CN1740056A - Airplane with airflow jetted over wings to generate lift force - Google Patents
Airplane with airflow jetted over wings to generate lift force Download PDFInfo
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- CN1740056A CN1740056A CN 200510096767 CN200510096767A CN1740056A CN 1740056 A CN1740056 A CN 1740056A CN 200510096767 CN200510096767 CN 200510096767 CN 200510096767 A CN200510096767 A CN 200510096767A CN 1740056 A CN1740056 A CN 1740056A
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Abstract
The airplane with airflow jetted over wings to generate lift force has wings mounted over the fuselage and one or several airflow pipelines and airflow nozzles communicated with the airflow machine set over the wings. The airplane of the present invention needs only short distance low speed sliding for taking off and landing, and has small wingspan, greatly raised flying safety and lowered flying cost.
Description
Technical field
The invention belongs to the aircaft configuration technical field.
Background technology
Traditional fixed wing aircraft must rely on aircraft and slide at a high speed or fly, and it is poor to produce enough air-flow velocitys at the wing upper and lower, thereby produces enough upper and lower sides' of wing difference of pressure, reaches and satisfies the purpose of taking off and flying.This aircraft has following deficiency: the one, and take off and land and must slide at a high speed, easily have an accident; The 2nd, the airport is required height, sufficiently long runway should be arranged, require the ground-surface intensity of runway enough again, the cost height of airport construction, the seaworthiness of aircraft is poor; The 3rd, because it is poor to lean on the differences in shape of wing upper and lower to produce air rate, current difference is limited, and the lift that is produced is limited, has seriously limited the load capacity of aircraft; The 4th, in order to satisfy the needs of high speed running take off, high-performance driving engine, the manufacturing of aircraft and flight cost height, energy consumption height must be installed; The 5th, in order to guarantee the lift requirement, wing must be done very long, the aircraft floor area is big, and the poor stability when sliding.
Summary of the invention
Purpose of the present invention; just in order to overcome above-mentioned the deficiencies in the prior art; provide a kind of span to reduce; chord increases; only need dash road low speed to slide; or only need the hardstand just can go up to the air and slowly landing, and improve flight safety greatly, reduce the aircraft of the airflow jetted over wings to generate lift force of flight support cost.
The objective of the invention is to be achieved through the following technical solutions.
The aircraft of airflow jetted over wings to generate lift force, its wing is installed on body upper, is provided with the air-flow spout that one or more are communicated with the air-flow machine by airflow line above wing.
Each air-flow machine of the present invention can connect an air-flow spout; Also can connect two or more air-flow spouts; Be provided with the vertically-guided wing and vertical direction rudder in air-flow spout both sides; The air-flow spout is the horn-like spout of flat of being close to upper surface of the airfoil; Be respectively arranged with forward hydroplane and back diving rudder in the front and back of wing; Afterbody at fuselage is provided with the decelerating flow machine that produces air-flow to fuselage the place ahead; Afterbody at fuselage is provided with trust engine; Described air-flow machine is for using the jet engine or the oar blade type driving engine of fuel oil, perhaps the oar blade type electrical motor of electrification.
The present invention makes full use of the principle of aerodynamics " air-flow velocity High Voltage more is more little; the more little pressure of flow velocity is big more ", the air-flow machine is close to is placed in wing top, by air-flow machine jet-stream wind backward, above wing, make high velocity air, produce, causing above the wing far below the gas pressure intensity below the wing much larger than the air-flow velocity of wing below, difference of pressure by the wing upper and lower provides lift for aircraft, and the air-flow that sprays backward also provides thrust for flight simultaneously.Wing is installed on body upper, and can effectively avoid and reduce air-flow machine gas flow temperature influences aircraft, and effectively strengthens the stability of aircraft flight.The vertically-guided wing that is provided with above wing had both guaranteed that the stable heading of aircraft was a state, the air-flow of effective again steering current machine ejection, and effectively overcome the influence of crosswind in-flight.The trumpet-shaped air-flow spout of flat can make the air-flow of ejection disperse and be close to upper surface of the airfoil, forms the high velocity air layer.Can change vector by changing the air flow jetting direction by rotation vertical direction rudder.Set forward hydroplane and back diving rudder are mainly used in assists the control state of flight.The decelerating flow machine that is arranged at afterbody is worked before aircraft landing, produces air-flow forward, under the cooperation of forward and backward diving rudder, provides reaction thrust for aircraft slows down, and to reduce air speed, is convenient to the landing of aircraft low speed, improves safety.Set trust engine is used for after aircraft reaches certain speed and height, close or reduce the air-flow acc power, the lift that " the top-surface camber lower plane " that utilizes forward and backward diving rudder and wing to form produced guarantees airplane ascensional force, utilizes the trust engine increase or flight thrust independently is provided.Trust engine of the present invention can determine whether apolegamy flexibly by the needs of different type of machines.
