CN101139010A - Device for improving airplane ascensional force - Google Patents
Device for improving airplane ascensional force Download PDFInfo
- Publication number
- CN101139010A CN101139010A CNA2007100351614A CN200710035161A CN101139010A CN 101139010 A CN101139010 A CN 101139010A CN A2007100351614 A CNA2007100351614 A CN A2007100351614A CN 200710035161 A CN200710035161 A CN 200710035161A CN 101139010 A CN101139010 A CN 101139010A
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- air
- aircraft
- fuselage
- fixed
- casing
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Abstract
The present invention discloses a device to increase aircraft lift force. The device comprises a shell, an air inlet, an air outlet and a plurality of airflow plates. According to the principle of fluid mechanics, a plurality of arch arc-shaped airflow plates with a certain elevation angle are arranged in the shell, and airflow from the front air inlet and the two bottom lateral air inlets impacts each airflow plate and flows out from an air outlet opening on the top of the shell and the air outlet on the tail so that each airflow plate generates tension resultant force and therefore the aircraft lift force fixed on the shell is increased; the device not only can increase aircraft lift force, but also slow down falling velocity when the aircraft engine is failure, which is good for security glider landing by pilot. The device can be fixed on the upper part of the body of a plurality of aircrafts or the aircraft can be arranged in the body of the device so that the lift force of the aircraft can be increased.
Description
[technical field]
The present invention relates to a kind of device that increases airplane ascensional force.
[background technology]
Existing aircraft all is to fly by the thrust of air, and the engine horsepower of aircraft is big more, and air is just big more to the thrust of aircraft, and the speed of aircraft flight is just fast more, and the load carrying ability of aircraft is also big more.But the horsepower size of aircraft is directly proportional with the energy of consumption, and driving engine is subjected to the restriction of manufacturing process, so the flying speed of the load carrying ability of aircraft and aircraft has certain limit.When driving engine one timing of aircraft, its maximum lift is also just certain, and wanting increases some load carrying abilities again, is very difficult.
[summary of the invention]
The lift that is to overcome existing aircraft must be subjected to the defective of engine horsepower restriction, the invention provides a kind ofly under the certain situation of engine horsepower, can increase the device of airplane ascensional force, with the load-carrying ability that improves aircraft and the safety of aircraft.
For solving its technical matters, the technical solution used in the present invention is: set up a device that comprises the increase airplane ascensional force of casing, admission port, air extractor duct and a plurality of air-flow sheets on the fuselage of aircraft, be characterized in: 1. the front end at fuselage is provided with air inlet, the tail end of fuselage is provided with the air air extractor duct, two bottom sides at aircraft is provided with free-air diffuser, the top of aircraft is provided with a plurality of air air gates, is fixed with a plurality of air-flow sheets in fuselage interior by fixed mount.
2. on the admission port of front fuselage, be provided with the inlet valve that can limit suction quantity, on the inlet channel of fuselage bottom both sides, be provided with a plurality of induction openings, this induction opening is provided with the adjustment doors that can regulate suction quantity, respectively is provided with an escutcheon of giving vent to anger that adjusts tolerance on a plurality of air gates at fuselage top.
3. be provided with the fixed mount that intersects in length and breadth in fuselage interior, be fixed with a plurality of air-flow sheets on fixed mount, each air-flow sheet is arch or arc, and two ends are closed, and the middle part is provided with a plurality of air extractor vents, and the angle of facing upward down with the wind of each air-flow sheet and horizontal direction is 8～12 °.
The invention has the beneficial effects as follows: 1. when aircraft advances, air-flow enters fuselage by nose air intake, simultaneously also the induction opening from the inlet channel of two bottom sides enters fuselage, air-flow to each air-flow sheet in the past backward, impact from bottom to top, and discharge fuselage by a plurality of air gates and the afterbody air extractor duct from the fuselage top behind the air extractor vent on the air-flow sheet, the tension force that each air-flow sheet is produced is made a concerted effort, form the powerful lift of fuselage, be fixed on the fuselage or machine top of existing aircraft when this lift unit after, can increase the lift of aircraft, improve the load-carrying ability of aircraft.2. owing to be equipped with the air door that to control suction quantity on admission port of the present invention and the air gate, turn suction quantity when flying speed is fast down, transfer big suction quantity when flying speed is slow, make the tension force adjustable size of fuselage, after being contained on the aircraft, can alleviate the load of driving engine, help saving the energy.3. because the present invention does not establish power, and it is also light to conduct oneself with dignity, and cost is low, can be fixed on the various aircrafts, be connected the lift of aircraft to increase, therefore of many uses, easy to utilize.4. when the aero-engine et out of order,, allow air enter in a large number in the casing, increase the tension force of casing, can reduce the aircraft falling speed, help driver safety glide landing, the generation of minimizing accident as long as all open the adjustment doors of induction opening.
[description of drawings]
The present invention is further described below in conjunction with drawings and Examples.
Fig. 1 is a structural representation section-drawing of the present invention.
Fig. 2 is the A-A cutaway view among Fig. 1.
Fig. 3 is the B-B cutaway view among Fig. 1.
Fig. 4 is an inlet channel structural representation in bottom side among Fig. 1.
Fig. 5 is the structural representation front view that the present invention is installed in passenger plane or transport plane top.
Fig. 6 is the lateral plan of Fig. 5.
Fig. 7 is that the present invention is installed in the structural representation front view on the autogyro.
Fig. 8 is the lateral plan of Fig. 7.
Fig. 9 is the structural representation that the present invention is installed in the air minibus top.
Figure 10 is that the present invention is installed in the structural representation on the skycar vehicle body.
Figure 11 is the birds-eye view of Fig. 1.
Among the figure: 1 casing, 2 nose air intakes, 3 inlet valves, 4 side induction openings, 5 adjustment doors, 6 air-flow sheets, 7 fixed mounts, 8 tail air extractor ducts, 9 top air gates, 10 escutcheons of giving vent to anger.
[specific embodiment]
Embodiment 1: be installed in the airplane ascensional force device on airliner or the transport plane
With reference to accompanying drawing 1～6 and Figure 11: the casing 1 that is fixed with ichthyoid at the top of aircraft, front end at casing 1 is provided with nose air intake 2, this admission port is provided with the inlet valve 3 of scalable suction quantity, respectively be provided with a bottom side inlet channel 4 in the both sides of bottom of shell, inlet channel is provided with a plurality of side induction openings 5, the side induction opening is provided with adjustment doors 11, afterbody at casing is provided with tail air extractor duct 8, be provided with a plurality of air gates 9 at the top of casing 1, be equipped with the escutcheon 10 of giving vent to anger that to open/close air gate on each air gate 9, be provided with crisscross trellis fixed mount 7 in the inside of casing 1, on fixed mount, be fixed with a plurality of air-flow sheets 6, each air-flow sheet all is arch or arc, and becomes 8～12 ° at the elevation angle with level, and the middle part of air-flow sheet is provided with a plurality of air extractor vents.When aircraft advances, air-flow enters in the casing from the front end admission port and the both sides induction opening of casing, and a plurality of air-flow sheets are impacted, and air-flow makes each air-flow sheet produce tension force with joint efforts from the afterbody air extractor duct of casing subsequently, flow out in order to lift and the top air gate that increases aircraft.
Embodiment 2: be installed in the airplane ascensional force device on the autogyro
With reference to accompanying drawing 1～4 and Fig. 7, Fig. 8: the airplane ascensional force device of embodiment 1 described structure is fixed on the underbelly of autogyro, only exposes the screw propeller at top and the roller of operator's compartment and bottom.That is: the fuselage of autogyro is installed in the top of casing 1, the admission port 2 of casing 1 front end is consistent with driving compartment direction before the autogyro, the air extractor duct 8 of casing tail end is located at the tail below of autogyro, the inlet channel 4 of casing 1 bottom is located at the top of autogyro roller, does not contact with ground.
