 3 is blocked under the states of hovering, vertical take-off and landing and low-speed flight of the helicopter, and the overall lift effect of the helicopter can be adversely affected, therefore, in this case, the size of the short wing 5 is reduced to the minimum, the short wing 5 is retracted into the helicopter body 1, and the adverse effect of the short wing 5 on the overall performance of the helicopter is reduced;

under the condition that the helicopter flies forward at a higher speed, because the lower washing flow of the main rotor 3 inclines towards the rear side of the fuselage, the short wing 5 can extend out of the fuselage to serve as a lifting surface without impacting the short wing 5, and meanwhile, the installation angle of the short wing 5 and the expansion amount of the short wing 5 are reasonably adjusted through a series of devices such as a central control box 9, a driver 8 and the like, so that the lifting effect of the short wing can be optimally exerted, the overall load distribution of the helicopter is reduced, the main rotor of the helicopter can provide more power in the forward direction, or the load and the required power of the rotor are reduced, and the purpose of improving the overall aerodynamic performance of the helicopter is achieved.

The standard parts used in the invention can be purchased from the market, the special-shaped parts can be customized according to the description of the specification and the accompanying drawings, the specific connection mode of each part adopts conventional means such as bolts, rivets, welding and the like mature in the prior art, the machines, the parts and equipment adopt conventional models in the prior art, and the circuit connection adopts the conventional connection mode in the prior art, so that the detailed description is omitted.

Although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that various changes in the embodiments and/or modifications of the invention can be made, and equivalents and modifications of some features of the invention can be made without departing from the spirit and scope of the invention.

Claims

1. The utility model provides a can receive and release adjustable angle formula helicopter aileron, includes fuselage (1), fin (4) and aileron (5), its characterized in that: undercarriage (2) are installed to the below of fuselage (1), and main rotor (3) are installed at the top of fuselage (1), the end of fuselage (1) is provided with fin (4), and the middle part outside of fuselage (1) is provided with short wing (5), the outside of short wing (5) is provided with the chamber (6) of accomodating that is located the inside of fuselage (1), and the end of short wing (5) installs hinge (7), the internally mounted who accomodates chamber (6) has driver (8), and the outside of driver (8) is provided with well accuse box (9).

2. A retractable adjustable angle helicopter pony wing as claimed in claim 1, wherein: the short wings (5) are provided with 2 groups, and the short wings (5) are respectively positioned on two sides of the fuselage (1).

3. A retractable adjustable angle helicopter pony wing as claimed in claim 1, wherein: the longitudinal position of the short wing (5) is positioned behind and below the main rotor wing (3).

4. A retractable adjustable angle helicopter pony wing as claimed in claim 1, wherein: the short wing (5) is arranged at the position behind the gravity center of the fuselage (1) in a rotating connection mode through a hinge (7).

5. A retractable adjustable angle helicopter pony wing as claimed in claim 1, wherein: one end of the short wing (5) far away from the fuselage (1) is convexly arranged on the outer side of the containing cavity (6).

6. A retractable adjustable angle helicopter pony wing as claimed in claim 1, wherein: accomodate and be the one-to-one setting between chamber (6) and short wing (5), and short wing (5) are in the inside of accomodating chamber (6) and accomodate the structure.

7. A retractable adjustable angle helicopter pony wing as claimed in claim 1, wherein: the head and the tail of the driver (8) are respectively hinged to the tail end of the short wing (5) and the inside of the containing cavity (6), and a linkage structure is formed between the driver (8) and the containing cavity (6).