CN205098475U - Vertical take -off and landing aircraft - Google Patents
Vertical take -off and landing aircraft Download PDFInfo
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- CN205098475U CN205098475U CN201520896554.4U CN201520896554U CN205098475U CN 205098475 U CN205098475 U CN 205098475U CN 201520896554 U CN201520896554 U CN 201520896554U CN 205098475 U CN205098475 U CN 205098475U
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Abstract
The utility model relates to a flying device field, aim at provides a vertical take -off and landing aircraft, vertical take -off and landing aircraft, the reciprocating impact tunnel drilling machine comprises a machine body, the waist symmetry is equipped with two main wings, the afterbody is equipped with the fin, still includes two mechanisms of verting, two first motors, two first rotors, second motor and second rotors, fuselage head bilateral symmetry is equipped with two mechanisms of verting, it includes dead lever and third motor to vert the mechanism, the dead lever level sets up. The utility model has the advantages of the fore -body is equipped with first rotor, and the fuselage rear portion is equipped with the second rotor, and when the aircraft took off, first rotor and second rotor produced ascending lift jointly for the aircraft can not have vertical take -off under the condition of runway, and the mechanism of verting when aircraft level flight drives first rotor and rotates, makes first rotor produce prorsad pulling force with higher efficiency.
Description
Technical field
The utility model relates to flight instruments field, particularly a kind of vertically taking off and landing flyer.
Background technology
General fixed-wing formula aircraft has that voyage is far away, speed is fast, efficiency advantages of higher, but in landing process, do not break away from the dependence to airport.And though helicopter can carry out vertical takeoff and landing (VTOL) without airport, general helicopter flight speed is comparatively slow, voyage is short, efficiency is low.Although present occurred tilting rotor formula aircraft can overcome above-mentioned deficiency of determining wing aircraft and helicopter further, but the rotor due to this class vertically taking off and landing flyer verts, system is mostly distributed on wing, the air-flow that screw propeller produces is blocked by wing mostly, loss of lift is serious, and efficiency is lower.
Utility model content
The purpose of this utility model is to overcome above-mentioned defect, provides the vertically taking off and landing flyer that a kind of efficiency low in energy consumption is high.
In order to solve the problems of the technologies described above, the technical solution adopted in the utility model is:
A kind of vertically taking off and landing flyer, comprise fuselage, described waist is arranged with two main wings, described afterbody is provided with empennage, also comprise two inclining rotary mechanisms, two the first motors, two the first rotors, second motor and the second rotor, described fuselage head bilateral symmetry is provided with two inclining rotary mechanisms, described inclining rotary mechanism comprises fixed link and the 3rd motor, described fixed link is horizontally disposed with, described 3rd motor is arranged on fuselage, described fixed link one end is coaxially connected with the output shaft of the 3rd motor, the described fixed link other end is provided with the first motor, the output shaft of described first motor is mutually vertical with fixed link, described first rotor is arranged on the output shaft of the first motor, described afterbody is provided with the second motor, the output shaft setting direction of described second motor straight down, described second rotor is arranged on the output shaft of described second motor.
Further, the length of described inclining rotary mechanism is greater than the radius of rotation of the first rotor, and described inclining rotary mechanism to the distance of main wing is greater than the radius of rotation of the first rotor.
Further, described second rotor comprises oar pad, lower oar pad, two bolts and two screw propellers, described upper oar pad and lower oar pad are interfixed by bolt, described two screw propellers are arranged on two bolts respectively, described screw propeller is with the bolt of correspondence for rotating shaft is rotatably installed, and described upper oar pad is connected with the output shaft of the second motor.
Further, also comprise wheel undercarriage, described wheel undercarriage is arranged at fuselage bottom.
The beneficial effects of the utility model are: forebody is provided with the first rotor, fuselage afterbody is provided with the second rotor, when aircraft takeoff, first rotor and the second rotor produce lift upwards jointly, aircraft can be taken off vertically when not having runway, when aircraft horizontal flight, inclining rotary mechanism drives the first rotor rotational, the first rotor is made to produce pulling force forward with higher efficiency, simultaneously because the first rotor is arranged on aircraft Handpiece Location, the air-flow that screw propeller produces can not be blocked by wing, loss of lift is less, and efficiency significantly improves.
Accompanying drawing explanation
Fig. 1 is the block diagram of the utility model embodiment vertically taking off and landing flyer;
Fig. 2 is the birds-eye view of the utility model embodiment vertically taking off and landing flyer;
Fig. 3 is the exploded view of the utility model embodiment second rotor.
Label declaration:
1, fuselage; 2, main wing; 3, inclining rotary mechanism; 4, the first motor; 5, the first rotor; 6, the second motor; 7, the second rotor; 8, wheel undercarriage; 71, upper oar pad; 72, lower oar pad; 73, bolt; 74, screw propeller.
Detailed description of the invention
By describing technology contents of the present utility model, structural attitude in detail, realized object and effect, accompanying drawing is coordinated to be explained in detail below in conjunction with embodiment.
The design of the utility model most critical is: the first rotor is connected with fuselage by inclining rotary mechanism, the conversion of lifting power and onward impulse can be realized, aircraft can vertical takeoff and landing (VTOL), simultaneously because the first rotor is arranged on aircraft Handpiece Location, the air-flow that screw propeller produces can not be blocked by wing, loss of lift is less, and efficiency significantly improves.
Refer to shown in Fig. 1 to Fig. 3, the vertically taking off and landing flyer of the present embodiment, comprise fuselage 1, two main wings 2 are arranged with in the middle part of described fuselage 1, described fuselage 1 afterbody is provided with empennage, also comprise two inclining rotary mechanisms 3, two the first motors 4, two the first rotors 5, second motor 6 and the second rotor 7, described fuselage 1 head bilateral symmetry is provided with two inclining rotary mechanisms 3, described inclining rotary mechanism comprises fixed link and the 3rd motor, described fixed link is horizontally disposed with, described 3rd motor is installed on the fuselage 1, described fixed link one end is coaxially connected with the output shaft of the 3rd motor, the described fixed link other end is provided with the first motor 4, the output shaft of described first motor 4 is mutually vertical with fixed link, described first rotor 5 is arranged on the output shaft of the first motor 4, described fuselage 1 afterbody is provided with the second motor 6, the output shaft setting direction of described second motor 6 straight down, described second rotor 7 is arranged on the output shaft of described second motor 6.
Working process of the present utility model is: during startup, the output shaft of the first motor 4 is towards downwards, start the first motor 4 and the second motor 6 simultaneously, aircraft vertical takes off, when aircraft rises to certain altitude, inclining rotary mechanism 3 drives the first motor 4 to rotate to level attitude gradually, second motor 6 rotating speed drops to gradually and stops operating, and aircraft is converted to horizontal flight pattern.
From foregoing description, the beneficial effects of the utility model are: fuselage 1 front portion is provided with the first rotor 5, fuselage 1 rear portion is provided with the second rotor 7, when aircraft takeoff, first rotor 5 and the second rotor 7 produce lift upwards jointly, aircraft can be taken off vertically when not having runway, when aircraft horizontal flight, inclining rotary mechanism 3 drives the first rotor 5 to rotate, the first rotor 5 is made to produce pulling force forward with higher efficiency, simultaneously because the first rotor 5 is arranged on aircraft Handpiece Location, the air-flow that screw propeller 74 produces can not be blocked by wing, loss of lift is less, efficiency significantly improves.
Further, the length of described inclining rotary mechanism 3 is greater than the radius of rotation of the first rotor 5, and the distance of described inclining rotary mechanism 3 to main wing 2 is greater than the radius of rotation of the first rotor 5.
Seen from the above description, the length of inclining rotary mechanism 3 is greater than the radius of rotation of the first rotor 5, and the distance of described inclining rotary mechanism 3 to main wing 2 is greater than the radius of rotation of the first rotor 5, can prevent the first rotor 5 from colliding with fuselage 1 or main wing 2.
Further, described second rotor 7 comprises oar pad 71, lower oar pad 72, two bolts 73 and two screw propellers 74, described upper oar pad 71 and lower oar pad 72 are interfixed by bolt 73, described two screw propellers 74 are arranged on two bolts 73 respectively, described screw propeller 74 is rotatably installed for rotating shaft with the bolt 73 of correspondence, and described upper oar pad 71 is connected with the output shaft of the second motor 6.
Seen from the above description, screw propeller 74 can rotate freely within the scope of certain angle around bolt 73, when the second rotor 7 rotates, this structure also can provide lift as ordinary construction rotor, when the second rotor 7 stops operating, two screw propellers 74 swing under the action of the forces of the wind backward, reduce the air resistance produced, and improve aircraft efficiency.
Further, also comprise wheel undercarriage 8, described wheel undercarriage 8 is arranged at bottom fuselage 1.
Seen from the above description, under the condition having runway, aircraft assisting also by wheel undercarriage 8, takes off with the form of linear accelerating, and make the field of application of aircraft wider, applicability is better.
Please refer to shown in Fig. 1 to Fig. 3, embodiment one of the present utility model is:
A kind of vertically taking off and landing flyer, comprise fuselage 1, two main wings 2 are arranged with in the middle part of described fuselage 1, described fuselage 1 afterbody is provided with empennage, also comprise two inclining rotary mechanisms 3, two the first motors 4, two the first rotors 5, second motor 6 and the second rotor 7, described fuselage 1 head bilateral symmetry is provided with two inclining rotary mechanisms 3, described inclining rotary mechanism comprises fixed link and the 3rd motor, described fixed link is horizontally disposed with, described 3rd motor is installed on the fuselage 1, described fixed link one end is coaxially connected with the output shaft of the 3rd motor, the described fixed link other end is provided with the first motor 4, the output shaft of described first motor 4 is mutually vertical with fixed link, described first rotor 5 is arranged on the output shaft of the first motor 4, described fuselage 1 afterbody is provided with the second motor 6, the output shaft setting direction of described second motor 6 straight down, described second rotor 7 is arranged on the output shaft of described second motor 6, the length of described inclining rotary mechanism 3 is greater than the radius of rotation of the first rotor 5, the distance of described inclining rotary mechanism 3 to main wing 2 is greater than the radius of rotation of the first rotor 5, described second rotor 7 comprises oar pad 71, lower oar pad 72, two bolts 73 and two screw propellers 74, described upper oar pad 71 and lower oar pad 72 are interfixed by bolt 73, described two screw propellers 74 are arranged on two bolts 73 respectively, described screw propeller 74 is rotatably installed for rotating shaft with the bolt 73 of correspondence, described upper oar pad 71 is connected with the output shaft of the second motor 6, also comprise wheel undercarriage 8, described wheel undercarriage 8 is arranged at bottom fuselage 1.
In sum, the vertically taking off and landing flyer that the utility model provides, forebody is provided with the first rotor, fuselage afterbody is provided with the second rotor, when aircraft takeoff, first rotor and the second rotor produce lift upwards jointly, aircraft can be taken off vertically when not having runway, when aircraft horizontal flight, inclining rotary mechanism drives the first rotor rotational, the first rotor is made to produce pulling force forward with higher efficiency, simultaneously because the first rotor is arranged on aircraft Handpiece Location, the air-flow that screw propeller produces can not be blocked by wing, loss of lift is less, efficiency significantly improves, the length of inclining rotary mechanism is greater than the radius of rotation of the first rotor, described inclining rotary mechanism to the distance of main wing is greater than the radius of rotation of the first rotor, can prevent the first rotor and fuselage or main wing from colliding, screw propeller can rotate freely within the scope of certain angle around bolt, when the second rotor rotational, this structure also can provide lift as ordinary construction rotor, when the second rotor stops operating, two screw propellers swing under the action of the forces of the wind backward, reduce the air resistance produced, improve aircraft efficiency, under the condition having runway, aircraft assisting also by wheel undercarriage, take off with the form of linear accelerating, make the field of application of aircraft wider, applicability is better.
The foregoing is only embodiment of the present utility model; not thereby the scope of the claims of the present utility model is limited; every utilize the utility model specification sheets and accompanying drawing content to do equivalent structure or equivalent flow process conversion; or be directly or indirectly used in other relevant technical fields, be all in like manner included in scope of patent protection of the present utility model.
Claims (4)
1. a vertically taking off and landing flyer, comprise fuselage, described waist is arranged with two main wings, described afterbody is provided with empennage, it is characterized in that: also comprise two inclining rotary mechanisms, two the first motors, two the first rotors, second motor and the second rotor, described fuselage head bilateral symmetry is provided with two inclining rotary mechanisms, described inclining rotary mechanism comprises fixed link and the 3rd motor, described fixed link is horizontally disposed with, described 3rd motor is arranged on fuselage, described fixed link one end is coaxially connected with the output shaft of the 3rd motor, the described fixed link other end is provided with the first motor, the output shaft of described first motor is mutually vertical with fixed link, described first rotor is arranged on the output shaft of the first motor, described afterbody is provided with the second motor, the output shaft setting direction of described second motor straight down, described second rotor is arranged on the output shaft of described second motor.
2. vertically taking off and landing flyer according to claim 1, is characterized in that: the length of described inclining rotary mechanism is greater than the radius of rotation of the first rotor, and described inclining rotary mechanism to the distance of main wing is greater than the radius of rotation of the first rotor.
3. vertically taking off and landing flyer according to claim 1, it is characterized in that: described second rotor comprises oar pad, lower oar pad, two bolts and two screw propellers, described upper oar pad and lower oar pad are interfixed by bolt, described two screw propellers are arranged on two bolts respectively, described screw propeller is with the bolt of correspondence for rotating shaft is rotatably installed, and described upper oar pad is connected with the output shaft of the second motor.
4. vertically taking off and landing flyer according to claim 1, is characterized in that: also comprise wheel undercarriage, described wheel undercarriage is arranged at fuselage bottom.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520896554.4U CN205098475U (en) | 2015-11-11 | 2015-11-11 | Vertical take -off and landing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520896554.4U CN205098475U (en) | 2015-11-11 | 2015-11-11 | Vertical take -off and landing aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN205098475U true CN205098475U (en) | 2016-03-23 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520896554.4U Active CN205098475U (en) | 2015-11-11 | 2015-11-11 | Vertical take -off and landing aircraft |
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| CN (1) | CN205098475U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105882952A (en) * | 2016-04-20 | 2016-08-24 | 羊丁 | Unmanned aerial vehicle for automatically clearing garbage on overhead lines |
| CN107021206A (en) * | 2017-04-11 | 2017-08-08 | 深圳智航无人机有限公司 | Unmanned plane |
-
2015
- 2015-11-11 CN CN201520896554.4U patent/CN205098475U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105882952A (en) * | 2016-04-20 | 2016-08-24 | 羊丁 | Unmanned aerial vehicle for automatically clearing garbage on overhead lines |
| CN107021206A (en) * | 2017-04-11 | 2017-08-08 | 深圳智航无人机有限公司 | Unmanned plane |
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