CN2714420Y - Vertically ascending device without rotary wing - Google Patents
Vertically ascending device without rotary wing Download PDFInfo
- Publication number
- CN2714420Y CN2714420Y CN 200320128091 CN200320128091U CN2714420Y CN 2714420 Y CN2714420 Y CN 2714420Y CN 200320128091 CN200320128091 CN 200320128091 CN 200320128091 U CN200320128091 U CN 200320128091U CN 2714420 Y CN2714420 Y CN 2714420Y
- Authority
- CN
- China
- Prior art keywords
- fin
- fan
- vertical lift
- girdle
- wing
- Prior art date
- 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.)
- Expired - Fee Related
Links
Abstract
The utility model relates to the technical field of an active type vertically ascending air vehicle, particularly a vertically ascending device without a rotary wing. The utility model comprises the components of an engine, a gear box, a fan, etc., and also comprises two wind shield plates which are positioned at the left end and the right end of a half wind tunnel structure composed of the wind shield plates. The fan is arranged in the half wind tunnel. A blade group mechanism which is composed of fins is arranged in the direction of air flow blown by the fan, and each fin is movably arranged on the wind shield plates of the left end and the right end by an end shaft of the fin and is ranged from high position to low position along the direction of the air flow. The blade group mechanism is provided with a regulating mechanism for an attack angle of each fin. The rate of Cl / Cd is between 15 and 25, and even higher because each fin is orderly arranged up and down or back and forth so that the device has novel ascending force. The utility model has the advantages of thrust force combination and high quality, vertical takeoff and landing with zero speed is realized, and flight distance equal to or larger than 1600 km is realized.
Description
Technical field:
The utility model relates to active vertical lift-off vehicle technology field, the vertical lift-off device of particularly a kind of no rotor.
Background technology:
The drawback that modern helicopter exists: (1) is in cruising, before rotor is tilted to, lift both was provided, the pulling force that advances is provided again, because the rotor quality factor are too low, waste of power is too big, thereby the helicopter voyage is bitter short, cause unable executing the task in, the desert marine, in the grassland, more unable transoceanic flight at writing brush.(2) naked the flying cruelly of rotor changeed, and can not walk in the atural object of complexity, carries out rescue, fire-fighting, hunting.
Summary of the invention:
The purpose of this utility model aims to provide a kind ofly can vertically go up to the air and overcome drawback described in the background technology (2), with high C
L: C
DThe slow-witted wing lift in cruising is provided, overcome drawback described in the background technology (2), to realize the vertical lift-off device of no rotor of oceangoing voyage.
The technical scheme that realizes the foregoing invention purpose is: the vertical lift-off device of this no rotor comprises outside the parts such as driving engine, change speed gear box, fan, it also comprises two ends, the left and right sides air baffle that constitutes half construction of wind tunnel, described fan holds in it, the air flow line that fan bloats is provided with the girdle wing group mechanism that is made up of fin, each fin all is movably arranged on the air baffle of two ends, the left and right sides by its end axle, each fin is arranged to low by height along air flow line, and girdle wing flock mating is equipped with fin angle of attack regulating mechanism.Externally under the effect of artificial wind regime, the wing good aerodynamic configuration that becomes of upper and lower ventilative " half construction of wind tunnel " and girdle at first produces lift, produce forward pulling force and thrust after the lift-off again, the formation of lift and pulling force is by the angle of attack regulating mechanism of composition girdle wing group's fin.Make the utility model not have the vertical lift-off device of rotor thus and be called as " active vertical lift-off aircraft ".
The vertical lift-off device of no rotor according to technique scheme is implemented is arranged on the aircraft and could embodies its value.As make a class and do not have the long-range helicopter WVH of rotor, to promote the use of, the aircraft cost reduces by one times and even more, and aircraft fuel consumption falls few 50% even still less, and aircraft passenger and freight cost reduces to 1/3 or lower, and the airplane fault rate is reduced to about 1/10.So in fact adopted aircraft of the present utility model, its excellent performance, of many uses.
Description of drawings:
Fig. 1 is the utility model lift unit link/exploitativeness structural representation.
The specific embodiment:
Provide a specific embodiment of the present utility model below in conjunction with accompanying drawing.The vertical lift-off device of the described no rotor of this embodiment is by driving engine 1, change speed gear box 2, fan 3, air baffle 4, fin 5, pitman shaft knot 6, posture adjustment connecting rod 7, connecting rod hook 8, slide rail 9, handle 10, fixedly arbor wheel 11, posture adjustment slip-knot 12, whole to slip-knot 13, movable rod 14, honeycomb screen mechanism 15 forms, driving engine 1--change speed gear box 2 back (show left plate with two ends, left and right sides air baffle 4 among the figure, right panel is slightly) formation half construction of wind tunnel, fan 3 holds to go among this half construction of wind tunnel, the air flow line that fan 3 bloats is provided with the girdle wing group mechanism that is made up of fin 5, each fin 5 all is movably arranged on two ends, the left and right sides air baffle 4 by its end axle, each fin 5 is arranged to low by height along air flow line, and girdle wing flock mating is equipped with the angle of attack regulating mechanism of fin 5.
Each girdle wing group in the present embodiment is made up of 1～8 fin.
Fin angle of attack regulating mechanism in the present embodiment is a manual link mechanism, the movable rod 14 of this connecting rod mechanism and posture adjustment connecting rod 7 are by slide rail 9 location, this posture adjustment connecting rod 7 its upper ends are connected with fin 5 by pitman shaft knot 6, its lower end is connected with movable rod 14 by connecting rod hook 8, this movable rod 14 by whole to slip-knot 13, posture adjustment slip-knot 12, fixedly arbor wheel 11 and handle 10 formation manual control mechanisms.
Fin angle of attack setting range in the present embodiment is 4 °～15 °.
Be provided with the honeycomb screen of being made up of erect and parallel current plate 15 in the present embodiment between fan 3 and the girdle wing group, this honeycomb screen is made up of 0～10 current plate.
The combination of the fan 3-girdle wing can be a single-stage in the present embodiment, also can be multistage, 1～5 grade of scope.Fan 3 radiuses are 0.5～2.5m, and fan 3 blades are 2～30.
Fin angle of attack regulating mechanism described in the utility model can also be the mechanical control mechanism of electronic control mechanism, servo-control mechanism or alternate manner.
Below sketch principle of design of the present utility model:
The vertical lift-off device of no rotor described in the utility model belongs to low aspect ratio person, in order to reduce induced drag, and prevent that air-flow from escaping both sides to the left and right, and hold up two baffle plates 4, fan 3, the girdle wing are held in it, constitute upper and lower ventilative " half wind-tunnel ", every winglet sheet 5 two ends are sticking with fine and close fine hair, with form dynamically airtightly in " half wind-tunnel " when plate 4 Elastic Contact, airflow kinetic energy is P before the wing
Ow.air=1/2 ρ
0∮ U
3On the girdle wing, look lift F
L=C
L* 1/2 ρ
0S
WU
2, can consume a part of kinetic energy in the girdle wing, the air-flow rate of departure can decrease, approximately
So the air-flow effective value that acts on the girdle wing is about U
Ef=0.918U, the actual lift value is F
L.sure=0.42C
Lρ
0S
WU
2, system quality factor Q
0=0.84C
LS
W/ ∮ U.
Suitably select C
L, S
W, principal parameters such as ∮, U, just can realize the target of takeoff gross weight/driving engine gross horsepower 〉=6Kgf/KW.
As seen, improve S
W/ ∮ or reduction U then can improve Q
0So available multistage half construction of wind tunnel is distributed in power on several fans, lift is provided by several groups of girdle wings.In this system, axle adopts hollow shaft, universal knot nylon; Axle and girdle wing combination carbon fiber composite material; Flabellum also adopts carbon fiber composite material.
Practical flight: vertically go up to the air the stage (1)---and fan 3 provides wind regime, girdle wing C
L〉=16, when taking off, handle 10 is pushed into anteposition, each winglet sheet 5 bottom angles of attack of forming the girdle wing are transferred to α=15 °, this moment, girdle wing lift coefficient maximum was under driving engine 1 rated speed of rotation under the air-flow effect, obtain maximum lift/power rate, about 6～15kgf/KW realizes taking off vertically; (2) cruising level flight state---along with aircraft quickens in the horizontal direction, each winglet sheet 5 of handling girdle wing group gradually makes it gradually to the horizontal direction convergence, needs according to flying speed, the angle of attack α of each winglet sheet 5 adjusts in 15 °～4 ° scopes, when handle 10 is pulled to last position, each winglet sheet 5 angle of attack α=4 °, this moment the systemic resistance minimum, to realize high-performance cruise.Because each winglet sheet about in the of 5, front and back are in picturesque disorder, can make C
L/ C
D≈ 20 ± 5, and even higher, and this is the novel lift of a cover. and the thrust combination, product height of fine quality can be realized the vertical takeoff and landing of the zero speed of a ship or plane also realizing voyage R 〉=1600km.
Claims (8)
1, the vertical lift-off device of a kind of no rotor, comprise driving engine, change speed gear box, fan, it is characterized in that it also comprises two ends, the left and right sides air baffle that constitutes half construction of wind tunnel, described fan holds in it, the air flow line that fan bloats is provided with the girdle wing group mechanism that is made up of fin, each fin all is movably arranged on the air baffle of two ends, the left and right sides by its end axle, and each fin is arranged to low by height along air flow line, and girdle wing flock mating is equipped with fin angle of attack regulating mechanism.
2, the vertical lift-off device of no rotor according to claim 1 is characterized in that each girdle wing group is made up of 1～8 fin.
3, the vertical lift-off device of no rotor according to claim 1, it is characterized in that this fin angle of attack regulating mechanism is a manual link mechanism, the movable rod of this connecting rod mechanism and posture adjustment connecting rod are located by slide rail, its upper end of this posture adjustment connecting rod is connected with fin by the pitman shaft knot, its lower end is connected with movable rod by connecting rod hook, and this movable rod is by putting in order to slip-knot, posture adjustment slip-knot, fixedly arbor wheel and handle formation manual control mechanism.
4, according to claim 1 or the vertical lift-off device of 3 described no rotors, it is characterized in that 4 °～15 ° of fin angle of attack setting ranges.
5, the vertical lift-off device of no rotor according to claim 1 is characterized in that being provided with the honeycomb screen of being made up of erect and parallel current plate between fan and the girdle wing group.
6, do not have the vertical lift-off device of rotor according to claim 1 or 5, it is characterized in that honeycomb screen is made up of 0～10 current plate.
7, the vertical lift-off device of no rotor according to claim 1 is characterized in that fan-girdle wing combination can be a single-stage, also can be multistage, 1～5 grade of scope.
8, the vertical lift-off device of no rotor according to claim 1 is characterized in that the fan radius is 0.5～2.5m, and fan blade is 2～30.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200320128091 CN2714420Y (en) | 2003-12-18 | 2003-12-18 | Vertically ascending device without rotary wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200320128091 CN2714420Y (en) | 2003-12-18 | 2003-12-18 | Vertically ascending device without rotary wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2714420Y true CN2714420Y (en) | 2005-08-03 |
Family
ID=34866560
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200320128091 Expired - Fee Related CN2714420Y (en) | 2003-12-18 | 2003-12-18 | Vertically ascending device without rotary wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2714420Y (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102120490A (en) * | 2010-01-11 | 2011-07-13 | 刘跃东 | Wind tunnel type aircraft |
| CN102642450A (en) * | 2011-02-22 | 2012-08-22 | 刘跃东 | Wind tunnel type hovercar |
| CN104129500A (en) * | 2014-07-02 | 2014-11-05 | 张力 | Fixed-wing-type vertical rising and landing flight method |
-
2003
- 2003-12-18 CN CN 200320128091 patent/CN2714420Y/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102120490A (en) * | 2010-01-11 | 2011-07-13 | 刘跃东 | Wind tunnel type aircraft |
| CN102642450A (en) * | 2011-02-22 | 2012-08-22 | 刘跃东 | Wind tunnel type hovercar |
| CN104129500A (en) * | 2014-07-02 | 2014-11-05 | 张力 | Fixed-wing-type vertical rising and landing flight method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |