CN205131654U - Compound aircraft - Google Patents
Compound aircraft Download PDFInfo
- Publication number
- CN205131654U CN205131654U CN201520852942.2U CN201520852942U CN205131654U CN 205131654 U CN205131654 U CN 205131654U CN 201520852942 U CN201520852942 U CN 201520852942U CN 205131654 U CN205131654 U CN 205131654U
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- wing
- rotor
- fuselage
- composite wing
- compound
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Abstract
The utility model provides a compound aircraft, belongs to aircraft technical field, including fuselage, left composite wing, right composite wing, compound fin and undercarriage. Be furnished with control system and airborne equipment in the fuselage. Compound fin is located the afterbody of fuselage, and compound fin includes vertical tail, left power -driven propeller and right power -driven propeller. Power -driven propeller is the same with right power -driven propeller structure on a left side, turns to on the contrary, and symmetrical arrangement is both sides in about vertical tail. The undercarriage adopts wheel -type structure or skid and wheeled integrated configuration. Composite wing is the same with right composite wing structure on a left side, and their symmetries are installed in the left and right sides of fuselage. Be furnished with two or three rotor in the composite wing of a left side, every rotor is all by an engine driven. Left side composite wing's fin includes fixed anterior fin and can wind the rear portion fin that blade axis deflected. All rotors all are located blade axis's below. It is little that compound aircraft takes off and land the place, can vertical lift. The lift that produces is great, safety and stability and flexible.
Description
Technical field
A kind of compound type aircraft, belongs to vehicle technology field, particularly relates to a kind of compound type aircraft.
Background technology
Traditional taking off and land needs comparatively long runway, can not vertical takeoff and landing, also inconvenient Ultra-Low Speed or hovering flight, and comparatively short take-off and landing is also very difficult.Traditional helicopter energy consumption is large, and efficiency is low, and safety and stability is not high.
Summary of the invention
The object of the invention is the above-mentioned deficiency overcoming traditional aircraft and helicopter, inventing a kind of short take-off and landing that facilitates even can the compound type aircraft of efficient safety and stability of vertical takeoff and landing.
A kind of compound type aircraft, comprises fuselage, left composite wing, right composite wing, compound empennage and alighting gear.Control system and airborne equipment is furnished with in fuselage.Left composite wing is identical with right composite wing structure, and their symmetries are installed on the left and right sides of fuselage.Compound empennage is positioned at the afterbody of fuselage, and compound empennage comprises vertical tail, left electric propeller and right electric propeller.Left electric propeller is identical with right electric screw paddle structure, turns to contrary, is symmetrically arranged in the right and left of vertical tail.Left electric propeller comprises screw propeller and motor, and motor is by lithium battery power supply.Vertical tail plays vertical stabilator and yaw rudder, and the effect of left electric propeller and right electric propeller lifting rudder is also used for adjusting flight attitude.Alighting gear adopts wheeled construction or sled and wheeled unitized construction.
The structure of left composite wing is: left composite wing comprises front flaps, rear plastic, wing axle, outer rotor, interior rotor, outer driving engine, intrinsic motivation and support.Front flaps is fixed on the left side of fuselage.Wing axle horizontal arrangement, the left end of wing axle is connected with front flaps, and the right-hand member of wing axle is fixed on fuselage, and wing axle is placed in the trailing edge place of front flaps.The leading edge of front flaps is higher than the trailing edge of front flaps, and the angle of front flaps and horizontal surface is between 8 °-30 °.The front end of rear plastic is connected with wing axle, and rear plastic can deflect up and down around wing axle.Relative level face, the maximum angle that rear plastic upward deflects is no more than 35 °, and the maximum angle that rear plastic deflects down is no more than 30 °.Interior rotor near fuselage installation, install away from fuselage by outer rotor.The diameter of outer rotor is not more than the diameter of interior rotor.Outer driving engine and intrinsic motivation are arranged on the support that is all connected with fuselage and wing axle, and outer driving engine provides power for outer rotor, and intrinsic motivation provides power for interior rotor.The line of the centre of gration of interior rotor and the centre of gration of outer rotor is in the below of wing axle, and this line is parallel with wing axle.The plane of rotation of outer rotor and the plane of rotation of interior rotor coplanar.The plane of rotation of interior rotor tilts slightly toward front lower place or is horizontal, and the angle of the plane of rotation of interior rotor and the forward downward of horizontal surface is not more than 8 °.Shortest distance between the rearmost end of the wing tip turning circumference of interior rotor and rear plastic is greater than 8mm.The chord length of rear plastic is equal to or slightly greater than the radius of rotation of interior rotor.The chord length of front flaps is equal to or slightly greater than the radius of rotation of interior rotor.The length of left composite wing is greater than the diameter of interior rotor and the diameter sum of outer rotor.
Rotor in compound type aircraft of the present invention and the quantity of driving engine also have the form of six covers except four covers: three rotors are housed and supporting three driving engines in left composite wing, these three rotors are arranged in a linear in the below of the wing axle of left composite wing, and during this form, the length of left composite wing is greater than the diameter sum of three rotors; Right composite wing is identical with the structure of left composite wing, and their symmetries are installed on the left and right sides of fuselage.
In order to improve manoevreability, will leave a blank in the middle of the canned paragraph of the vertical tail of described compound type aircraft, longitudinally vertically arranging the electronic vertical screw propeller of installation one in this position of leaving a blank, facilitate described aircraft to hover like this or low speed time wide-angle turn to.
The principle of work of a kind of compound type of this invention aircraft is: as the rear plastic of the rear plastic of left composite wing and right composite wing is all deflected downwards to extreme lower position, and alighting gear is adjusted to wheeled state, start all driving engines, drive corresponding rotor wing rotation respectively, described aircraft can realize rolling start; As the rear plastic of the rear plastic of left composite wing and right composite wing is all deflected upward into extreme higher position, described aircraft can realize taking off vertically.Adjust the deflection angle of the rear plastic of left composite wing and the rear plastic of right composite wing and direction and can change the aerodynamic direction and size that described aircraft produces, also can be changed aerodynamic size and Orientation of described aircraft by the rotating speed adjusting each rotor.Pitching and the course of described aircraft is controlled by compound empennage.Compare with traditional aircraft, the landing site of compound type aircraft requirements of the present invention is little, and can vertical lift.Compare with traditional helicopter, compound type aircraft of the present invention is due to the existence of left composite wing and right composite wing, the lift that described aircraft produces is larger, if run out of steam longer distance of also gliding, more time docking facility can be striven for or find safe landing point, safer like this; Because the rotor of left composite wing and the corresponding rotor of right composite wing turn on the contrary, rotating torque can be offset, flight stability and control simple; Because all rotors are all in the below of fin, the flow field of fin upper and lower surface can be improved during rotor rotational, increase downwash flow, delay the burbling of the upper surface of fin, raise the efficiency, lift coefficient is increased greatly, due to the existence of multiple rotor and compound empennage, described aircraft maneuverability.
Accompanying drawing explanation
Fig. 1 is that schematic diagram is looked on a left side for a kind of compound type aircraft of the present invention; Fig. 2 is the schematic top plan view of Fig. 1; Fig. 3 is that schematic diagram is looked on a left side for the left composite wing be exaggerated, and Fig. 4 is the schematic top plan view of Fig. 3.
In figure, 1-fuselage, the left composite wing of 2-, the right composite wing of 3-, 4-vertical tail, the left electric propeller of 5-, the right electric propeller of 6-, 7-alighting gear; The component belonging to left composite wing 2 comprises: 21-front flaps, 22-rear plastic, 23-wing axle, the outer rotor of 24-, rotor in 25-, the outer driving engine of 26-, 27-intrinsic motivation, 28-support.
Detailed description of the invention
Now by reference to the accompanying drawings the present invention is illustrated: a kind of compound type aircraft, comprised fuselage 1, left composite wing 2, right composite wing 3, compound empennage and alighting gear 7.Control system and airborne equipment is furnished with in fuselage 1.Left composite wing 2 is identical with right composite wing 3 structure, and their symmetries are installed on the left and right sides of fuselage 1.Compound empennage is positioned at the afterbody of fuselage 1, and compound empennage comprises vertical tail 4, left electric propeller 5 and right electric propeller 6.Left electric propeller 5 is identical with right electric propeller 6 structure, and turn to contrary, on even keel is symmetrically arranged in the right and left of vertical tail 4.Left electric propeller 5 comprises screw propeller and motor, and motor is by lithium battery power supply.Vertical tail 4 plays vertical stabilator and yaw rudder, and the effect of left electric propeller 5 and right electric propeller 6 lifting rudder is also used for adjusting flight attitude.Alighting gear 7 adopts wheeled construction.The structure of left composite wing 2 is: left composite wing 2 comprises front flaps 21, rear plastic 22, wing axle 23, outer rotor 24, interior rotor 25, outer driving engine 26, intrinsic motivation 27 and support 28.Front flaps 21 is fixed on the left side of fuselage 1.Wing axle 23 horizontal arrangement, the left end of wing axle 23 is connected with front flaps 21, and the right-hand member of wing axle 23 is fixing on the fuselage 1, and wing axle 23 is placed in the trailing edge place of front flaps 21.The leading edge of front flaps 21 is higher than the trailing edge of front flaps 21, and front flaps 21 is 23 ° with the angle of horizontal surface.The front end of rear plastic 22 is connected with wing axle 23, and rear plastic 22 can deflect around wing axle about 23.Relative level face, the maximum angle that rear plastic 22 upward deflects is 25 °, and the maximum angle that rear plastic deflects down is 15 °.Interior rotor 25 to be installed and outer rotor 24 is installed away from fuselage 1 near fuselage 1.The diameter of outer rotor 24 is not more than the diameter of interior rotor 25.Outer driving engine 26 and intrinsic motivation 27 are arranged on the support 28 that is all connected with fuselage 1 and wing axle 23, and outer driving engine 26 provides power for outer rotor 24, and intrinsic motivation 27 provides power for interior rotor 25.The line of the centre of gration of interior rotor 25 and the centre of gration of outer rotor 24 is in immediately below wing axle 23, and this line is parallel with wing axle 23.The plane of rotation of outer rotor 24 and the plane of rotation of interior rotor 25 coplanar.The plane of rotation of interior rotor 25 is horizontal.Shortest distance between the rearmost end of the wing tip turning circumference of interior rotor 25 and rear plastic 22 is greater than 8mm.The chord length of rear plastic 22 is a bit larger tham the radius of rotation of interior rotor 25.The chord length of front flaps 21 is equal to or slightly greater than the radius of rotation of interior rotor 25.The length of left composite wing 2 is greater than the diameter of interior rotor 25 and the diameter sum of outer rotor 24.
Compound type aircraft of the present invention produces beneficial effect like this: as the rear plastic 22 of left composite wing 2 and the rear plastic of right composite wing 3 are all deflected downwards to extreme lower position, start all driving engines, drive corresponding rotor wing rotation respectively, described aircraft can realize rolling start; As the rear plastic 22 of left composite wing 2 and the rear plastic of right composite wing 3 are all deflected upward into extreme higher position, described aircraft can realize taking off vertically.Adjust the deflection angle of the rear plastic 22 of left composite wing 2 and the rear plastic of right composite wing 3 and direction and can change the aerodynamic direction and size that described aircraft produces, also can be changed aerodynamic size and Orientation of described aircraft by the rotating speed adjusting each rotor.Pitching and the course of described aircraft is controlled by compound empennage.Compare with traditional aircraft, the landing site of compound type aircraft requirements of the present invention is little, and can vertical lift.Compare with traditional helicopter, compound type aircraft of the present invention is due to the existence of left composite wing and right composite wing, the lift that described aircraft produces is larger, if run out of steam longer distance of also gliding, more time docking facility can be striven for or find safe landing point, safer like this; Because the rotor of left composite wing and the corresponding rotor of right composite wing turn on the contrary, rotating torque can be offset, flight stability and control simple; Because all rotors are all in the below of fin, the flow field of fin upper and lower surface can be improved during rotor rotational, increase downwash flow, delay the burbling of the upper surface of fin, raise the efficiency, lift coefficient is increased greatly, due to the existence of multiple rotor and compound empennage, described aircraft maneuverability.The rear plastic 22 of left composite wing 2 and the rear plastic of right composite wing 3 can also play wing flap and the aileron of traditional aircraft.Therefore described compound type aircraft maneuverability more.
Claims (7)
1. a compound type aircraft, is characterized in that: comprise fuselage (1), left composite wing (2), right composite wing (3), compound empennage and alighting gear (7); Fuselage is furnished with control system and airborne equipment in (1); Left composite wing (2) is identical with right composite wing (3) structure, and their symmetries are installed on the left and right sides of fuselage (1); Compound empennage is positioned at the afterbody of fuselage (1), and compound empennage comprises vertical tail (4), left electric propeller (5) and right electric propeller (6); Left electric propeller (5) is identical with right electric propeller (6) structure, and turn to contrary, on even keel is symmetrically arranged in the right and left of vertical tail (4); Left electric propeller (5) comprises screw propeller and motor; Vertical tail (4) plays vertical stabilator and yaw rudder, and the effect of left electric propeller (5) and right electric propeller (6) lifting rudder is also used for adjusting flight attitude; Alighting gear (7) adopts wheeled construction or sled and wheeled unitized construction; The structure of left composite wing (2) is: left composite wing (2) comprises front flaps (21), rear plastic (22), wing axle (23), outer rotor (24), interior rotor (25), outer driving engine (26), intrinsic motivation (27) and support (28); Front flaps (21) is fixed on the left side of fuselage (1); Wing axle (23) horizontal arrangement, the left end of wing axle (23) is connected with front flaps (21), and the right-hand member of wing axle (23) is fixed on fuselage (1), and wing axle (23) is placed in the trailing edge place of front flaps (21); The leading edge of front flaps (21) is higher than the trailing edge of front flaps (21), and the angle of front flaps (21) and horizontal surface is between 8 °-30 °; The front end of rear plastic (22) is connected with wing axle (23), and rear plastic (22) can deflect up and down around wing axle (23); Relative level face, the maximum angle that rear plastic (22) upward deflects is no more than 35 °, and the maximum angle that rear plastic (22) deflects down is no more than 30 °; Interior rotor (25) near fuselage (1) installation, install away from fuselage (1) by outer rotor (24); The diameter of outer rotor (24) is not more than the diameter of interior rotor (25); Outer driving engine (26) and intrinsic motivation (27) are arranged on the support (28) that is all connected with fuselage (1) and wing axle (23), and outer driving engine (26) provides power for outer rotor (24), and intrinsic motivation (27) provides power for interior rotor (25); The line of the centre of gration of interior rotor (25) and the centre of gration of outer rotor (24) is in the below of wing axle (23), and this line is parallel with wing axle (23); The plane of rotation of outer rotor (24) and the plane of rotation of interior rotor (25) coplanar; The plane of rotation of interior rotor (25) tilts slightly toward front lower place or is horizontal; Shortest distance between the rearmost end of the wing tip turning circumference of interior rotor (25) and rear plastic (22) is greater than 8mm; The chord length of rear plastic (22) is equal to or slightly greater than the radius of rotation of interior rotor (25); The chord length of front flaps (21) is equal to or slightly greater than the radius of rotation of interior rotor (25); The length of left composite wing (2) is greater than the diameter of interior rotor (25) and the diameter sum of outer rotor (24).
2. a kind of compound type aircraft according to claim 1, is characterized in that: the leading edge of front flaps (21) is higher than the trailing edge of front flaps (21), and front flaps (21) is 23 ° with the angle of horizontal surface.
3. a kind of compound type aircraft according to claim 1, is characterized in that: relative level face, and the maximum angle that rear plastic (22) upward deflects is 25 °, and the maximum angle that rear plastic (22) deflects down is 15 °.
4. a kind of compound type aircraft according to claim 1, is characterized in that: the line of the centre of gration of interior rotor (25) and the centre of gration of outer rotor (24) is in immediately below wing axle (23).
5. a kind of compound type aircraft according to claim 1 or 2 or 3 or 4, it is characterized in that: the quantity of rotor and driving engine also has the form of six covers except four covers: three rotors are housed and supporting three driving engines in left composite wing, these three rotors are arranged in a linear in the below of the wing axle of left composite wing, and during this form, the length of left composite wing is greater than the diameter sum of three rotors; Right composite wing is identical with the structure of left composite wing, and their symmetries are installed on the left and right sides of fuselage.
6. a kind of compound type aircraft according to claim 1 or 2 or 3 or 4, is characterized in that: the angle of the plane of rotation of interior rotor (25) and the forward downward of horizontal surface is not more than 8 °.
7. a kind of compound type aircraft according to claim 1 or 2 or 3 or 4, is characterized in that: leave a blank in the middle of the canned paragraph of vertical tail (4), and this position of leaving a blank longitudinally vertically is arranged and is installed with an electronic vertical screw propeller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520852942.2U CN205131654U (en) | 2015-10-30 | 2015-10-30 | Compound aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520852942.2U CN205131654U (en) | 2015-10-30 | 2015-10-30 | Compound aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205131654U true CN205131654U (en) | 2016-04-06 |
Family
ID=55617471
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520852942.2U Withdrawn - After Issue CN205131654U (en) | 2015-10-30 | 2015-10-30 | Compound aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205131654U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105217026A (en) * | 2015-10-30 | 2016-01-06 | 佛山市神风航空科技有限公司 | A kind of compound type aircraft |
| CN111532426A (en) * | 2020-04-22 | 2020-08-14 | 中国空气动力研究与发展中心 | Aircraft with V-shaped empennage and multiple rotors in vertical take-off and landing layout |
-
2015
- 2015-10-30 CN CN201520852942.2U patent/CN205131654U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105217026A (en) * | 2015-10-30 | 2016-01-06 | 佛山市神风航空科技有限公司 | A kind of compound type aircraft |
| CN111532426A (en) * | 2020-04-22 | 2020-08-14 | 中国空气动力研究与发展中心 | Aircraft with V-shaped empennage and multiple rotors in vertical take-off and landing layout |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20160406 Effective date of abandoning: 20171219 |
|
| AV01 | Patent right actively abandoned |