CN105015760A - Propeller-type lift-enhancing structure for symmetric wing - Google Patents
Propeller-type lift-enhancing structure for symmetric wing Download PDFInfo
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- CN105015760A CN105015760A CN201510394326.1A CN201510394326A CN105015760A CN 105015760 A CN105015760 A CN 105015760A CN 201510394326 A CN201510394326 A CN 201510394326A CN 105015760 A CN105015760 A CN 105015760A
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- wing
- propeller
- reinforcing frame
- lift
- paddle mechanism
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Abstract
The invention discloses a propeller-type lift-enhancing structure for symmetric wing. The propeller-type lift-enhancing structure comprises a reinforcing frame, a propeller mechanism mounting frame, a propeller mechanism, a propeller and a driving motor, wherein the propeller mechanism and the propeller mechanism mounting frame are embedded in the reinforcing frame in a matched way; the reinforcing frame is fixed in the wing; and the reinforcing frame is symmetrically mounted in a double-wing extending direction. The propeller mechanism mounting frame is in clearance fit with the reinforcing frame; a circuit transmission part is placed within a hollow radial shaft bracket; and the propeller mechanism is operated by the driving motor so as to drive the propeller to rotate to different directions at different rotation speeds so that requirements of an aircraft on aerodynamic characteristics in different flight stages are satisfied. The propeller-type lift-enhancing structure for the symmetric wing, disclosed by the invention, is advantaged in that the wing is embedded into the propeller mechanism to generate integrated lift without affecting the total mass of the aircraft structure so that the lift of the whole aircraft is supplemented; and through controlling working states of the propellers of the two wings, specific vertical landing, lift enhancing, lift weakening, posture controlling functions are realized.
Description
Technical field
The present invention relates to aerospace applications technical field, specifically, relate to a kind of rotary propeller type lift-rising structure for symmetrical wing.
Background technology
The further raising that modern needs require aircraft performance, the optimization of aerodynamic configuration becomes the focus that field of flight vehicle design is chased, the design of the wing most important thing especially in general design links.
Existing disclosed technical literature " fan lift-rising wing " (Nanchang University of aviation's journal, 4th phase in 2010) in, propose, in the above-head of aerofoil profile, a rotatable part is installed, increase the circular rector of wing by its rotation and utilize the Shedding Vortex of certain parts generation on aircraft to the interference of main plane, improving airfoil lift.This design apparatus adds the lift in full range of angles of attack that wing normally works; Also by fan pressure-vaccum effect backward, restrained effectively the burbling of wing, thus the stalling incidence of wing is increased, namely the maximum lift of wing increases.The fan lift-rising wing proposed in " fan lift-rising wing " utilizes fan to the meiobar of front end generation during final vacuum to increase airfoil lift, although carried out pneumatic checking in full range of angles of attack, and obtains ideal effect; But integrally-built installation is arranged and structural strength is not verified, and this structure is only applicable to the lift-rising of low-speed operations device.
At document " whirlpool oar nacelle of airplane/high lift device integrated pneumatic design study " (Aeronautics, 2013) in, propose one for large aircraft and realize aircraft lift-rising mentality of designing and scheme by Airfoils design and the change of wing three-dimensional structure, and analyze structure design and its lift-rising principle and feature of wing flap.In " whirlpool oar nacelle of airplane/high lift device integrated pneumatic design study ", Airfoils design is similar to the installation effect of wing trailing edge flaps, the aeroperformance of aircraft is improved indeed through the camber increasing aerofoil profile, the realization of its structure and pneumatic checking also comparative maturity, but the hinge moment problem of wing flap design exists always, and when the angle of attack is very large, resistance also can significantly increase, and aeroperformance is lost more than gain, the control realization difficulty of wing flap simultaneously.
Summary of the invention
In order to avoid the deficiency that prior art exists, the present invention proposes a kind of rotary propeller type lift-rising structure for symmetrical wing, and it utilizes wing embedding to revolve paddle mechanism and produces fusion type lift, realizes supplementing the lift of whole aircraft; By revolving the control of oar mode of operation to both wings, realize in the demand of different mission phase for aerodynamic characteristic, and realize specific vertical landing, lift increase and decrease and gesture stability function.
The technical solution adopted for the present invention to solve the technical problems is: comprise wing, characterized by further comprising reinforcing frame, revolve paddle mechanism placing frame, revolve paddle mechanism, radial pedestal, center settle ring, screw propeller, drive motor, strengthening rib, thin circular cylinder, connection box, revolve paddle mechanism and revolve paddle mechanism placing frame and coordinate and be positioned at reinforcing frame, reinforcing frame is nested in wing, and installs along two wing exhibitions to symmetry;
The described paddle mechanism placing frame that revolves settles ring, radial pedestal and connection box to form by center, three radial pedestals centrally settle ring circumference angularly to distribute, connection box and center settle ring fixedly to be welded by radial pedestal, revolving paddle mechanism placing frame is nested in reinforcing frame, and the connection box external diameter and the reinforcing frame internal diameter that revolve paddle mechanism placing frame are free-running fit; It is inner to pedestal that circuit transmission part is placed on hollow drive; Screw propeller is connected with drive motor, and drive motor and the center of revolving paddle mechanism settle ring minor diameter fit to install, and drive motor carrying screws rotates;
Described reinforcing frame is double-layer thin wall cylindrical structure, and between double-layer thin wall cylinder, circumference is angularly distributed with three strengthening ribs, the fixed form that double-layer thin wall cylinder and strengthening rib adopt node to weld, and the strengthening rib place along reinforcing frame internal ring wall is angularly distributed with through hole.
Revolve paddle mechanism, center arrangement ring and reinforcing frame coaxially to install.
Beneficial effect
A kind of rotary propeller type lift-rising structure for symmetrical wing that the present invention proposes, under the prerequisite not affecting Flight Vehicle Structure total mass, manipulated by drive motor and embeddedly revolve paddle mechanism, drive it to rotate with different rotating speeds and direction, meet aircraft in the requirement of different mission phases to aeroperformance.Revolve paddle mechanism work can ensure aircraft without off, without angle of attack state under vertical and landing takeoff; By controlling the velocity of rotation of drive motor, realizing the control to lift size, coordinating and changing drive motor rotation direction, realize longitudinal plane of symmetry both sides generation normal force poor, thus change of flight attitude; When cruising phase needs aircraft lift face to provide less lift, by the drive motor velocity of rotation that slows down, even stop drive motor rotating and reach energy-conservation object.
The present invention is used for the rotary propeller type lift-rising structure of symmetrical wing, because symmetrical airfoil realizes conveniently, being applicable to any symmetrical shape aerofoil profile in embedding is installed and mechanism is fixed.Utilization is revolved oar and is rotated the lift produced, and realizes the vertical takeoff and landing of aircraft, lift compensation, lift method to motor-driven overload and gesture stability function.
The present invention is used for the rotary propeller type lift-rising structure of symmetrical wing, adopts the composite material of modern light-duty, can realize the requirement of laser intensity on the one hand, on the other hand, can not bring more puzzlement again to the design of Flight Vehicle Structure oeverall quality.
Accompanying drawing explanation
Below in conjunction with drawings and embodiments, a kind of rotary propeller type lift-rising structure for symmetrical wing of the present invention is described in further detail.
Fig. 1 is the rotary propeller type lift-rising structural representation of the symmetrical wing of the present invention.
Fig. 2 is the reinforcing frame schematic diagram of rotary propeller type lift-rising structure of the present invention.
Fig. 3 of the present inventionly revolves paddle mechanism placing frame connection box schematic diagram.
Fig. 4 is that ring connection diagram is settled at radial pedestal of the present invention and center.
Fig. 5 is screw propeller of the present invention and drive motor installation position schematic diagram.
In figure:
1. wing 2. reinforcing frame 3. revolves paddle mechanism placing frame 4. and revolves paddle mechanism 5. radial pedestal 6. center arrangement ring 7. screw propeller 8. drive motor 9. strengthening rib 10. thin circular cylinder 11. connection box
Detailed description of the invention
The present embodiment is a kind of rotary propeller type lift-rising structure for symmetrical wing.
Consult Fig. 1 ~ Fig. 5, the present embodiment is used for the rotary propeller type lift-rising structure of symmetrical wing, be a kind of can for aircraft provide merge the embedded of lift revolve paddle mechanism, the realization of whole mechanism lift-rising effect is the controlled synergy by inner each several part mechanism, driven by drive motor and make itself and wing jointly for aircraft provides lift, structure ensure that the size and Orientation of lift is controlled effectively, and is adapted to the pneumatic requirement of different inflight phase; Structure is more obvious for the anti-proliferative effect of low-altitude low-speed flight environment of vehicle.
In the present embodiment, for the rotary propeller type lift-rising structure of symmetrical wing by wing 1, reinforcing frame 2, revolve paddle mechanism placing frame 3, revolve paddle mechanism 4, radial pedestal 5, center settle ring 6, screw propeller 7, drive motor 8, strengthening rib 9, thin circular cylinder 10, connection box 11 to form; Revolve paddle mechanism 4 and revolve paddle mechanism placing frame 3 and coordinate, be fixedly connected with reinforcing frame 2, reinforcing frame 2 is nested in wing 1, and reinforcing frame 2 is opened up along two wings 1 and installed to symmetry.Reinforcing frame 2 is for agreeing with double-layer thin wall cylinder 10 structure of wing cover height, and its material selection is consistent with wing 1 inner structure material, the fixed form of welding with adopting node between inner skeleton.Between double-layer thin wall cylinder 10, circumference is angularly distributed with three strengthening ribs 9, and double-layer thin wall cylinder and strengthening rib adopt and be welded and fixed, and strengthening rib 9 place along reinforcing frame 2 internal ring wall angularly distributes and is processed with through hole.Strengthening rib 9 ensure that the resistance to compression shear strength of structure, utilize the feature that thin circular cylinder 10 stress limit is axially larger, connect not only failure-free by the reinforcement of double-layer thin wall cylinder and ensure the aerodynamic configuration of memory, prevent from being out of shape under larger Aerodynamic force action, and provide connection location for revolving paddle mechanism placing frame 3.Revolving paddle mechanism placing frame 3 settles ring 6, radial pedestal 5 and connection box 11 to form by center, revolves the material selection intensity of paddle mechanism placing frame 3, hardness is large, and the composite material of lighter weight.Three radial pedestals 5 centrally settle ring 6 circumference angularly to distribute, and connection box 11 and center settle ring 6 to be welded to connect by radial pedestal 5, and carry out strengthening.Revolve paddle mechanism placing frame 3 to be nested in reinforcing frame 2, connection box 11 external diameter and reinforcing frame 2 internal diameter that revolve paddle mechanism placing frame 3 are free-running fit; It is inner to pedestal 5 that circuit transmission part is placed on hollow drive; Screw propeller 7 is connected with drive motor 8, and the drive motor 8 revolving paddle mechanism 4 settles ring 6 minor diameter fit to install with center, and drive motor 8 carrying screws 7 rotates, and then produces lift.
In the present embodiment, driven by the classification of drive motor 8, screw propeller 7 velocity of rotation is controlled, thus the lift size and Orientation provided for whole aircraft is controlled, not only can realize the vertical takeoff and landing without the need to the start of a race, more can control attitude of flight vehicle and the motor-driven overload of change normal direction in flight course.By the rotating speed that adjustment drive motor 8 is different, can meet under difference flight requires for aircraft provides required lift, by setting rotation direction and the rotating speed of the drive motor of wing side, make aircraft plane of symmetry both sides screw propeller 7 provide lift direction contrary, differ in size, the quick control to attitude of flight vehicle can be realized.
Claims (2)
1. the rotary propeller type lift-rising structure for symmetrical wing, comprise wing, it is characterized in that: also comprise reinforcing frame, revolve paddle mechanism placing frame, revolve paddle mechanism, radial pedestal, center settle ring, screw propeller, drive motor, strengthening rib, thin circular cylinder, connection box, revolve paddle mechanism and revolve paddle mechanism placing frame and coordinate and be positioned at reinforcing frame, reinforcing frame is nested in wing, and installs along two wing exhibitions to symmetry;
The described paddle mechanism placing frame that revolves settles ring, radial pedestal and connection box to form by center, three radial pedestals centrally settle ring circumference angularly to distribute, connection box and center settle ring fixedly to be welded by radial pedestal, revolving paddle mechanism placing frame is nested in reinforcing frame, and the connection box external diameter and the reinforcing frame internal diameter that revolve paddle mechanism placing frame are free-running fit; It is inner to pedestal that circuit transmission part is placed on hollow drive; Screw propeller is connected with drive motor, and drive motor and the center of revolving paddle mechanism settle ring minor diameter fit to install, and drive motor carrying screws rotates;
Described reinforcing frame is double-layer thin wall cylindrical structure, and between double-layer thin wall cylinder, circumference is angularly distributed with three strengthening ribs, the fixed form that double-layer thin wall cylinder and strengthening rib adopt node to weld, and the strengthening rib place along reinforcing frame internal ring wall is angularly distributed with through hole.
2. the rotary propeller type lift-rising structure for symmetrical wing according to claim 1, is characterized in that: revolve paddle mechanism, center arrangement ring and reinforcing frame and coaxially install.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510394326.1A CN105015760A (en) | 2015-07-07 | 2015-07-07 | Propeller-type lift-enhancing structure for symmetric wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510394326.1A CN105015760A (en) | 2015-07-07 | 2015-07-07 | Propeller-type lift-enhancing structure for symmetric wing |
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| Publication Number | Publication Date |
|---|---|
| CN105015760A true CN105015760A (en) | 2015-11-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510394326.1A Pending CN105015760A (en) | 2015-07-07 | 2015-07-07 | Propeller-type lift-enhancing structure for symmetric wing |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3083935A (en) * | 1962-01-15 | 1963-04-02 | Piasecki Aircraft Corp | Convertible aircraft |
| US3139244A (en) * | 1961-08-15 | 1964-06-30 | Cooper B Bright | Inflatable vtol aircraft |
| US5320305A (en) * | 1992-07-22 | 1994-06-14 | Lockheed Corporation | Propulsion system for an aircraft providing V/STOL capability |
| US5454531A (en) * | 1993-04-19 | 1995-10-03 | Melkuti; Attila | Ducted propeller aircraft (V/STOL) |
| US20060192046A1 (en) * | 2005-02-25 | 2006-08-31 | The Boeing Company | Aircraft capable of vertical and short take-off and landing |
| CN102120489A (en) * | 2011-02-28 | 2011-07-13 | 南昌航空大学 | Tilt ducted unmanned aerial vehicle |
| WO2014021798A2 (en) * | 2012-07-31 | 2014-02-06 | Bulent Oran | Vertical take off/landing and balance system for aerial vehicles |
| CN104176250A (en) * | 2013-05-23 | 2014-12-03 | 中国直升机设计研究所 | Vertical take-off and landing rotor aircraft with ducts built in wings |
-
2015
- 2015-07-07 CN CN201510394326.1A patent/CN105015760A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3139244A (en) * | 1961-08-15 | 1964-06-30 | Cooper B Bright | Inflatable vtol aircraft |
| US3083935A (en) * | 1962-01-15 | 1963-04-02 | Piasecki Aircraft Corp | Convertible aircraft |
| US5320305A (en) * | 1992-07-22 | 1994-06-14 | Lockheed Corporation | Propulsion system for an aircraft providing V/STOL capability |
| US5454531A (en) * | 1993-04-19 | 1995-10-03 | Melkuti; Attila | Ducted propeller aircraft (V/STOL) |
| US20060192046A1 (en) * | 2005-02-25 | 2006-08-31 | The Boeing Company | Aircraft capable of vertical and short take-off and landing |
| CN102120489A (en) * | 2011-02-28 | 2011-07-13 | 南昌航空大学 | Tilt ducted unmanned aerial vehicle |
| WO2014021798A2 (en) * | 2012-07-31 | 2014-02-06 | Bulent Oran | Vertical take off/landing and balance system for aerial vehicles |
| CN104176250A (en) * | 2013-05-23 | 2014-12-03 | 中国直升机设计研究所 | Vertical take-off and landing rotor aircraft with ducts built in wings |
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Effective date of abandoning: 20171222 |
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