Embodiment 3: the airplane ascensional force device that is installed in the air minibus top
With reference to accompanying drawing 1～4 and accompanying drawing 9: the top that the airplane ascensional force device of embodiment 1 described structure is fixed on air minibus, that is: make casing 1 by riveting or be weldingly fixed on the fuselage top of air minibus, the nose air intake 2 of casing is consistent with the direction of head, the afterbody air extractor duct 8 of casing is consistent with the tail direction of aircraft, the top of casing is provided with a plurality of air gates 9, is equipped with on the air extractor vent 9 to control the escutcheon 10 of giving vent to anger of opening/closing.
Embodiment 4: be installed in the airplane ascensional force device on the skycar
With reference to accompanying drawing 1～4 and accompanying drawing 10: the vehicle body that skycar is installed in the top enclosure 1 of the airplane ascensional force device of embodiment 1 described structure, the nose air intake 2 of casing 1 is provided with inlet valve 3, the bottom side of casing is provided with inlet channel 4, inlet channel 4 is provided with the induction opening 5 of band adjustment doors 11, bottom at casing 1 also is provided with four rolling, the air extractor duct 8 of casing afterbody is located at the afterbody of skycar, the casing top is provided with a plurality of air gates 9, air gate 9 is provided with the escutcheon 10 of giving vent to anger that can open/close, be fixed with the air-flow sheet 6 of a plurality of arches in the casing by fixed mount 7, each air-flow sheet is provided with a plurality of through holes, and the angle of facing upward down with the wind of air-flow sheet and horizontal direction is 10 °.
Claims (3)
1. device that increases airplane ascensional force, comprise casing, admission port, air extractor duct and a plurality of air-flow sheet, it is characterized in that: the front end at fuselage is provided with air inlet, the tail end of fuselage is provided with the air air extractor duct, two bottom sides at aircraft is provided with free-air diffuser, the top of aircraft is provided with a plurality of air gates, is fixed with a plurality of air-flow sheets in fuselage interior by fixed mount.
2. according to the device of the described increase airplane ascensional force of claim 1, it is characterized in that: on the admission port of front fuselage, be provided with the inlet valve that can limit suction quantity, on the inlet channel of fuselage bottom both sides, be provided with a plurality of induction openings, this induction opening is provided with the adjustment doors that can regulate suction quantity, respectively is provided with an air leaving cover that adjusts tolerance on a plurality of air gates at fuselage top.
3. according to the device of claim 1 or 2 described increase airplane ascensional forces, it is characterized in that: be provided with the fixed mount that intersects in length and breadth in fuselage interior, on fixed mount, be fixed with a plurality of air-flow sheets, each air-flow sheet is an arc, two ends are dull and stereotyped and curved downwards, the middle part is provided with a plurality of air extractor vents and upwards arches upward, and the angle of facing upward of each air-flow sheet and horizontal direction is 8～12 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2007100351614A CN101139010A (en) | 2007-06-15 | 2007-06-15 | Device for improving airplane ascensional force |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2007100351614A CN101139010A (en) | 2007-06-15 | 2007-06-15 | Device for improving airplane ascensional force |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101139010A true CN101139010A (en) | 2008-03-12 |
Family
ID=39191156
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA2007100351614A Pending CN101139010A (en) | 2007-06-15 | 2007-06-15 | Device for improving airplane ascensional force |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101139010A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102272001A (en) * | 2009-01-29 | 2011-12-07 | 波音公司 | Rigid tipped riblets |
| WO2021001674A3 (en) * | 2019-07-01 | 2021-09-30 | Zhang Chuanrui | Aerodynamic techniques and methods for quieter supersonic flight |
-
2007
- 2007-06-15 CN CNA2007100351614A patent/CN101139010A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102272001A (en) * | 2009-01-29 | 2011-12-07 | 波音公司 | Rigid tipped riblets |
| CN102272001B (en) * | 2009-01-29 | 2014-09-17 | 波音公司 | Rigid tipped riblets |
| WO2021001674A3 (en) * | 2019-07-01 | 2021-09-30 | Zhang Chuanrui | Aerodynamic techniques and methods for quieter supersonic flight |
| CN114450224A (en) * | 2019-07-01 | 2022-05-06 | 张传瑞 | Aerodynamic techniques and methods for performing quieter supersonic flight |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |