CN104888466A - Vertical take-off and landing fixed wing aircraft - Google Patents
Vertical take-off and landing fixed wing aircraft Download PDFInfo
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- CN104888466A CN104888466A CN201510279376.5A CN201510279376A CN104888466A CN 104888466 A CN104888466 A CN 104888466A CN 201510279376 A CN201510279376 A CN 201510279376A CN 104888466 A CN104888466 A CN 104888466A
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- whole movable
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- 238000002485 combustion reaction Methods 0.000 claims abstract description 3
- 238000009434 installation Methods 0.000 claims description 11
- 230000001105 regulatory effect Effects 0.000 claims description 4
- 230000002337 anti-port Effects 0.000 claims description 2
- 239000000203 mixture Substances 0.000 claims description 2
- 230000000630 rising effect Effects 0.000 claims description 2
- 230000002146 bilateral effect Effects 0.000 abstract 3
- 238000005096 rolling process Methods 0.000 abstract 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
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Abstract
The invention discloses a vertical take-off and landing fixed wing aircraft. The aircraft is characterized by being provided with a left whole movable flap and a right whole movable flap. A power device is composed of power device bodies of bilateral symmetry. The left whole movable flap is composed of a left wing root and a left wing tip, the right whole movable flap of the aircraft is composed of a right wing root and a right wind tip, namely, the left whole movable flap and the right whole movable flap are a left whole wing and a right whole wing respectively or are parallel to a rolling rotating shaft of an aircraft body, namely, the straight line of the aircraft X-axis cuts the left wing and the right wing symmetrically, from the cutting face of the left wing and the cutting face of the right wing to the wing tip part of the left wing and the wing tip part of the right wing, the left whole movable flap and the right whole movable flap are symmetrically installed on a left main shaft and a right main shaft which can rotate independently by 90 degrees in the forward and reverse directions respectively, and a main shaft of the left whole movable flap and a main shaft of the right whole movable flap are symmetrically installed on a servo device and controlled by the servo device, wherein the servo device controls the main shaft of the left whole movable flap and the main shaft of the right whole movable flap to rotate in the forward and reserve directions. Motors of bilateral symmetry or internal combustion engines of bilateral symmetry are adopted to supply power to the aircraft. The power device bodies have the functions of exerting power in the opposite directions.
Description
(1) technical field
the present invention relates to a kind of VTOL fixed wing aircraft, particularly a kind of VTOL fixed wing aircraft of symmetrical power electric model plane.
(2) background technology
present fixed wing aircraft does not generally have the ability of VTOL, does not namely have the ability of vertical soft landing, with short take-off and landing ability.
(3) summary of the invention
in view of the deficiency of this type of electronic fixed wing aircraft, the invention provides a kind of VTOL fixed wing aircraft of symmetrical power electric model plane.
the technical solution adopted for the present invention to solve the technical problems is, a kind of VTOL fixed wing aircraft, it is characterized in that, VTOL fixed wing aircraft is provided with a left side, right complete dynamic aileron, power set are symmetrical power compositions, a left side for aircraft, right complete dynamic aileron is respectively by a left side, right flank root is to left, right flank nose part forms, namely left, right complete dynamic aileron is whole port wing and whole starboard wing respectively, or the straight line symmetry cutting being parallel to body wobble shaft and aircraft X-axis is left, starboard wing, from a left side, starboard wing cut surface is respectively to left, the tip station of starboard wing, the part port wing namely split outside place left wing wing by left wing's cut surface and the part starboard wing of same symmetry division, move aileron in dynamic aileron and the right side entirely entirely respectively as a left side, left, right complete dynamic aileron respectively symmetry be arranged on can independently to just, a left side for negative both direction 90-degree rotation, on right main shaft, left, the complete dynamic aileron main shaft in the right side respectively symmetrical being arranged on controls it on the servomechanism installation of positive and negative contrary both direction rotation, and controls by it, and left, right main wing, left, right complete dynamic aileron, left, right complete dynamic aileron main shaft, with a left side, right servomechanism installation has symmetrical structure and symmetrical assembling.Aircraft power is symmetrical motor or internal combustion engine, and each power set have the function that contrary each other direction applies power respectively, and such as, the forward and reverse rotation of direct current generator, applies the thrust that direction is contrary each other.
fixed wing aircraft VTOL flight of the present invention comprises the steps:
(1) electronic model plane are in put down and fly state;
(2) left and right power motor is out of service;
(3) the instantaneous total power antiport of left and right power motor, forces air speed rapid drawdown;
(4) left and right complete dynamic aileron is less than the suitable angle of 90 degree with the corresponding symmetry of positive and negative rotation respectively respectively under respective servomechanism installation controls;
(5) left and right power motor is again out of service;
(6) left and right power motor rightabout total power applied thrust each other, force aircraft with aircraft steering spindle and Z axis or its parallel lines for axle rotates, direction of rotation produces thrust downwards with main wing and is as the criterion;
(7) aircraft stops along the rectilinear motion of former navigation, and the rotary motion that to change into steering spindle and Z axis or its parallel lines be rotating shaft, maintains this rotary motion;
(8) symmetrically regulate left and right power motor power, or the symmetrical respective angles regulating left and right complete dynamic aileron, reach the object regulating airplane ascensional force size, and then control aircraft and continue vertical rising or slowly vertical landing or the aerial object that suspends.
the operation principle of VTOL fixed wing aircraft is very simple, left and right complete dynamic aileron Rotational Symmetry angle in the opposite direction under the driving of servomechanism installation, the screw that actual just upper formation one is blade with the left and right complete dynamic aileron of aircraft, the left and right power motor of aircraft is to direction applied thrust contrary each other, force the rotary motion that aircraft is rotating shaft with steering spindle and Z axis or its parallel lines, reach and produce lift in the vertical direction, control the VTOL of aircraft.
the invention has the beneficial effects as follows, provide a kind of VTOL fixed wing aircraft of symmetrical power electric model plane, the left and right complete dynamic aileron of appropriate control can also complete the action such as short field take-off, landing, has outstanding meaning for the operation of fixed-wing unmanned plane.
(4) accompanying drawing explanation
fig. 1 is the right main wing of invention and the right side dynamic aileron structure chart entirely.
in figure, the right complete dynamic aileron of 1 ﹒, the right complete dynamic aileron servomechanism installation of 2 ﹒.
(5) detailed description of the invention, for Fig. 1, starboard wing is partitioned into part wing and entirely moves aileron as the right side, right complete dynamic aileron is fixed on right complete dynamic aileron main shaft, main shaft controls by right complete dynamic aileron servomechanism installation, servomechanism installation can be conventional steering wheel, or stepper motor etc., corresponding installation port wing, the left and right power motor with two-way applying power function is installed, tailplane can not be installed and controls steering wheel, with tailplane rudder face, VTOL flight just can be completed according to above-mentioned steps, unsettled flight after taking off.
Claims (3)
1. a VTOL fixed wing aircraft, it is characterized in that: VTOL fixed wing aircraft is provided with a left side, right complete dynamic aileron, power set are symmetrical power compositions, a left side for aircraft, right complete dynamic aileron is respectively by a left side, right flank root is to left, right flank nose part forms, namely left, right complete dynamic aileron is whole port wing and whole starboard wing respectively, or the straight line symmetry cutting being parallel to body wobble shaft and aircraft X-axis is left, starboard wing, from a left side, starboard wing cut surface is respectively to left, the tip station of starboard wing, the part starboard wing of the part port wing namely split outside place left wing wing by left wing's cut surface and same symmetry division, respectively as a left side dynamic aileron and the right side dynamic aileron entirely entirely, aircraft power is symmetrical motor or internal combustion engine, each power set have the function that direction contrary each other applies power respectively.
2. a kind of VTOL fixed wing aircraft according to claim 1, it is characterized in that: symmetrical being arranged on can independently on the left and right main shaft of positive and negative both direction 90-degree rotation respectively for left and right complete dynamic aileron, left and right complete dynamic aileron main shaft respectively symmetrical being arranged on controls it on the servomechanism installation of positive and negative contrary both direction rotation, and control by it, and left and right main wing, left and right complete dynamic aileron, left and right complete dynamic aileron main shaft, has symmetrical structure and symmetrical assembling with left and right servomechanism installation.
3. a kind of VTOL fixed wing aircraft according to claim 1, is characterized in that: this fixed wing aircraft VTOL flight comprises the steps:
(1) electronic model plane are in put down and fly state;
(2) left and right power motor is out of service;
(3) the instantaneous total power antiport of left and right power motor, forces air speed rapid drawdown;
(4) left and right complete dynamic aileron is less than the suitable angle of 90 degree with the corresponding symmetry of positive and negative rotation respectively respectively under respective servomechanism installation controls;
(5) left and right power motor is again out of service;
(6) left and right power motor rightabout total power applied thrust each other, force aircraft with aircraft steering spindle and Z axis or its parallel lines for axle rotates, direction of rotation produces thrust downwards with main wing and is as the criterion;
(7) aircraft stops along the rectilinear motion of former navigation, and the rotary motion that to change into steering spindle and Z axis or its parallel lines be rotating shaft, maintains this rotary motion;
(8) symmetrically regulate left and right power motor power, or the symmetrical respective angles regulating left and right complete dynamic aileron, reach the object regulating airplane ascensional force size, and then control aircraft and continue vertical rising or slowly vertical landing or the aerial object that suspends.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510279376.5A CN104888466A (en) | 2015-05-28 | 2015-05-28 | Vertical take-off and landing fixed wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510279376.5A CN104888466A (en) | 2015-05-28 | 2015-05-28 | Vertical take-off and landing fixed wing aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN104888466A true CN104888466A (en) | 2015-09-09 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510279376.5A Pending CN104888466A (en) | 2015-05-28 | 2015-05-28 | Vertical take-off and landing fixed wing aircraft |
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| Country | Link |
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| CN (1) | CN104888466A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105727569A (en) * | 2016-03-19 | 2016-07-06 | 高小秒 | Power supply device for electric fixed-wing simulation aircraft |
| CN106081098A (en) * | 2016-08-24 | 2016-11-09 | 广州朱雀航空科技有限公司 | A kind of unmanned plane |
| CN106564612A (en) * | 2015-10-08 | 2017-04-19 | 张斌 | Taking off structure for carrier-borne aircraft |
| CN110870980A (en) * | 2018-09-02 | 2020-03-10 | 张斌 | Method for using electric aircraft with bionic flight capability |
Citations (6)
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|---|---|---|---|---|
| JP2009234551A (en) * | 2008-03-26 | 2009-10-15 | Kenta Yasuda | Vertical takeoff and landing aircraft having main wing installation angle changing device |
| CN101643116A (en) * | 2009-08-03 | 2010-02-10 | 北京航空航天大学 | Tiltrotor controlled by double-propeller vertical duct |
| CN101837195A (en) * | 2010-01-21 | 2010-09-22 | 罗之洪 | Model airplane with vertical takeoff and landing |
| JP2012111475A (en) * | 2010-11-28 | 2012-06-14 | Kenta Yasuda | Vertical takeoff and landing unmanned aircraft by wing-rotor |
| CN102642612A (en) * | 2012-05-11 | 2012-08-22 | 中国航空工业集团公司西安飞机设计研究所 | Airplane full chord length aileron |
| CN103991542A (en) * | 2014-05-30 | 2014-08-20 | 佛山市神风航空科技有限公司 | Rotary flapping wing driving airplane |
-
2015
- 2015-05-28 CN CN201510279376.5A patent/CN104888466A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2009234551A (en) * | 2008-03-26 | 2009-10-15 | Kenta Yasuda | Vertical takeoff and landing aircraft having main wing installation angle changing device |
| CN101643116A (en) * | 2009-08-03 | 2010-02-10 | 北京航空航天大学 | Tiltrotor controlled by double-propeller vertical duct |
| CN101837195A (en) * | 2010-01-21 | 2010-09-22 | 罗之洪 | Model airplane with vertical takeoff and landing |
| JP2012111475A (en) * | 2010-11-28 | 2012-06-14 | Kenta Yasuda | Vertical takeoff and landing unmanned aircraft by wing-rotor |
| CN102642612A (en) * | 2012-05-11 | 2012-08-22 | 中国航空工业集团公司西安飞机设计研究所 | Airplane full chord length aileron |
| CN103991542A (en) * | 2014-05-30 | 2014-08-20 | 佛山市神风航空科技有限公司 | Rotary flapping wing driving airplane |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106564612A (en) * | 2015-10-08 | 2017-04-19 | 张斌 | Taking off structure for carrier-borne aircraft |
| CN105727569A (en) * | 2016-03-19 | 2016-07-06 | 高小秒 | Power supply device for electric fixed-wing simulation aircraft |
| CN106081098A (en) * | 2016-08-24 | 2016-11-09 | 广州朱雀航空科技有限公司 | A kind of unmanned plane |
| CN110870980A (en) * | 2018-09-02 | 2020-03-10 | 张斌 | Method for using electric aircraft with bionic flight capability |
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Application publication date: 20150909 |