CN205311891U - Two anti wind suddenly that vert increase steady bendable flap aircraft - Google Patents
Two anti wind suddenly that vert increase steady bendable flap aircraft Download PDFInfo
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- CN205311891U CN205311891U CN201521017964.3U CN201521017964U CN205311891U CN 205311891 U CN205311891 U CN 205311891U CN 201521017964 U CN201521017964 U CN 201521017964U CN 205311891 U CN205311891 U CN 205311891U
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Abstract
The utility model relates to a two anti wind suddenly that vert increase steady bendable flap aircraft, include: the aircraft body to and locate undercarriage on the aircraft body, vertical tail, and tilting wing, characterized in that: the tilting wing includes the main wing roof beam, locate inner wing on the main wing roof beam, and be connected with the inner wing and can the buckle outer wing of dismantlement through the elasticity hinge, install first airscrew engine and second airscrew engine respectively on the main wing roof beam that lies in aircraft body both sides, this aircraft still includes the horizontal tail of verting, and the horizontal tail of verting includes the horizontal tail roof beam, locate tailplane on the horizontal tail roof beam, link to each other and lie in the connecting rod of vertical tail both sides respectively and install the third airscrew engine in connecting rod one end with the horizontal tail roof beam is fixed, above -mentioned first airscrew engine, second airscrew engine and third airscrew engine constitute three 3 canard configurations, the tilting wing with the horizontal tail of verting constitutes two structures of verting.
Description
Technical field
The utility model relates to vehicle technology field, especially relates to a kind of two anti-prominent wind that verts and increases steady bent rotor aircraft.
Background technology
Aircraft especially without man-machine in recent years along with the fast development of science and technology and the continuous increase of all kinds of specific demand, start to be widely used.
But, current existing without man-machine can realize wing bending in flight course and realize that empennage verts actually rare. Confirming after deliberation, reducing prominent wind bending moment and have very big help to without man-machine flight stability, the unmanned tail wing verts and is very beneficial for overall coordination performance.
In order to solve the problem and realize target, two anti-prominent wind that vert that this case contriver has invented a kind of compact construction increase steady bent rotor aircraft, utilize elasticity hinge arrangement to achieve without man-machine outer wing in the prominent wind bending moment masterpiece used time, it is possible to bending. Meanwhile, also achieve the arbitrarily angled of empennage to vert.
Practical novel content
The utility model object is to provide a kind of two anti-wind of dashing forward that vert scientific and reasonable for structure, that control is accurate, smoothness of verting, anti-prominent wind energy power are strong to increase steady bent rotor aircrafts.
The technical problem that the utility model solves realizes by the following technical solutions:
Two anti-prominent wind that verts increases steady bent rotor aircraft, comprise: aircraft body, and the landing gear being located on described aircraft body, vertical fin and the wing that verts, it is characterised in that: described in vert wing comprise through described aircraft body and the first actuator that can be placed in this body drive the main wing beam rotated, the inner wing being located on described main wing beam and be connected with described inner wing by elasticity hinge and the outer wing of bent dismounting;
It is being positioned on the described main wing beam of described aircraft body both sides to be separately installed with the first water screw engine and the 2nd water screw engine;
This aircraft also comprises one and verts horizontal tail, described in vert horizontal tail comprise through described vertical fin and the 2nd actuator that can be placed in this vertical fin drive the horizontal tail beam rotated, the tailplane being located on described horizontal tail beam and described horizontal tail beam are fixedly linked and lay respectively at the connecting rod of described vertical fin both sides and be arranged on the 3rd water screw engine of described connecting rod one end;
Above-mentioned first water screw engine, the 2nd water screw engine and the 3rd water screw engine form three 3 duck formula layouts, described in vert wing and described horizontal tail of verting forms two structure of verting.
Described in one or more, the bottom surface of described inner wing is fixed in one end of elasticity hinge, the other end is fixed on the bottom surface of described outer wing, and then make described outer wing realize bending downward or upward under the bending moment force effect by rising windage or decline windage, wherein, the maximum degree upwards bent is determined by the peak torque of described elasticity hinge.
Also it is provided with to impel the 3rd actuator that described outer wing initiatively bends in described aircraft body or on described inner wing, the bottom surface of described outer wing is fixed in one end of a kind of rope, the other end is fixed on the output revolving shaft of described 3rd actuator, described rope can be crispaturaed by described output revolving shaft, and then pull described outer wing to bend to described aircraft body, it is achieved passing through smoothly of narrow space.
The support also being provided with to set up described main wing beam in described aircraft body, also offers to place the card groove of described main wing beam or perforation and on the bracket in order to limit the limited block that described main wing beam is subjected to displacement.
In described aircraft body, also it is provided with the protective casing establishing described first actuator in order to cover, described protective casing is also offered the heat radiation hole in order to heat radiation.
Described inner wing is also provided with the flaperon can assisted and handle attitude of flight vehicle.
Described vertical fin is also equipped with the vertical rudder face can assisted and handle aircraft and turn to.
One end of a kind of diagonal brace bar is connected with described inner wing by bearing, and the other end is then connected with described landing gear.
A kind of intelligent control device also it is provided with in described aircraft body, described intelligent control device is connected by communication with described first actuator and the 2nd actuator respectively, and control described first actuator and the 2nd actuator can be stopped at any corner postiton, and then vert described in causing wing and described in horizontal tail of verting rotate to arbitrary combination angle.
The useful effect that the utility model has is: outer wing can passive bending under the effect of prominent wind bending moment power, it is possible to initiatively bending under power of the crispaturaing effect of the 3rd actuator, can realize anti-wind and increase and surely can pass through smoothly by narrow space again; Empennage realizes arbitrarily angled verting or stopping under the effect of the 2nd actuator, it is achieved that the total tune of aircraft and functional diversity.
Accompanying drawing explanation
In order to be illustrated more clearly in the utility model embodiment or technical scheme of the prior art, it is briefly described to the accompanying drawing used required in embodiment or description of the prior art below.
Fig. 1 is one-piece construction schematic diagram of the present utility model;
Fig. 2 is outer wing 43 initiatively bending structure schematic diagram in the utility model;
Fig. 3 is the structural representation of main wing beam 41 and support 6 in the utility model.
Embodiment
In order to the utility model is realized technique means, creation characteristic, reach object and effect is easy to understand, below in conjunction with specific embodiment, set forth the utility model further.
Steady bent rotor aircraft is increased with reference to the two anti-prominent wind that vert shown in Fig. 1,2,3, comprise aircraft body 1, in the bottom of aircraft body 1, landing gear 2 is installed, afterbody at aircraft body 1 is provided with and is perpendicular to aircraft body 1 and forms the vertical fin 3 of integrated structure with this body 1, is also provided with the vertical rudder face 31 can assisted and handle aircraft and turn on this vertical fin 3.
Also being provided with in the both sides of aircraft body 1 can at the arbitrarily angled wing 4 that verts verted and stop. This wing 4 that verts comprises main wing beam 41, be arranged on main wing beam 41 inner wing 42 and being connected with inner wing 42 by elasticity hinge 5 and the outer wing 43 of bent dismounting;
Wherein, main wing beam 41 is through aircraft body 1, and its two ends are in the both sides of aircraft body 1 respectively, and two inner wings 42 are separately fixed at the two ends of main wing beam 41 and are positioned at the both sides of aircraft body 1. Inner wing 42 is also provided with the flaperon 44 can assisted and handle attitude of flight vehicle. It is equipped with one or more elasticity hinges 5 in every side of aircraft body 1, the bottom surface of inner wing 42 is fixed in one end of each elasticity hinge 5, the other end is fixed on the bottom surface of outer wing 43, and then make outer wing 43 when being subject to the bending moment force effect of rising windage or decline windage, realizing bending downward or upward, the maximum degree that outer wing 43 upwards bends is determined by the peak torque of elasticity hinge 5;
The main wing beam 41 being positioned at aircraft body 1 both sides is separately installed with the first water screw engine 45 and the 2nd water screw engine 46, in order to promote the motion of aircraft body 1.
First actuator 101 is also installed in aircraft body 1, in order to drive the rotation of main wing beam 41, and then drives the synchronous axial system of inner wing 42, outer wing 43, flaperon 44, first water screw engine 45, the 2nd water screw engine 46 and elasticity hinge 5. Wherein, main wing beam 41 is directly set up on aircraft body 1 by bearing, or the support 6 being provided with to set up main wing beam 41 as shown in Figure 3 in aircraft body 1, offers to place card groove or the perforation 61 and in order to limit the limited block 62 that main wing beam 41 is subjected to displacement of main wing beam 41 on the frame 6;
Also it is provided with the protective casing 7 establishing the first actuator 101 in order to cover in the inside of aircraft body 1, protective casing 7 is also offered the heat radiation hole in order to heat radiation.
Afterbody at aircraft body 1 is also provided with one and verts horizontal tail 8, and this horizontal tail 8 of verting comprises the horizontal tail beam 81 through vertical fin 3, the tailplane 82 that is arranged on horizontal tail beam 81 and horizontal tail beam 81 are fixedly linked and lay respectively at the connecting rod 83 of vertical fin 3 both sides and be arranged on the 3rd water screw engine 84 of connecting rod 83 one end;
Wherein, horizontal tail beam 81 is directly set up on vertical fin 3, is also provided with the 2nd actuator 102 in vertical fin 3, in order to drive the rotation of horizontal tail beam 81, and then drives the synchronous axial system of tailplane 82, connecting rod 83 and the 3rd water screw engine 84.
Above-mentioned first water screw engine 45, the 2nd water screw engine 46 and the 3rd water screw engine 84 form three 3 duck formula layouts, and the wing 4 that verts forms two structure of verting with horizontal tail 8 of verting.
As shown in Figure 2, in the inside of aircraft body 1 or the 3rd actuator 103 also being provided with to impel outer wing 43 active bending on inner wing 42. The bottom surface of outer wing 43 is fixed in one end of a kind of rope 9, the other end is fixed on the output revolving shaft of the 3rd actuator 103, rope 9 can be crispaturaed by the output revolving shaft of the 3rd actuator 103, and then pulls outer wing 43 to bend to aircraft body 1 direction, it is achieved passing through smoothly of narrow space.
A kind of intelligent control device 10 is also installed in the inside of aircraft body 1, this intelligent control device 10 is connected by communication with the first actuator 101, the 2nd actuator 102 and the 3rd actuator 103 respectively, and control above-mentioned actuator and can stop at any corner postiton, and then cause vert wing 4 and horizontal tail 8 of verting rotate to arbitrary combination angle and control outer wing 43 in office what is the need for be bent time, it is achieved initiatively bending.
One end of a kind of diagonal brace bar 11 is connected with inner wing 42 by bearing, and the other end is then connected with landing gear 2, firmly integrally-built to realize.
Aircraft provided by the utility model, its outer wing 43 can passive bending under the effect of prominent wind bending moment power, it is possible to initiatively bending under power of the crispaturaing effect of the 3rd actuator 103, can realize anti-wind and increase and surely can pass through smoothly by narrow space again; Empennage realizes arbitrarily angled verting or stopping under the effect of the 2nd actuator 102, it is achieved that the total tune of aircraft and functional diversity.
More than show and describe ultimate principle of the present utility model and main characteristic sum advantage of the present utility model. The technician of the industry should understand; the utility model is not restricted to the described embodiments; what describe in above-described embodiment and specification sheets just illustrates principle of the present utility model; under the prerequisite not departing from the utility model spirit and scope; the utility model also has various changes and modifications, and these changes and improvements all fall within the scope of claimed the utility model. The claimed scope of the utility model is defined by appending claims and equivalent thereof.
Claims (9)
1. the anti-prominent wind that pair verts increases steady bent rotor aircraft, comprise aircraft body, and the landing gear being located on described aircraft body, vertical fin and the wing that verts, it is characterised in that: described in vert wing comprise through described aircraft body and the first actuator that can be placed in this body drive the main wing beam rotated, the inner wing being located on described main wing beam and be connected with described inner wing by elasticity hinge and the outer wing of bent dismounting;
It is being positioned on the described main wing beam of described aircraft body both sides to be separately installed with the first water screw engine and the 2nd water screw engine;
This aircraft also comprises one and verts horizontal tail, described in vert horizontal tail comprise through described vertical fin and the 2nd actuator that can be placed in this vertical fin drive the horizontal tail beam rotated, the tailplane being located on described horizontal tail beam and described horizontal tail beam are fixedly linked and lay respectively at the connecting rod of described vertical fin both sides and be arranged on the 3rd water screw engine of described connecting rod one end;
Above-mentioned first water screw engine, the 2nd water screw engine and the 3rd water screw engine form three 3 duck formula layouts, described in vert wing and described horizontal tail of verting forms two structure of verting.
2. two anti-prominent wind that verts according to claim 1 increases steady bent rotor aircraft, it is characterized in that: described in one or more, the bottom surface of described inner wing is fixed in one end of elasticity hinge, the other end is fixed on the bottom surface of described outer wing, and then make described outer wing realize bending downward or upward under the bending moment force effect by rising windage or decline windage, wherein, the maximum degree upwards bent is determined by the peak torque of described elasticity hinge.
3. two anti-prominent wind that verts according to claim 1 increases steady bent rotor aircraft, it is characterised in that: the 3rd actuator also being provided with to impel the active bending of described outer wing in described aircraft body or on described inner wing;
The bottom surface of described outer wing is fixed in one end of a kind of rope, the other end is fixed on the output revolving shaft of described 3rd actuator, described rope can be crispaturaed by described output revolving shaft, and then pulls described outer wing to bend to described aircraft body, it is achieved passing through smoothly of narrow space.
4. two anti-prominent wind that verts according to claim 1 increases steady bent rotor aircraft, it is characterized in that: the support also being provided with to set up described main wing beam in described aircraft body, also offer to place the card groove of described main wing beam or perforation on the bracket and in order to limit the limited block that described main wing beam is subjected to displacement.
5. two anti-prominent wind that verts according to claim 1 increases steady bent rotor aircraft, it is characterized in that: in described aircraft body, be also provided with the protective casing establishing described first actuator in order to cover, described protective casing is also offered the heat radiation hole in order to heat radiation.
6. two anti-prominent wind that verts according to claim 1 increases steady bent rotor aircraft, it is characterised in that: on described inner wing, also it is provided with the flaperon can assisted and handle attitude of flight vehicle.
7. two anti-prominent wind that verts according to claim 1 increases steady bent rotor aircraft, it is characterised in that: the vertical rudder face can assisted and handle aircraft and turn to also is housed on described vertical fin.
8. two anti-prominent wind that verts according to claim 1 increases steady bent rotor aircraft, it is characterised in that: one end of a kind of diagonal brace bar is connected with described inner wing by bearing, and the other end is then connected with described landing gear.
9. two anti-prominent wind that verts according to claim 1 increases steady bent rotor aircraft, it is characterized in that: in described aircraft body, be also provided with a kind of intelligent control device, described intelligent control device is connected by communication with described first actuator and the 2nd actuator respectively, and control described first actuator and the 2nd actuator can be stopped at any corner postiton, and then vert described in causing wing and described in horizontal tail of verting rotate to arbitrary combination angle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521017964.3U CN205311891U (en) | 2015-12-09 | 2015-12-09 | Two anti wind suddenly that vert increase steady bendable flap aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521017964.3U CN205311891U (en) | 2015-12-09 | 2015-12-09 | Two anti wind suddenly that vert increase steady bendable flap aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN205311891U true CN205311891U (en) | 2016-06-15 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201521017964.3U Expired - Fee Related CN205311891U (en) | 2015-12-09 | 2015-12-09 | Two anti wind suddenly that vert increase steady bendable flap aircraft |
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| CN (1) | CN205311891U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107187578A (en) * | 2017-05-18 | 2017-09-22 | 钟江汉 | A kind of Fixed Wing AirVehicle utilizes the wing structure for being vortexed lift-rising |
| WO2018040312A1 (en) * | 2016-08-31 | 2018-03-08 | 数字鹰科技盐城有限公司 | Unmanned aerial vehicle of folding wing-type |
| CN108016591A (en) * | 2017-12-30 | 2018-05-11 | 镇江同舟螺旋桨有限公司 | A kind of ending flap shape propeller blade ending styling apparatus |
| CN112550668A (en) * | 2021-03-01 | 2021-03-26 | 北京清航紫荆装备科技有限公司 | Cross double-rotor helicopter and horizontal tail control system |
-
2015
- 2015-12-09 CN CN201521017964.3U patent/CN205311891U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018040312A1 (en) * | 2016-08-31 | 2018-03-08 | 数字鹰科技盐城有限公司 | Unmanned aerial vehicle of folding wing-type |
| CN107187578A (en) * | 2017-05-18 | 2017-09-22 | 钟江汉 | A kind of Fixed Wing AirVehicle utilizes the wing structure for being vortexed lift-rising |
| CN108016591A (en) * | 2017-12-30 | 2018-05-11 | 镇江同舟螺旋桨有限公司 | A kind of ending flap shape propeller blade ending styling apparatus |
| CN112550668A (en) * | 2021-03-01 | 2021-03-26 | 北京清航紫荆装备科技有限公司 | Cross double-rotor helicopter and horizontal tail control system |
| CN112550668B (en) * | 2021-03-01 | 2021-06-15 | 北京清航紫荆装备科技有限公司 | Cross double-rotor helicopter and horizontal tail control system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160615 Termination date: 20171209 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |