CN114426098A - Novel dish wing - Google Patents
Novel dish wing Download PDFInfo
- Publication number
- CN114426098A CN114426098A CN202210186504.1A CN202210186504A CN114426098A CN 114426098 A CN114426098 A CN 114426098A CN 202210186504 A CN202210186504 A CN 202210186504A CN 114426098 A CN114426098 A CN 114426098A
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- CN
- China
- Prior art keywords
- connecting plate
- propeller blades
- wing
- accommodating groove
- section
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/06—Aircraft not otherwise provided for having disc- or ring-shaped wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C37/00—Convertible aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/10—All-wing aircraft
- B64C2039/105—All-wing aircraft of blended wing body type
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a novel disc wing, which comprises a disc wing main body and a plurality of propeller blades. The disc wing body is provided with a plurality of accommodating grooves. The propeller blades are respectively connected in the accommodating grooves in a sliding mode, the elastic pieces are arranged between the propeller blades and the accommodating grooves, and when the rotating speed of the novel disc wing reaches a certain numerical value, the propeller blades overcome the resistance of the elastic pieces and slide out of the notches of the accommodating grooves under the action of centrifugal force. When the rotating speed reaches a certain value (namely, the disc wing propulsion system is in a rotating state), the propeller blades can overcome the resistance of the elastic piece to automatically extend out under the action of centrifugal force, so that lift force is provided for the aircraft; when the rotating speed is zero (namely when the disc wing propulsion system stops rotating) or less than a certain value, the centrifugal force is zero or less, and the propeller blades can automatically retract under the action of the elastic force of the elastic element and are in a flat flying state, so that the disc wing main body with the airfoil section provides lift.
Description
Technical Field
The invention belongs to the technical field of aircraft machinery, and particularly relates to a novel disc wing.
Background
The disc wing is a novel aircraft propulsion system, can enable the aircraft to vertically take off and land and hover in the air like a helicopter, and can also provide lift force for the aircraft like a fixed wing during flat flight. The disk wing has the characteristics that the aircraft can be mutually matched and switched between a helicopter mode and a fixed wing aircraft mode, and the utilization rate is high. In the field of low-speed aerodynamics, the modern disc wing technology proposed by Russian Central hydrodynamics research institute has the advantages of small cruising resistance, extremely large lift coefficient, extremely high economy, suitability for vertical take-off and landing and the like, and is successfully used for the design and development of vertical take-off and landing passenger planes and disc wing type airships. The dynamics of the related research on disc wings are worthy of research and attention by the same.
The disk wing is mainly formed by combining a wing disk with corresponding wing profiles and a plurality of propellers, when the disk wing needs to take off and land vertically or hover, the propellers mainly provide lift force, and when the disk wing flies flatly, the propellers need to be hidden, and the wing disk provides lift force. The structural transformation of the disc wings between flat flight and vertical take-off and landing or hovering is a big difficulty.
Disclosure of Invention
The invention aims to provide a novel disc wing to solve the problem that the structure of the disc wing is difficult to convert between flat flight and vertical take-off and landing or hovering in the prior art.
The technical scheme of the invention is as follows:
a novel disc wing comprises a disc wing body and a plurality of propeller blades, wherein the disc wing body is provided with a plurality of accommodating grooves matched with the propeller blades, and the propeller blades are connected in the corresponding accommodating grooves in a sliding manner;
the novel disc wing is characterized in that an elastic piece is arranged between the propeller blades and the accommodating groove, and when the rotating speed of the novel disc wing reaches a certain numerical value, the propeller blades overcome the resistance of the elastic piece to slide out of the groove opening of the accommodating groove under the action of centrifugal force.
Preferably, a limiting structure is arranged in the accommodating groove and used for preventing the propeller blades from being separated from the accommodating groove under the action of centrifugal force.
Preferably, the one end of screw propeller paddle orientation storage tank bottom is connected with the connecting plate, the elastic component respectively with the connecting plate with the tank bottom of storage tank is connected, the elastic component has through the connecting plate will the screw propeller paddle draws to the pulling force of storage tank bottom.
Preferably, the accommodating groove is divided into a connecting plate section and a paddle section along the depth direction, the paddle section is arranged on one side of the groove bottom of the accommodating groove, and the connecting plate section is arranged on one side of a notch of the accommodating groove;
the connecting plate is connected in the connecting plate section in a sliding manner, and the connecting plate is matched with the connecting plate section; the propeller blades are connected with the blade sections in a sliding mode, and the propeller blades are matched with the blade sections.
Preferably, the boundary between the paddle section and the connecting plate section is a step surface facing the bottom of the accommodating groove, and the step surface is used for limiting the connecting plate to enter the paddle section.
Preferably, the propeller blades are partially received in the web section and partially received in the blade section.
Preferably, the cross-sectional area of the accommodating groove at the connecting plate section is larger than that at the blade section.
Preferably, the connecting plate is rotatably connected with a plurality of idler wheels, the idler wheels are in rolling connection with the side walls of the accommodating groove, and the connecting plate moves in the accommodating groove along the groove depth direction through the idler wheels.
Preferably, the side wall of the accommodating groove is provided with a plurality of roller grooves corresponding to the plurality of rollers respectively, and the roller grooves are used for limiting the moving track of the rollers.
Preferably, the depth of the accommodating groove is greater than the length of the propeller blades, and when the rotating speed of the novel disc wing is zero or less than a certain value, the propeller blades are all accommodated in the accommodating groove.
Due to the adoption of the technical scheme, compared with the prior art, the invention has the following advantages and positive effects:
when the rotating speed reaches a certain value (namely the disc wing propulsion system is in a rotating state), the propeller blades can overcome the resistance of the elastic part and automatically extend out under the action of centrifugal force to provide lift force for the aircraft, and at the moment, the novel disc wings are in a vertical take-off and landing or hovering state; when the rotating speed is zero (namely when the disc wing propulsion system stops rotating) or less than a certain value, the centrifugal force is zero or less, and the propeller blades can automatically retract under the action of the elastic force of the elastic piece to be in a flat flying state. Therefore, the invention solves the problem that the structure of the disc wing is difficult to convert between flat flight and vertical take-off and landing or hovering in the prior art.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention.
FIG. 1 is a schematic view of the overall structure of a novel disk wing of the present invention in a propeller blade extended state;
FIG. 2 is a schematic view of the overall structure of a novel disk wing of the present invention in a retracted state of the propeller blades;
FIG. 3 is a schematic cross-sectional view of a novel disc wing of the present invention in a propeller blade extended condition;
FIG. 4 is a schematic cross-sectional view of a novel disc wing of the present invention in a retracted state of the propeller blades;
FIG. 5 is a schematic diagram showing a specific structure of a novel disc wing of the present invention at a connection plate;
fig. 6 is a schematic structural view of a roller groove according to the present invention.
Description of reference numerals:
1: a disc wing body; 2: a propeller blade; 3: a connecting plate; 4: a spring; 5: a roller; 6: a connecting plate section; 7: a blade section; 8: and (4) a roller groove.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following description will be made with reference to the accompanying drawings. It is obvious that the drawings in the following description are only some examples of the invention, and that for a person skilled in the art, other drawings and embodiments can be derived from them without inventive effort.
For the sake of simplicity, the drawings only schematically show the parts relevant to the present invention, and they do not represent the actual structure as a product. In addition, in order to make the drawings concise and understandable, components having the same structure or function in some of the drawings are only schematically illustrated or only labeled. In this document, "a" means not only "only one of this but also a case of" more than one ".
When the disc wings serve as fixed wings, the propeller blades can have unnecessary influence on aerodynamics, so that the propeller blades need to be hidden; when the propeller is required to provide lift, the propeller must be extended in time. The novel disc wing provided by the invention can meet the switching requirement of the disc wing from a helicopter mode to a fixed wing mode, and particularly realizes the automatic telescopic function of a propeller part of a disc wing propulsion system.
Referring to fig. 1 to 6, the present embodiment provides a novel discone wing, including a discone wing main body and a plurality of propeller blades 2. The disc wing body 1 is provided with a plurality of accommodating grooves matched with the propeller blades 2, and the propeller blades 2 are connected in the corresponding accommodating grooves in a sliding mode. An elastic piece is arranged between the propeller blades 2 and the accommodating groove, and when the rotating speed of the novel disc wing reaches a certain numerical value, the propeller blades 2 overcome the resistance of the elastic piece and slide out of the groove opening of the accommodating groove under the action of centrifugal force.
When the rotating speed reaches a certain value (namely, the disc wing propulsion system is in a rotating state), the propeller blades 2 can overcome the resistance of the elastic part and automatically extend out under the action of centrifugal force, so that lift force is provided for the aircraft; when the rotation speed is zero (i.e. when the disc wing propulsion system stops rotating) or less than a certain value, the centrifugal force is zero or less, and the propeller blades 2 can automatically retract under the elastic force of the elastic member, and are in a flat flight state, and lift is provided by the disc wing main body with the airfoil section.
The structure of the present embodiment will now be explained.
The groove depth of the accommodating groove is greater than the length of the propeller blades 2, and when the rotating speed of the novel disc wing is zero or less than a certain numerical value, the propeller blades 2 are all accommodated in the accommodating groove. The containing groove is internally provided with a limiting structure for preventing the propeller blades 2 from being separated from the containing groove under the action of centrifugal force, namely, the propeller blades 2 are still partially positioned in the containing groove when vertically taking off and landing or hovering.
The one end of screw paddle 2 towards the storage tank bottom is connected with connecting plate 3, and the elastic component is connected with the tank bottom of connecting plate 3 and storage tank respectively, and the elastic component has the pulling force of pulling screw paddle 2 to the storage tank bottom through connecting plate 3. The propeller blades 2 and the connecting plate 3 can be connected in a screw or high-performance glue mode, and the extension of the propeller blades 2 is controlled by controlling the connecting plate 3.
Specifically, the accommodating groove can be divided into a connecting plate section 6 and a paddle section 7 along the depth direction, wherein the paddle section 7 is arranged on one side of the groove bottom of the accommodating groove, and the connecting plate section 6 is arranged on one side of the groove opening of the accommodating groove. The connecting plate 3 is connected in the connecting plate section 6 in a sliding manner, and the connecting plate 3 is matched with the connecting plate section 6; the propeller blades 2 are connected with the blade sections 7 in a sliding mode, and the propeller blades 2 are matched with the blade sections 7. Specifically, the cross section of the connecting plate 3 may be slightly larger than the cross section of the accommodating groove at the connecting plate section 6, and the cross section of the propeller blade 2 may be slightly larger than the cross section of the accommodating groove at the blade section 7. The propeller blades 2 are partly received in the connecting plate section 6 and partly in the blade section 7.
The limit structure can be arranged at the boundary of the connecting plate section 6 and the blade section 7, and specifically can be as follows: the boundary between the blade section 7 and the connecting plate section 6 is a step surface arranged towards the bottom of the accommodating groove, and the step surface is used for limiting the connecting plate 3 from entering the blade section 7. The stepped surface may be a surface of a fixture block protruding from the side wall of the receiving groove, and it is noted that the fixture block cannot affect the movement of the propeller blade 2. Also, as in this embodiment, the cross-sectional area of the receiving groove at the connecting plate section 6 is larger than the cross-sectional area at the blade section 7, and the step surface is a surface naturally formed at the connection point of the connecting plate section 6 and the blade section 7. In the invention, the arrangement mode of the step surface and even the specific structure of the limiting structure can have various conditions, and the arrangement mode is not limited.
A plurality of idler wheels 5 can be rotatably connected to the connecting plate 3, the idler wheels 5 are in rolling connection with the side wall of the accommodating groove, and the connecting plate 3 moves in the accommodating groove along the groove depth direction through the idler wheels 5. The arrangement of the roller 5 can reduce the friction resistance of the propeller blade 2 during extension and retraction.
Further, a plurality of roller grooves 8 respectively corresponding to the plurality of rollers 5 may be disposed on a side wall of the accommodating groove (specifically, a side wall of the connecting plate section 6) to limit a moving track of the rollers 5 and prevent the rollers 5 from being dislocated. Simultaneously, the moment that propeller blade 2 received can transmit on the wing dish body through connecting plate 3 and gyro wheel 5.
The elastic member may employ a spring 4. The tank bottom of storage tank is the center pin of novel dish wing, and the one end and the connecting plate 3 of spring 4 are connected, and the other end is connected with the center pin. When novel dish wing rotational speed risees, screw paddle 2 is under the effect of centrifugal force, and the pulling force of overcoming spring 4 removes to the notch external direction of storage tank, realizes the purpose that screw paddle 2 stretches out. When the novel dish wing stall or rotational speed are not enough, can pull back the screw propeller blade 2 in the storage tank on dish wing body 1 through the pulling force of spring 4, realize the shrink purpose of screw.
Specifically, in this embodiment, four propeller blades 2 may be provided, and four accommodating grooves may be correspondingly provided on the disc wing body 1. However, the number of the propeller blades 2 in the present embodiment is a specific case of the present invention, and is not limited thereto, and the specific case may be designed according to practical situations.
The novel dish wing that this embodiment provided utilizes the centrifugal force effect of novel dish wing when rotating to realize propeller blade 2's the function of stretching out, utilizes the pulling force of spring 4 to realize propeller blade 2's contraction function. Specifically, when the disc wing propulsion system is in a rotating state, the propeller blades 2 automatically extend out under the action of centrifugal force to provide lift force for the aircraft; when the disc wing propulsion system stops rotating, is in a flat flight state or stops working, the propeller can be automatically retracted, and the novel disc wing provides lift force through the disc wing body with the wing section. Furthermore, the connecting plate 3 with the roller 5 and the roller groove 8 arranged in the accommodating groove stabilize the telescopic motion of the propeller blade 2, and the step at the boundary of the connecting plate section 6 and the blade section 7 on the accommodating groove limits the extension degree of the propeller blade 2.
The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the above embodiments. Even if various changes are made to the present invention, it is still within the scope of the present invention if they fall within the scope of the claims of the present invention and their equivalents.
Claims (10)
1. The novel disc wing is characterized by comprising a disc wing body and a plurality of propeller blades, wherein the disc wing body is provided with a plurality of accommodating grooves matched with the propeller blades, and the propeller blades are connected in the corresponding accommodating grooves in a sliding manner;
the novel disc wing is characterized in that an elastic piece is arranged between the propeller blades and the accommodating groove, and when the rotating speed of the novel disc wing reaches a certain numerical value, the propeller blades overcome the resistance of the elastic piece to slide out of the groove opening of the accommodating groove under the action of centrifugal force.
2. The novel disc wing as claimed in claim 1, wherein a limiting structure is provided in the accommodating groove for preventing the propeller blades from being separated from the accommodating groove by centrifugal force.
3. The novel pan wing as claimed in claim 1, wherein a connecting plate is connected to the end of the propeller blade facing the bottom of the tank, and the elastic member is connected to the connecting plate and the bottom of the tank, respectively, and has a pulling force pulling the propeller blade toward the bottom of the tank through the connecting plate.
4. The novel disc wing according to claim 3, wherein the accommodating groove is divided into a connecting plate section and a paddle section in a depth direction, the paddle section is provided on one side of a groove bottom of the accommodating groove, and the connecting plate section is provided on one side of a notch of the accommodating groove;
the connecting plate is connected in the connecting plate section in a sliding manner, and the connecting plate is matched with the connecting plate section; the propeller blades are connected with the blade sections in a sliding mode, and the propeller blades are matched with the blade sections.
5. The novel disc wing as claimed in claim 4, wherein the boundary between the blade section and the connecting plate section is a step surface disposed toward the bottom of the accommodating groove, and the step surface is used for limiting the connecting plate from entering the blade section.
6. The novel disc wing as claimed in claim 4, wherein the propeller blades are partially received in the web section and partially received in the blade section.
7. The novel pan wing as claimed in claim 6, wherein the cross-sectional area of the receiving slot at the web section is greater than the cross-sectional area at the blade section.
8. The novel dish wing as claimed in claim 3, wherein a plurality of rollers are rotatably connected to the connecting plate, the rollers are in rolling connection with the side wall of the accommodating groove, and the connecting plate is moved in the accommodating groove along the groove depth direction by the rollers.
9. The novel dish wing as claimed in claim 8, wherein the side wall of the accommodating groove is provided with a plurality of roller grooves corresponding to the plurality of rollers, respectively, for limiting the moving track of the rollers.
10. The novel disc wing as claimed in claim 1, wherein the groove depth of the accommodating groove is greater than the length of the propeller blades, and when the rotating speed of the novel disc wing is zero or less than a certain value, the propeller blades are all accommodated in the accommodating groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210186504.1A CN114426098A (en) | 2022-02-28 | 2022-02-28 | Novel dish wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210186504.1A CN114426098A (en) | 2022-02-28 | 2022-02-28 | Novel dish wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114426098A true CN114426098A (en) | 2022-05-03 |
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ID=81312479
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210186504.1A Pending CN114426098A (en) | 2022-02-28 | 2022-02-28 | Novel dish wing |
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| CN (1) | CN114426098A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3273655A (en) * | 1966-09-20 | Center body fivotally retractable rotor | ||
| US5064143A (en) * | 1989-04-19 | 1991-11-12 | Sky Disk Holding Sa | Aircraft, having a pair of counter rotating rotors |
| CN102649476A (en) * | 2011-02-28 | 2012-08-29 | 波音公司 | Disc rotor retraction system |
| CN104773291A (en) * | 2015-04-08 | 2015-07-15 | 南昌航空大学 | Disc-shaped rotor wing unmanned helicopter |
| US20170320564A1 (en) * | 2014-08-26 | 2017-11-09 | Sergei Yurevich Kuzikov | Air wheel rotor, a gyro stabilized aircraft and a wind-driven power generator using the air wheel rotor, and a stationary launching device |
| US20210354810A1 (en) * | 2016-08-11 | 2021-11-18 | The Hayden Effect, Llc | Apparatus for providing rail-based vertical short takeoff and landing and operational control |
-
2022
- 2022-02-28 CN CN202210186504.1A patent/CN114426098A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3273655A (en) * | 1966-09-20 | Center body fivotally retractable rotor | ||
| US5064143A (en) * | 1989-04-19 | 1991-11-12 | Sky Disk Holding Sa | Aircraft, having a pair of counter rotating rotors |
| CN102649476A (en) * | 2011-02-28 | 2012-08-29 | 波音公司 | Disc rotor retraction system |
| US20170320564A1 (en) * | 2014-08-26 | 2017-11-09 | Sergei Yurevich Kuzikov | Air wheel rotor, a gyro stabilized aircraft and a wind-driven power generator using the air wheel rotor, and a stationary launching device |
| CN104773291A (en) * | 2015-04-08 | 2015-07-15 | 南昌航空大学 | Disc-shaped rotor wing unmanned helicopter |
| US20210354810A1 (en) * | 2016-08-11 | 2021-11-18 | The Hayden Effect, Llc | Apparatus for providing rail-based vertical short takeoff and landing and operational control |
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