CN103754372B - Vertical takeoff and landing can stop the aircraft with inverted flight in the air - Google Patents
Vertical takeoff and landing can stop the aircraft with inverted flight in the air Download PDFInfo
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- CN103754372B CN103754372B CN201310458281.0A CN201310458281A CN103754372B CN 103754372 B CN103754372 B CN 103754372B CN 201310458281 A CN201310458281 A CN 201310458281A CN 103754372 B CN103754372 B CN 103754372B
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Abstract
Vertical takeoff and landing can stop the aircraft with inverted flight in the air, propelling unit is sprayed under spraying propelling unit and two before being included in the installed in front two of aircraft two wing, propelling unit is sprayed under the rear side of two wings installs two, two side spray propelling units are installed in the both sides of two wings, after tail installs three, spray propelling unit; It is characterized in that: at the wing of aircraft and tail, 11 small-sized, volute air cushion reinforcement propelling units are efficiently installed altogether, wherein spray propelling unit under four, spray propelling unit before two, two side spray propelling units, spray propelling unit after three, comprise under each wing sprays propelling unit and one before each installation one near fuselage and spray propelling unit, near fuselage, propelling unit is sprayed under each installation one at the rear side of two wings, respectively install a side spray propelling unit in the both sides of two wings away from fuselage distalmost end, three propelling units installed at tail form equilateral equilateral triangle.
Description
Technical field
The present invention relates to and vertical takeoff and landing can stop the aircraft with inverted flight in the air, be applicable to all aircraft flown in an atmosphere, belong to aero-engine and flight sciemtifec and technical sphere.
Background technology
The research and development of modern aeroengine are advanced by leaps and bounds, but all these driving engines all cannot be accomplished that aircraft can take off vertically in an atmosphere, be stopped in the air and inverted flight, Britain once produced the aircraft that can slow down and stop aloft, but its landing will consume the fuel of 40%, affect flying distance and the flight time of this aircraft widely, so Britain does not re-use this kind of aircraft yet now; The present invention utilizes in the patent " 201310448764. 2 volute air cushion reinforcement propelling unit " of uncle minister in ancient times Wei near air nozzle, form the method that " air cushion " improves jet reaction thrust efficiency, and before and after the wing making this high efficiency propeller with low cost be arranged on aircraft and tail, thus make this aircraft can realize flight forward, backward flight, vertical takeoff and landing aloft, stop in the air.
Summary of the invention
The object of this invention is to provide a kind of can rapid flight, fast speed-raising aloft, vertical takeoff and landing, flight slow down, to stop in the air, inverted flight of rolling, crabbing energy vertical takeoff and landing stop in the air and the aircraft of inverted flight.
Vertical takeoff and landing can stop the aircraft with inverted flight in the air, propelling unit is sprayed under spraying propelling unit and two before being included in the installed in front two of aircraft two wing, propelling unit is sprayed under the rear side of two wings installs two, two side spray propelling units are installed in the both sides of two wings, after tail installs three, spray propelling unit; It is characterized in that:
1, the wing of aircraft and tail install altogether 11 small-sized, efficient volute air cushion reinforcement propelling unit, wherein spray propelling unit under four, propelling unit is sprayed before two, two side spray propelling units, propelling unit is sprayed after three, specifically comprise under each wing sprays propelling unit and one before each installation one near fuselage and spray propelling unit, near fuselage, propelling unit is sprayed under each installation one at the rear side of two wings, away from fuselage distalmost end, a side spray propelling unit is respectively installed in the both sides of two wings, tail install three afterwards spray propelling unit form equilateral equilateral triangle, namely one be in upper position, one is in lower left position, one is in bottom-right location, spray propelling unit under four for aircraft vertical landing, its power is maximum, and when spraying propelling unit maximum power work simultaneously under four, aircraft obtains maximum vertical lift, and namely aircraft takes off vertically from ground or type aircraft carrier deck, propelling unit is sprayed for deceleration and the inverted flight of flying before two, namely before aircraft is opened in flight forward process, propelling unit is sprayed, what aircraft acquisition was contrary with heading makes aircraft to back pressure, in aircraft process, when the lift that aircraft makes aircraft wing obtain to a certain extent is less than or equal to the weight of aircraft, propelling unit is sprayed under keeping the flying height of aircraft just must open four, when aircraft is zero to flying speed, and the lift spraying propelling unit under four and provide is when just equaling the weight of aircraft, propelling unit is sprayed before closing two, namely aircraft rests on motionless in the air, if when aircraft is zero to flying speed, the lift that spraying propelling unit under four provides is less than the weight of aircraft, aircraft is namely vertical to decline, if when aircraft is zero to flying speed, and the lift spraying propelling unit under four and provide just equals the weight of aircraft, now spray propelling unit before two also in running order, now namely aircraft forms inverted flight, two side spray propelling units are used for aircraft crabbing, tumbling flight, circuit, because only have these two side spray propelling units and spout thereof can do Q angle up and down in these 11 propelling units to rotate, 0 °≤Q≤90 °, two side spray propelling units: when another side spray propelling unit and spout thereof are rotated down when a side spray propelling unit and spout thereof rotate up, namely aircraft does the spiraling around airframe axis towards the direction that side spray propelling unit jet-stream wind is contrary, when when a side spray propelling unit and spout thereof rotate forward, another side spray propelling unit and spout thereof rotate backward, namely aircraft does the circuit close to aircraft wing plane towards the direction that side spray propelling unit jet-stream wind is contrary, when two side spray propelling units and spout thereof are rotated downwardly to perpendicular to aircraft wing simultaneously, aircraft obtains lift upwards, can rise fast by boosting aircraft, when two side spray propelling units and spout thereof are rotated upwardly to perpendicular to aircraft wing simultaneously, aircraft obtains downward thrust, can decline fast by boosting aircraft, when two side spray propelling units and spout thereof rotate to forward be simultaneously parallel to airframe axis time, aircraft obtains thrust backward, can boosting aircraft quick deceleration, when two side spray propelling units and spout thereof rotate to backward be simultaneously parallel to airframe axis time, aircraft obtains thrust forward, can accelerate fast by boosting aircraft, three spray propelling unit afterwards and become equilateral triangle to distribute, rear spray propelling unit is used for the acceleration of aircraft and regulates the heading of aircraft, when three spray propelling unit is opened afterwards simultaneously, aircraft obtains great forward propulsion, aircraft is fast to preacceleration, if when now nozzle outlet rotary also sprays by two side spray propelling units backward, aircraft obtains larger forward thrust, now aircraft obtains maximum forward acceleration, rear spray propelling unit is for regulating the heading of aircraft: when lower-left propelling unit is then sprayed in propelling unit unlatching upper in rear spray and rear spray bottom right propelling unit is closed or turns down flow and the flow velocity of Jet Stream, the thrust that aircraft tail top obtains is greater than the thrust that middle and lower part obtains, plane nose does low-angle downwards and turns to flight, when in rear spray lower-left propelling unit and rear spray bottom right propelling unit unlatching then spray, upper propelling unit is closed or turns down flow and the flow velocity of Jet Stream, the thrust of the middle and lower part acquisition of aircraft tail is greater than the thrust of top acquisition, plane nose upwards does low-angle and turns to flight, if each propelling unit cooperation of aircraft opens and closes, then the airflight performance of aircraft is that existing aircraft is unsurpassable.
2, the volute air cushion reinforcement propelling unit of 11 small-sized efficients, rotary power is provided by the multiple automotive engine in fuselage or electrical motor, the rotary power provided can be accomplished: V=0 and 2500 rev/min <V< 20000 revs/min.
The volute air cushion reinforcement propelling unit of the small-sized efficient 3, near aircraft wing, be installed in the downside of aircraft wing, object is the air-flow velocity do not affected on the upside of aircraft wing, thus ensures the lift that the upper and lower air-flow velocity difference of aircraft wing is formed.
The present invention compared with prior art has the following advantages:
1, do not find that there is and similar multiple angle of rake patent documentation report is installed on board the aircraft.
2, present invention utilizes the small-sized efficient volute air cushion reinforcement propelling unit of Wei Baiqing invention, so the propelling unit that installation 11 is so aboard and multiple automotive engine, its total weight estimates the driving engine total weight that can not exceed existing jet airplane.
3, the small-sized efficient volute air cushion reinforcement propelling unit of Wei Baiqing invention, utilizes automotive engine to do power, volume is little, lightweight, consumption of fuel is few, and this brings maximum air mileage and flight time or maximum capacity weight to aircraft.
4, aircraft vertical landing can not only make the development of the space shuttle of China obtain larger fast lifting, and the Carrier Development of China can also be made to solve maximum carrier-borne aircraft to take off problem.
5, the present invention utilizes the small-sized efficient volute air cushion reinforcement propelling unit of 11 uncle minister in ancient times inventions Wei, its high velocity air ejected is the air slightly high compared with normal temperature, the high-temperature gas of F35 ejection up to 927 DEG C of the U.S. can not be resembled, very easily type aircraft carrier deck or runway are burnt out.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of the embodiment of the present invention;
Fig. 2 is middle A-A generalized section embodiment illustrated in fig. 1.
In Fig. 1-2: 1, head 2, ventral 3, front spray left side flap forward propeller 4, lower spray left side flap forward propeller 5, lower spray right side flap forward propeller 6, front spray right side flap forward propeller 7, starboard wing 8, right spray right-side propellers 9, lower spray right side flap after propeller 10, lower spray left side flap after propeller 11, port wing 12, left spray left side propelling unit 13, tail 14, the tail wing 15, main injection jet 16, cap jet 17, tail shell 18, rear spray lower-left propelling unit 19, rear spray bottom right propelling unit 20, after spray middle propelling unit.
body embodiment
In the embodiment one shown in Fig. 1-2: vertical takeoff and landing can stop the aircraft with inverted flight in the air, propelling unit is sprayed under spraying propelling unit and two before being included in the installed in front two of aircraft two wing, propelling unit is sprayed under the rear side of two wings installs two, two side spray propelling units are installed in the both sides of two wings, after tail installs three, spray propelling unit, it is characterized in that: the wing of aircraft and tail install altogether 11 small-sized, efficient volute air cushion reinforcement propelling unit, wherein spray propelling unit under four, propelling unit is sprayed before two, two side spray propelling units, propelling unit is sprayed after three, specifically comprise under each wing sprays propelling unit and one before each installation one near fuselage and spray propelling unit, near fuselage, propelling unit is sprayed under each installation one at the rear side of two wings, away from fuselage distalmost end, a side spray propelling unit is respectively installed in the both sides of two wings, tail 13 install three afterwards spray propelling unit form equilateral equilateral triangle, namely one be in upper position, one is in lower left position, one is in bottom-right location, spray propelling unit under four for aircraft vertical landing, its power is maximum, and when spraying propelling unit maximum power work simultaneously under four, aircraft obtains maximum vertical lift, and namely aircraft takes off vertically from ground or type aircraft carrier deck, propelling unit is sprayed for deceleration and the inverted flight of flying before two, namely before aircraft is opened in flight forward process, propelling unit is sprayed, what aircraft acquisition was contrary with heading makes aircraft to back pressure, in aircraft process, when the lift that aircraft makes aircraft wing obtain to a certain extent is less than or equal to the weight of aircraft, propelling unit is sprayed under keeping the flying height of aircraft just must open four, when aircraft is zero to flying speed, and the lift spraying propelling unit under four and provide is when just equaling the weight of aircraft, propelling unit is sprayed before closing two, namely aircraft rests on motionless in the air, if when aircraft is zero to flying speed, the lift that spraying propelling unit under four provides is less than the weight of aircraft, aircraft is namely vertical to decline, if when aircraft is zero to flying speed, and the lift spraying propelling unit under four and provide just equals the weight of aircraft, now spray propelling unit before two also in running order, now namely aircraft forms inverted flight, two side spray propelling units are used for aircraft crabbing, tumbling flight, circuit, because only have these two side spray propelling units and spout thereof can do Q angle up and down in these 11 propelling units to rotate, 0 °≤Q≤90 °, two side spray propelling units: when another side spray propelling unit and spout thereof are rotated down when a side spray propelling unit and spout thereof rotate up, namely aircraft does the spiraling around airframe axis towards the direction that side spray propelling unit jet-stream wind is contrary, when when a side spray propelling unit and spout thereof rotate forward, another side spray propelling unit and spout thereof rotate backward, namely aircraft does the circuit close to aircraft wing plane towards the direction that side spray propelling unit jet-stream wind is contrary, when two side spray propelling units and spout thereof are rotated downwardly to perpendicular to aircraft wing simultaneously, aircraft obtains lift upwards, can rise fast by boosting aircraft, when two side spray propelling units and spout thereof are rotated upwardly to perpendicular to aircraft wing simultaneously, aircraft obtains downward thrust, can decline fast by boosting aircraft, when two side spray propelling units and spout thereof rotate to forward be simultaneously parallel to airframe axis time, aircraft obtains thrust backward, can boosting aircraft quick deceleration, when two side spray propelling units and spout thereof rotate to backward be simultaneously parallel to airframe axis time, aircraft obtains thrust forward, can accelerate fast by boosting aircraft, three spray propelling unit afterwards and become equilateral triangle to distribute, rear spray propelling unit is used for the acceleration of aircraft and regulates the heading of aircraft, when three spray propelling unit is opened afterwards simultaneously, aircraft obtains great forward propulsion, aircraft is fast to preacceleration, if when now nozzle outlet rotary also sprays by two side spray propelling units backward, aircraft obtains larger forward thrust, now aircraft obtains maximum forward acceleration, rear spray propelling unit is for regulating the heading of aircraft: when propelling unit 20 upper in rear spray open then spray lower-left propelling unit 18 and rear spray bottom right propelling unit 19 close or turn down flow and the flow velocity of Jet Stream time, the thrust that aircraft tail 13 top obtains is greater than the thrust that middle and lower part obtains, plane nose 1 does low-angle downwards and turns to flight, when rear spray lower-left propelling unit 18 and rear spray bottom right propelling unit 19 open that in then spray, flow and the flow velocity of Jet Stream is closed or turned down to upper propelling unit 20, the thrust of the middle and lower part acquisition of aircraft tail 13 is greater than the thrust of top acquisition, plane nose 1 upwards does low-angle and turns to flight, if each propelling unit cooperation of aircraft opens and closes, then the airflight performance of aircraft is that existing aircraft is unsurpassable.
The volute air cushion reinforcement propelling unit of 11 small-sized efficients, rotary power is provided by the multiple automotive engine in fuselage or electrical motor, the rotary power provided can be accomplished: V=0 and 2500 rev/min <V< 20000 revs/min.
The volute air cushion reinforcement propelling unit of the small-sized efficient near aircraft wing, be installed in the downside of aircraft wing, object is the air-flow velocity do not affected on the upside of aircraft wing, thus ensures the lift that the upper and lower air-flow velocity difference of aircraft wing is formed.
Claims (1)
1. vertical takeoff and landing can stop the aircraft with inverted flight in the air, propelling unit is sprayed under spraying propelling unit and two before being included in the installed in front two of aircraft two wing, propelling unit is sprayed under the rear side of two wings installs two, two side spray propelling units are installed in the both sides of two wings, after tail installs three, spray propelling unit, it is characterized in that: at the wing of aircraft and tail, 11 small-sized, volute air cushion reinforcement propelling units are efficiently installed altogether, comprise under each wing sprays propelling unit and one before each installation one near fuselage and spray propelling unit, near fuselage, propelling unit is sprayed under each installation one at the rear side of two wings, away from fuselage distalmost end, a side spray propelling unit is respectively installed in the both sides of two wings, three that install at tail (13) spray propelling unit afterwards and form equilateral equilateral triangle, namely one be in upper position, one is in lower left position, and one is in bottom-right location, spray propelling unit under four for aircraft vertical landing, its power is maximum, and when spraying propelling unit maximum power work simultaneously under four, aircraft obtains maximum vertical lift, and namely aircraft takes off vertically from ground or type aircraft carrier deck, propelling unit is sprayed for deceleration and the inverted flight of flying before two, namely before aircraft is opened in flight forward process, propelling unit is sprayed, what aircraft acquisition was contrary with heading makes aircraft to back pressure, in aircraft process, when the lift that aircraft makes aircraft wing obtain to a certain extent is less than or equal to the weight of aircraft, propelling unit is sprayed under keeping the flying height of aircraft just must open four, when aircraft is zero to flying speed, and the lift spraying propelling unit under four and provide is when just equaling the weight of aircraft, propelling unit is sprayed before closing two, namely aircraft rests on motionless in the air, if when aircraft is zero to flying speed, the lift that spraying propelling unit under four provides is less than the weight of aircraft, aircraft is namely vertical to decline, if when aircraft is zero to flying speed, and the lift spraying propelling unit under four and provide just equals the weight of aircraft, now spray propelling unit before two also in running order, now namely aircraft forms inverted flight, two side spray propelling units are used for aircraft crabbing, tumbling flight, circuit, because only have these two side spray propelling units and spout thereof can do Q angle up and down in these 11 propelling units to rotate, 0 °≤Q≤90 °, two side spray propelling units: when another side spray propelling unit and spout thereof are rotated down when a side spray propelling unit and spout thereof rotate up, namely aircraft does the spiraling around airframe axis towards the direction that side spray propelling unit jet-stream wind is contrary, when when a side spray propelling unit and spout thereof rotate forward, another side spray propelling unit and spout thereof rotate backward, namely aircraft does the circuit close to aircraft wing plane towards the direction that side spray propelling unit jet-stream wind is contrary, when two side spray propelling units and spout thereof are rotated downwardly to perpendicular to aircraft wing simultaneously, aircraft obtains lift upwards, can rise fast by boosting aircraft, when two side spray propelling units and spout thereof are rotated upwardly to perpendicular to aircraft wing simultaneously, aircraft obtains downward thrust, can decline fast by boosting aircraft, when two side spray propelling units and spout thereof rotate to forward be simultaneously parallel to airframe axis time, aircraft obtains thrust backward, can boosting aircraft quick deceleration, when two side spray propelling units and spout thereof rotate to backward be simultaneously parallel to airframe axis time, aircraft obtains thrust forward, can accelerate fast by boosting aircraft, three spray propelling unit afterwards and become equilateral triangle to distribute, rear spray propelling unit is used for the acceleration of aircraft and regulates the heading of aircraft, when three spray propelling unit is opened afterwards simultaneously, aircraft obtains great forward propulsion, aircraft is fast to preacceleration, if when now nozzle outlet rotary also sprays by two side spray propelling units backward, aircraft obtains larger forward thrust, now aircraft obtains maximum forward acceleration, rear spray propelling unit is for regulating the heading of aircraft: when lower-left propelling unit (18) is then sprayed in propelling unit (20) unlatching upper in rear spray and rear spray bottom right propelling unit (19) closes or turn down flow and the flow velocity of Jet Stream, the thrust that aircraft tail (13) top obtains is greater than the thrust that middle and lower part obtains, plane nose (1) does low-angle downwards and turns to flight, when in rear spray lower-left propelling unit (18) and rear spray bottom right propelling unit (19) unlatching then spray, flow and the flow velocity of Jet Stream is closed or turned down to upper propelling unit (20), the thrust of the middle and lower part acquisition of aircraft tail (13) is greater than the thrust of top acquisition, plane nose (1) upwards does low-angle and turns to flight, if each propelling unit cooperation of aircraft opens and closes, then the airflight performance of aircraft is that existing aircraft is unsurpassable, the volute air cushion reinforcement propelling unit of 11 small-sized efficients, rotary power is provided by the multiple automotive engine in fuselage or electrical motor, the rotary power provided can be accomplished: V=0 and 2500 rev/min <V< 20000 revs/min.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310458281.0A CN103754372B (en) | 2013-10-01 | 2013-10-01 | Vertical takeoff and landing can stop the aircraft with inverted flight in the air |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310458281.0A CN103754372B (en) | 2013-10-01 | 2013-10-01 | Vertical takeoff and landing can stop the aircraft with inverted flight in the air |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103754372A CN103754372A (en) | 2014-04-30 |
| CN103754372B true CN103754372B (en) | 2015-09-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310458281.0A Active CN103754372B (en) | 2013-10-01 | 2013-10-01 | Vertical takeoff and landing can stop the aircraft with inverted flight in the air |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1137998A (en) * | 1995-06-15 | 1996-12-18 | 刘世英 | Finless and vertical landing wing jet aero-plane |
| CN1281409A (en) * | 1997-12-10 | 2001-01-24 | 佛朗哥·卡潘纳 | System to transform horizontal take-off and self-sustained horizontal flight airplane into self-sustained horizontal flight, vertical landing and take-off, hybrid integrated airplane |
| CN1629037A (en) * | 2003-12-18 | 2005-06-22 | 唐山大唐动力机械有限公司 | Helicopter without rotors |
| CN101367435A (en) * | 2008-09-16 | 2009-02-18 | 广州伟韬电子科技有限公司 | Novel air injection aerial vehicle |
| CN102320376A (en) * | 2011-06-17 | 2012-01-18 | 李卫华 | The VTOL jet plane |
| CN103318411A (en) * | 2012-03-19 | 2013-09-25 | 陈永春 | Fixed wing vertical takeoff and landing aircraft |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203623968U (en) * | 2013-10-01 | 2014-06-04 | 魏伯卿 | Aircraft with vertical take-off and landing and aerial halting and upside-down flight abilities |
-
2013
- 2013-10-01 CN CN201310458281.0A patent/CN103754372B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1137998A (en) * | 1995-06-15 | 1996-12-18 | 刘世英 | Finless and vertical landing wing jet aero-plane |
| CN1281409A (en) * | 1997-12-10 | 2001-01-24 | 佛朗哥·卡潘纳 | System to transform horizontal take-off and self-sustained horizontal flight airplane into self-sustained horizontal flight, vertical landing and take-off, hybrid integrated airplane |
| CN1629037A (en) * | 2003-12-18 | 2005-06-22 | 唐山大唐动力机械有限公司 | Helicopter without rotors |
| CN101367435A (en) * | 2008-09-16 | 2009-02-18 | 广州伟韬电子科技有限公司 | Novel air injection aerial vehicle |
| CN102320376A (en) * | 2011-06-17 | 2012-01-18 | 李卫华 | The VTOL jet plane |
| CN103318411A (en) * | 2012-03-19 | 2013-09-25 | 陈永春 | Fixed wing vertical takeoff and landing aircraft |
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| Publication number | Publication date |
|---|---|
| CN103754372A (en) | 2014-04-30 |
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Effective date of registration: 20180710 Address after: 226371 North four groups of Tu Shan village, Xingdong Town, Tongzhou District, Nantong, Jiangsu Patentee after: NANTONG HUAXIA AIRPLANE ENGINEERING TECHNOLOGY CO., LTD. Address before: 314408 304, room 2, 30 shallow water bay, Kashi street, Haining, Jiaxing, Zhejiang. Patentee before: Wei Boqing |