The present invention has the unrivaled following advantage of traditional fixed wing aircraft: the one, can realize taking off and land under the low velocity situation, and as safe as a house.The 2nd, the landing conditional request is low, need not long runway and slide landing, not only reduced guarantee, operating cost, can also improve seaworthiness greatly, can landing under simple and crude condition, in daily passenger traffic, shipping, rescue and relief work, warlike operation, be with a wide range of applications.The 3rd, owing to self-supporting high velocity air above wing, can be about wing, the side makes that great air-flow is poor, the lift that is obtained is huge, under the situation of using equal engine power, the load capacity of aircraft can obtain to improve, and traffic cost such as oil consumption can reduce.The 4th, what this aircraft was emphasized is to utilize the vertical high velocity air of aircraft self power manufacturing, so wing mainly is vertical layout, and the wing width can reduce greatly, and convenient driver behavior on runway machine airport is difficult for collision.The 5th, can effectively control aircraft balanced by regulating the air flow rate or the air-flow velocity of each air-flow machine or spout, the counterweight when taking off requires to reduce.The 6th, the rising of aircraft and reduction need not change angle and propelled at high velocity, and the acceleration/accel of flight is little, take advantage of seat more comfortable, the yet steady more safety of the goods of delivery.The 7th, utilize this technology, can develop superjumbo plane, the unit transportation volume increases greatly, reduces air freight costs greatly, and solves the problem that large cargo air transport difficulty maybe can't be transported.
Below, further set forth content of the present invention in conjunction with Figure of description.
Description of drawings
Fig. 1 is a front view of the present invention;
Fig. 2 is a birds-eye view of the present invention;
Fig. 3 is the scheme drawing of another embodiment of air-flow machine setting of the present invention;
Fig. 4 is the A-A cross-sectional schematic of air-flow machine of the present invention wing when connecting a plurality of air-flow spout;
Fig. 5 is a left view of the present invention;
Fig. 6 is the scheme drawing that the wing of conventional airplane produces lift;
Fig. 7 and Fig. 8 are air-flow machine of the present invention produces lift above wing principle schematic.
The specific embodiment
As Fig. 1, Fig. 2, Fig. 3, Fig. 4, shown in Figure 5, the present invention includes fuselage 1 and wing 2, wing 2 is installed on fuselage 1 top, above wing, be provided with the air-flow spout 5 that one or more are communicated with air-flow machine 3 by airflow line 4, each air-flow machine 3 can connect an air-flow spout 5, also can connect two or more air-flow spouts.Shown in Figure 2ly be provided with three air-flow machines, middle be the primary air machine, the both sides be inferior air-flow machine, air-flow spout of each air-flow machine connection; Three air-flow machines, three air-flow spouts of each air-flow machine connection of being provided with shown in Figure 3.Air-flow spout 5 is for being close to the horn-like spout of flat of upper surface of the airfoil.Air-flow machine 3 can select to use the jet engine or the oar blade type driving engine of fuel oil, perhaps the oar blade type electrical motor of electrification.Above wing, be provided with and the vertical vertically-guided rudder 6 in the same way of fuselage, can replace the very high vertical tail in conventional airplane tail top, reduce the influence of crosswind flight stability along air-flow spout both sides.At the rear of vertically-guided rudder vertical direction rudder 7 is set, improves turning efficiency.Forward hydroplane 9 and back diving rudder 8 are set respectively in the front and back of wing.Afterbody at fuselage also can be provided with the decelerating flow machine 10 that produces air-flow to fuselage the place ahead, and trust engine 11 is set.
As shown in Figure 6, traditional fixed wing aircraft, the top of its wing 2 is shaped as curved surface, and the below is the plane.Taking off is the principle of utilizing aerodynamics " air-flow velocity High Voltage more is more little; the more little pressure of flow velocity is big more ", leaning on the driving engine generation to produce air-flow promotion aircraft backward slides at a high speed, thereby producing above the wing greater than below the air-flow velocity V2 of air-flow velocity V1, and then the pressure P1 that makes wing below surpasses the pressure P2 of wing top, for taking off and flight provides lift.The present invention utilizes above-mentioned aerodynamic principle, but that adopts is Fig. 7, wing structure shown in Figure 8 and air-flow machine 3 is set above wing, make the air-flow velocity difference V4-V3 of wing upper and lower can reach the requirement of taking off at short notice by air-flow spout 5, the pressure difference P3-P4 that is the wing upper and lower is enough, thereby makes aircraft obtain the lift that takes off and fly.The air flow stream that the air-flow machine sprays is shown in dotted line among Fig. 7, Fig. 8.The high velocity air of air-flow machine ejection also provides powerful thrust for aircraft advances.After taking off, can reduce or close time air-flow machine or primary air acc power, the lift that utilizes the primary air machine to produce, and the lift that the shape of forward and backward diving rudder produces guarantees the required lift of aircraft flight.
This aircraft is realized taking off, flying and land by following operation control: the 3 startup work of air-flow machine, spray high velocity air by airflow line 4 backward from air-flow spout 5, produce take off lift and thrust rapidly, fly away from ground in the short range and improve constantly height and speed, finish take-off process; After reaching certain flying speed, because the top of the forward and backward diving rudder of wing is a curved surface and can be by being rotated down the raising curvature, still can produce needs lift, and keeps the due gliding ability of aircraft; Can suitably reduce the power of air-flow machine this moment, or the closed gas flow machine, and starting trust engine 11 provides flight thrust; Before the landing, open and control decelerating flow machine 10 generation reaction thrust, under the cooperation of forward and backward diving rudder, reduce air speed gradually, and recover the needs that the air-flow mechanomotive force guarantees slow landing process in good time, realize the safe falling of aircraft.The present invention also can not be provided with decelerating flow machine 10, and makes aircraft be in elevation angle flight by adjusting the flight angle, produces component backward and the back pull that forms, or adjusts forward and backward diving rudder angle and realize slowing down.The stable control of taking off, fly, landing and turn to control, diving rudder, yaw rudder be realized before and after power that can be by independent or comprehensive each air-flow machine of adjusting control, the adjusting control; The speed of aircraft flight can realize by the power of adjusting control air-flow machine or trust engine.
The present invention has the aeronautical technology of the maturation that aeronautical chart accumulates for many years and product basis for relying on, and has practicality.
Claims (9)
1, the aircraft of airflow jetted over wings to generate lift force, comprise fuselage (1) and wing (2), it is characterized in that wing (2) is installed on fuselage (1) top, is provided with the air-flow spout (5) that one or more are communicated with air-flow machine (3) by airflow line (4) above wing.
2, the aircraft of airflow jetted over wings to generate lift force according to claim 1 is characterized in that, each air-flow machine (3) connects an air-flow spout (5).
3, the aircraft of airflow jetted over wings to generate lift force according to claim 1 is characterized in that, each air-flow machine (3) connects two or more air-flow spouts (5).
4, the aircraft of airflow jetted over wings to generate lift force according to claim 1 is characterized in that, is provided with the vertically-guided wing (6) and vertical direction rudder (7) in air-flow spout (5) both sides.
5, the aircraft of airflow jetted over wings to generate lift force according to claim 1 and 2 is characterized in that, air-flow spout (5) is for being close to the horn-like spout of flat of upper surface of the airfoil.
6, the aircraft of airflow jetted over wings to generate lift force according to claim 1 is characterized in that, is respectively arranged with forward hydroplane (9) and back diving rudder (8) in the front and back of wing (2).
7, the aircraft of airflow jetted over wings to generate lift force according to claim 1 is characterized in that, is provided with the decelerating flow machine (10) that produces air-flow to fuselage the place ahead at the afterbody of fuselage (1).
8, the aircraft of airflow jetted over wings to generate lift force according to claim 1 is characterized in that, is provided with trust engine (11) at the afterbody of fuselage (1).
9, the aircraft of airflow jetted over wings to generate lift force according to claim 1 is characterized in that, described air-flow machine (3) is for using the jet engine or the oar blade type driving engine of fuel oil, perhaps the oar blade type electrical motor of electrification.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200510096767 CN1740056A (en) | 2005-08-01 | 2005-09-01 | Airplane with airflow jetted over wings to generate lift force |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200510010948 | 2005-08-01 | ||
| CN200510010948.6 | 2005-08-01 | ||
| CN 200510096767 CN1740056A (en) | 2005-08-01 | 2005-09-01 | Airplane with airflow jetted over wings to generate lift force |
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| Publication Number | Publication Date |
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| CN1740056A true CN1740056A (en) | 2006-03-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN 200510096767 Pending CN1740056A (en) | 2005-08-01 | 2005-09-01 | Airplane with airflow jetted over wings to generate lift force |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101857085A (en) * | 2010-06-03 | 2010-10-13 | 刘春� | Aircraft |
| CN102009743A (en) * | 2010-07-01 | 2011-04-13 | 北京航空航天大学 | Blowing based fuselage high incidence pitching moment control method |
| CN112197655A (en) * | 2020-09-25 | 2021-01-08 | 中国航天空气动力技术研究院 | Rolling control method and control device for rotating missile |
-
2005
- 2005-09-01 CN CN 200510096767 patent/CN1740056A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101857085A (en) * | 2010-06-03 | 2010-10-13 | 刘春� | Aircraft |
| CN101857085B (en) * | 2010-06-03 | 2013-06-12 | 刘春� | Aircraft |
| CN102009743A (en) * | 2010-07-01 | 2011-04-13 | 北京航空航天大学 | Blowing based fuselage high incidence pitching moment control method |
| CN102009743B (en) * | 2010-07-01 | 2013-06-05 | 北京航空航天大学 | Blowing based fuselage high incidence pitching moment control method |
| CN112197655A (en) * | 2020-09-25 | 2021-01-08 | 中国航天空气动力技术研究院 | Rolling control method and control device for rotating missile |
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