CN104787306A - Low-speed safety aircraft capable of controlling flight attitude by aerodynamic force - Google Patents
Low-speed safety aircraft capable of controlling flight attitude by aerodynamic force Download PDFInfo
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- CN104787306A CN104787306A CN201510127436.1A CN201510127436A CN104787306A CN 104787306 A CN104787306 A CN 104787306A CN 201510127436 A CN201510127436 A CN 201510127436A CN 104787306 A CN104787306 A CN 104787306A
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Abstract
The invention discloses a low-speed safety aircraft capable of controlling the flight attitude by an aerodynamic force. The low-speed safety aircraft comprises a flexible aircraft, an engine, a gas compressor, a supply air distributor, vortex chambers, high-pressure gas cells, strip-shaped jet flow seams, helium airbags, a safety cabin and the like. Compressed gas in the gas compressor is ejected to airfoils through the strip-shaped jet flow seams arranged at the transition positions of leading edges and the airfoils of wings to generate a lift force and a push force, and is ejected to airfoils through the strip-shaped jet flow seams arranged at the transition positions of leading edges and the airfoils of a horizontal tail and a vertical tail to generate a wing effect to control the flight attitude. Through the application of a flight control principle and the combination with flexible body-wings, the helium airbags and the safety cabinet, the super-safe low-speed aircraft is formed. The low-speed safety aircraft has the advantages that fuel consumption is reduced greatly; piloting is easy; due to super-strong low-speed safety and controllability, the low-speed safety aircraft can be widely applied to prospecting, shooting, urban road monitoring, aerial advertising and the like; a super entertainment project suitable for the crowds which have firsthand experience of piloting a plane to flight, without pilot licenses, can be further developed.
Description
Technical field
The present invention relates to aviation aircraft, the lift-rising form and the flight attitude that particularly relate to aircraft control.
Background technology
Manufacture since first fixed wing aircraft makes a successful trial flight from 1903 Nian Laite brothers, taking off with landing mode normally by sliding of fixed wing aircraft, namely aircraft sliding horizontal is made by the thrust of driving engine or pulling force, wing and air are done relative motion, according to wing principle, due to the difference of the upper and lower curvature of aerofoil, the aircraft wing of high speed slide makes the air of former geo-stationary flow through distance difference up and down at one time at wing, distance, flow velocity is accelerated, according to Pa Nuli theorem, wing just produces lift, make the liftoff flight of aircraft, so, fixed wing aircraft brings speed from static by sliding, then the pattern of lift is produced, just huge fund need be dropped into, the strip airport on ground is built, the drawback brought by sliding landing comprises: occupy vast soil, Clearance requirement is had to airport periphery, landing Frequent Accidents, meteorology requires high, wartime is easily under attack and cause paralysis etc.Have again, present fixed wing aircraft, in order to reduce ground run distance and sinking speed, usual employing mechanical type lift-rising, namely by the device such as connecting rod mechanism, screw rod transporter, guide rail hydraulic brake, to stretch respectively to front and back in wing front and rear edge part and deflect down, maintenance aerofoil profile, wing area is increased, increases wing lift at low speeds, now also realize the vertical of fixed wing aircraft and short take-off and landing (STOL) by other three kinds of methods: Russian use by way of being exactly specially as providing vertical takeoff and landing by second jet engine, another kind is United States Corps " sparrow hawk " formula vertical take off and landing fighter, the method used, namely transported by gas piping and spray vertically downward to provide landing from the air of leading engine air compressor, the third F-35B being Lockheed Corp. produces gangs up against in opportunity of combat and uses, namely axle is used to drive lift fan and vector spout, its three kinds of methods all realize vertical/short take off and landing by the direct Jet with downward flow direction of air-flow.The wing flaps of present fixed wing aircraft, aileron, tailplane, vertical tail, they play the gesture stability effect of flight, be all by use large, the unresponsive hydraulic pressure of volume or mechanical system come needed for employ, this type of mechanism causes wing structure complexity, the numerous wadding of action, considerably increases the structural weight of aircraft, makes manufacturing cost, maintenance cost increases greatly.
" low little slowly " aerocraft that all purpose aircraft has part ownership a large amount of, comprise helicopter, unmanned plane, propeller-parachuting, aerodone, dirigible, fire balloon etc., these aircraft certain structures are too complicated, some is too simple, applies single, poor safety performance, operator need train for a long time through specialty, cannot popularize.
Summary of the invention
The present invention is directed to the deficiency of existing vehicle technology, a kind of low speed safe aircraft utilizing aerodynamic force to control flight attitude is provided, namely by the powered belt dynamic pressure mechanism of qi of driving engine, the pressurized air produced is stitched through the pipeline strip jet of providing and delivering set by the leading-edge radius of each wing and the intermediate location of aerofoil curved surface camber line and is sprayed, thus make the wing produce lift and thrust, realize controlling aircraft vertical, short take-off and landing (STOL); Application same principle, realizes the control of aerodynamic force to tailplane and vertical tail.
Utilize above-mentioned control technology, a kind of low speed safe aircraft that can realize vertical/short take-off and landing (STOL), soft body fuselage, high security of advantage integrating helicopter, fixed wing aircraft, dirigible is provided.
For realizing above technical purpose, the present invention will take following technical scheme.
A kind of low speed safe aircraft utilizing aerodynamic force to control flight attitude is by fuselage, wing, tailplane, vertical tail, driving engine, air compressor, gas piping is formed, it is the driven by engine air compressor had by aircraft that described aerodynamic force controls flight attitude, the pressurized air that air compressor exports is stitched by strip jet by diverter and is sprayed to aerofoil after the vortex cavity rotary compression that wing air supply pipe ingress engine nose of wing is formed, add the high speed slide for aircraft, Magnus effect is utilized to produce lift and thrust, only need the power that driving engine is very little, just powerful lift can be produced.Above-mentioned strip jet seam is the curved surface camber line intermediate location being arranged at leading edge of a wing radius and aerofoil, and leading edge of a wing radius is rear overlapping along misplacing along long line and aerofoil camber line of aerofoil camber line, and leaves strip jet seam.
A kind of low speed safe aircraft utilizing aerodynamic force to control attitude of flight vehicle is by fuselage, wing, tailplane, vertical tail, driving engine, air compressor, gas piping is formed, it is the driven by engine air compressor gathered around by aircraft that described aerodynamic force controls flight attitude, the pressurized air that air compressor exports is by diverter, control gas piping, control gas transmission main and arrive air feed distributing box, according to flight attitude requirement, by air feed distributing box to the port tailplane decline tracheae leading to tailplane, riser on port tailplane, starboard tailplane decline tracheae, riser on starboard tailplane, vertical tail left-hand rotation tracheae, vertical tail right-hand rotation tracheae carries out air feed respectively, what institute's supplied gas was formed through the tailplane leading edge of symmetrical airfoil is separated into four symmetrical plenum chambers along arc length line, deflecting plate, strip jet seam sprays to upper and lower four aerofoils of left and right horizontal empennage, institute's supplied gas sprays from top airfoil, produce lift, lower aerofoil sprays, produce negative lift, longitudinal direction and pitching flying attitude can be realized, to sample, institute's supplied gas through the vertical tail leading edge of symmetrical airfoil form be separated into two symmetrical plenum chambers along arc length line, deflecting plate, strip jet seam spray to vertical tail left and right aerofoil, can realize course changing control.
Present invention also offers a kind of low speed safe aircraft, by fuselage, wing, tailplane, vertical tail, driving compartment, driving engine, air compressor, gas piping, helium capsule is formed, described low speed safe aircraft is applied above-mentioned aerodynamic force and is controlled flight and flight attitude, described low speed safe aircraft wraps up whole aircraft outside face by the malleable plastic body covering of tool, inside is provided with some ring flexible frames, flexible frame is provided with some expansion joints, cut the covering telescopic band left by plastic body covering stretch into expansion joint by carrying, again one of elastic component is connected at the hook on flexible frame, a hanging hole connected on covering telescopic band, rise and tighten up plastic body diaphragms effect, reach body external form smooth, there is the visual effect of rigid construction, flexible frame inner ring connects the bulkhead be made up of elastic web composite material, described bulkhead is along with the rising of aircraft, barometric pressure reduces, helium capsule can expand, bulkhead has the swollen function of certain receipts, just as the rib of human body, can with telling to pick up the expansion lying prostrate and adapt to helium capsule, and without the need to accomplishing the air-tightness ship body that dirigible is such, the re-entrant portion filling helium capsule formed in bulkhead, hole fastened by the helium capsule that the line of helium capsule connects on flexible frame, the spar of air heave type membrane structure is provided with in wing inside, to improve the rigidity of wing, tailplane, vertical tail, namely be made up of plastic body covering, flexible frame, bulkhead, helium capsule, spar and conform to aerodynamic flexible machine body structure, this structure is subject to resilient after external force collision.
Above the center-of-gravity position of described aircraft, fuselage back is provided with Security Module, be made up of folded airbag, quantitatively helium tank, control cock, gas piping, elastic hinge, safe hatchcover, under emergency conditions, open helium control cock, the helium of quantitative helium tank through gas piping inject be in unfold shape unfold safety air bag, make it expand, back down the safe hatchcover connected by elastic hinge, after the helium of quantitative helium tank is all discharged, safety air bag reaches design volume, produce required buoyancy, delay the descending speed of aircraft, guarantee the safety of driver and crew; Application is filled helium capsule and is slowed down descending speed, compares, can overcome a lot of drawbacks of parachute, guarantee reliability with parachuting.
The helium capsule of the bulkhead internal cavity position filling of described aircraft is made up of the helium balloon that fills of football size, and each balloon has a line, and the helium capsule that their line subregion boundling is connected on flexible frame is fastened hole; And connect Security Module and driving compartment by bulkhead, plastic body covering, when whole body falls apart because strong External Force Acting causes, the personnel of driving compartment also can not be born fast, and in order to alleviate the deadweight of aircraft as far as possible, helium capsule is also filled into the re-entrant portion of the wing and car bonnet.
Described aircraft fuselage front portion is provided with the driving compartment that separate space is formed, the seat of the longitudinal arrangement of favourable aircraft balance in roll is provided with in driving compartment, again by the Fuel Tank in aft body bottom in mobile box movable come the unlikely displacement of trimmed flight device lift center of gravity, the proportional numerical value of Fuel Tank miles of relative movement in mobile box can be set according to the full weight of upper machine personnel, be performed by screw body.
Described aircraft is established by the fan by flexiplast injection mo(u)lding at the admission port of driving engine, fan shaft can be done freely to rotate on powered support, when engine inlet port has air current flow, fan can rotate, can play the true effect of large-scale fanjet, and when car bonnet is subject to external force deformation, fan can corresponding change shape, when external force loses, restore to the original state again.
The advantage that the present invention utilizes aerodynamic force to control flight attitude is, fundamentally change the conventional confguration pattern of mechanical lift-rising and flight manipulation, adopt technological approaches of the present invention, greatly can improve the properties of aircraft, eliminate the thick heaviness of existing aircraft, use dumb, the fluid pressure type of wasting time and energy or mechanical operation pattern, Flight Vehicle Structure weight is alleviated greatly, only need input different offline mode parameters to airborne computer, during pilot operator state of flight, computer will control the allocation scheme of air feed distributing box gas automatically according to code, make to drive an airplane simply easily, supersonic plane vertical takeoff and landing is the target be unable to reach always, apply above technology, only need design and meet the fixing wing of cruising condition suitable lift value, vertical/short take-off and landing (STOL) and high-speed flight, only need adjust the output tolerance of air compressor and the thrust of driving engine.
The low speed safe aircraft of application aerodynamic force control design case, eliminate a large amount of rigid constructiones, and be furnished with the aerostatic lift of helium, aircraft own wt is alleviated greatly, more capacity weights can be carried, realize high security, low hot-tempered sound, safeguard convenient, without the need to the aerial mobile platform on airport, aerial mine locating, aerial patrol, the supervision of urban air road, aerophotography, sky writing etc. can be widely used in, more can develop a kind of general population of being suitable for do not possess flight driving license just can undergo fly fly super-amusement project.
Accompanying drawing explanation
Below in conjunction with the drawings and specific embodiments, the present invention is further detailed explanation.
Accompanying drawing 1 is the three-dimensional local structure cutaway view of the full machine of embodiment of the present invention aircraft.
Accompanying drawing 2 is along the embodiment of the present invention aircraft wing transverse cross-sectional view of A-A line and air flow press molding signal.
Accompanying drawing 3 is the three-dimensional transverse cross-sectional view of embodiment of the present invention tailplane along B-B line.
Accompanying drawing 4 is the embodiment of the present invention vertical tail top plan view along C-C line.
Accompanying drawing 5 are D to embodiment of the present invention airframe structure partial elevational cutaway view.
Accompanying drawing 6 is embodiment of the present invention bag structure schematic diagrams.
Detailed description of the invention
Technical scheme of the present invention is explained below in conjunction with accompanying drawing 1 to accompanying drawing 6.
Shown in accompanying drawing 1, accompanying drawing 2, of the present invention utilize aerodynamic force to control the low speed safe aircraft of flight attitude comprises fuselage 1, wing 19, tailplane 29, vertical tail 15, driving engine 36, air compressor 37 are formed, driving engine 36 drives air compressor 37, the vortex cavity 20 that output squeezing air is made up of through wing air supply pipe 24 ingress engine nose of wing 18 diverter 25, then stitch 32 arrival aerofoils 34 by strip jet; This strip jet seam 32 is arranged at the radius of the leading edge of a wing 18 and the curved surface camber line intermediate location of aerofoil 34, and the radius of the leading edge of a wing 18 misplaces overlapping along long line with aerofoil 34 camber line along aerofoil 34 camber line, and leaves strip jet and stitch 32.
Accompanying drawing 1, accompanying drawing 2, accompanying drawing 3, the pressurized air that what accompanying drawing 4 provided is is exported by diverter 25 is through controlling gas piping 26, control gas transmission main 5 and arrive air feed distributing box 7, according to flight attitude requirement, by air feed distributing box 7 to the Left Horizontal Tail decline tracheae 8 leading to tailplane 29, riser 9 on Left Horizontal Tail, . right tailplane decline tracheae 12, riser 13 on right tailplane, the vertical tail left-hand rotation tracheae 10 of vertical tail 15, vertical tail right-hand rotation tracheae 11 carries out air feed respectively, four plenum chambers 39 be separated into along chord length line that institute's supplied gas can be formed through the tailplane leading edge 28 of symmetrical airfoil, water conservancy diversion pole 38, strip jet seam 32 sprays to tailplane 29 4 aerofoils 34, institute's supplied gas sprays from top airfoil, produce lift, lower aerofoil sprays, produce negative lift, can realize longitudinal direction and pitching flying attitude, equally, what institute's supplied gas can be formed through the vertical tail leading edge 14 of the vertical tail 15 of symmetrical airfoil prolongs two plenum chambers 39 that arc length line is separated into, water conservancy diversion pole 38, strip jet seam 32 sprays to the left and right aerofoil 34 of vertical tail 15, can realize course changing control.
What accompanying drawing 1, accompanying drawing 5 provided is fuselage 1, wing 19, tailplane 29, vertical tail 15, car bonnet 22 are wrapped up by the malleable plastic body covering 27 of tool, some ring flexible frames 4 are provided with in fuselage 1 plastic body covering 27 inside, flexible frame 4 is provided with some expansion joints 45, cut the covering telescopic band 44 left by plastic body covering 27 stretch into expansion joint 45 by carrying, again two of elastic component 42 are connected in respectively the hanging hole 40 of hook 43 on flexible frame 4 and covering contraction bands 44, tighten up and support plastic body covering 27; Flexible frame 4 inner ring connects bulkhead 6, filling helium capsule 30 in the cavity 3 at the position, space be made up of bulkhead 6, and hole 41 fastened by the helium capsule that the line 46 of helium capsule 30 connects on flexible frame 4; Be provided with the spar 35 of air heave type membrane structure formation at plastic body covering 27 internal cavities 3 of wing 19, tailplane 29, vertical tail 15, improve its rigidity.
What accompanying drawing 1, accompanying drawing 6 provided is the Security Module device being provided with folded airbag 49, quantitatively helium tank 50, control cock 52, gas piping 51, elastic hinge 48, safe hatchcover 2 formation at the back of fuselage 1, the helium of quantitative helium tank 50 is made to enter folded airbag 49 through gas piping 51 by opening control cock 52, the safe hatchcover 2. its inflation being backed down connected by elastic hinge 48 is until become the safety air bag after inflation 47, aircraft is made to increase quiet buoyancy, delay aircraft falling speed, ensure driver and crew's safety.
Helium capsule 30 described above is made up of the helium balloon that fills of football size, each helium capsule 30 has a line 46, the helium capsule that the line 46 subregion boundling of helium capsule 30 is connected on flexible frame 4 is fastened hole 41, and by bulkhead 6, plastic body covering 27 connects folded airbag and the driving compartment 16 of Security Module, when whole aircraft falls apart because strong External Force Acting causes, the personnel of driving compartment also can not be born fast, in order to reduce the deadweight of aircraft as far as possible, helium capsule 30 is also filled into wing 19, tailplane 29, vertical tail 15, cavity 3 position of car bonnet 22.
Fuselage 1 front portion shown in accompanying drawing 1 is provided with the driving compartment 16 that separate space is formed, driver and crew's seat 17 of the longitudinal arrangement of favourable aircraft balance in roll is provided with in driving compartment 16, Fuel Tank 31 moving forward and backward in mobile box 23 again by being provided with at the rear pars infrasegmentalis of fuselage 1, come trimmed flight device lift center of gravity and the unlikely displacement of aircraft center of gravity, the miles of relative movement proportional numerical value of Fuel Tank 31 in mobile box 23 can be set according to the full weight of upper machine personnel, be performed by screw body.
The admission port of the car bonnet 22 of accompanying drawing 2, be provided with by the fan 21 of flexiplast injection mo(u)lding, the axle of fan 21 freely can rotate on powered support 33, when car bonnet 22 admission port has air current flow, fan 21 can rotate, and can play the true effect of large-scale fanjet, and when car bonnet 22 is subject to external force deformation, fan 21 can corresponding change shape, when external force loses, and resilient again.
Claims (7)
1. the low speed safe aircraft utilizing aerodynamic force to control flight attitude, comprise fuselage, wing, tailplane, vertical tail, driving engine, air compressor, gas piping is formed, it is characterized in that: it is the air compressor (37) that the driving engine (36) had by aircraft is driven that described aerodynamic force controls flight attitude, the pressurized air that air compressor (37) exports by diverter (25) after vortex cavity (20) rotary compression that wing air supply pipe (24) ingress engine nose of wing (18) is formed, stitch (32) by strip jet and spray to aerofoil (34), add the high speed slide for aircraft, mug(unit of measure) is utilized to exert wall effect, produce lift and thrust, described strip jet seam (32) is arranged at the radius of the leading edge of a wing (18) and the curved surface camber line intermediate location of aerofoil (34), and the leading edge of a wing (18) radius misplaces overlapping along long line with aerofoil (34) camber line along aerofoil (34) camber line, and leave strip jet seam (32).
2. utilize aerodynamic force to control a low speed safe aircraft for flight attitude, comprise fuselage, wing, tailplane, vertical tail, driving engine, air compressor, gas piping is formed, it is characterized in that: it is that the driving engine (36) had by aircraft drives air compressor (37) that described aerodynamic force controls flight attitude, and the pressurized air that air compressor (37) exports is by diverter (25), control gas piping (26), control gas transmission main (5) and arrive air feed distributing box (7), according to flight attitude requirement, by air feed distributing box (7) to the Left Horizontal Tail decline tracheae (8) leading to tailplane (29), riser (9) on Left Horizontal Tail, right tailplane downtake (12), riser (13) on right tailplane, vertical tail left-hand rotation tracheae (10), vertical tail right-hand rotation tracheae (11) carries out air feed respectively, supply pressure gas to form through the tailplane leading edge (28) of symmetrical airfoil, along symmetry four plenum chambers (39) that chord length line is separated, deflecting plate (38), strip jet seam (32) sprays to upper and lower four aerofoils (34) in left and right horizontal empennage (29) left and right, and institute's supplied gas produces lift from top airfoil ejection, and lower aerofoil ejection produces negative lift, can realize longitudinal direction and pitching flying attitude, equally, institute's supplied gas sprays to the left and right aerofoil (34) of vertical tail (15) through prolonging of forming of the vertical tail leading edge (14) of symmetrical airfoil symmetry two plenum chambers (39) that chord length line separates, deflecting plate (38), strip jet seam (32), can realize course changing control.
3. the low speed safe aircraft that an application rights requires 1, claim 2 is invented, be made up of fuselage, wing, tailplane, vertical tail, driving compartment, driving engine, air compressor, gas piping, helium capsule, it is characterized in that: described low speed safe aircraft application rights requirement 1, aerodynamic force according to claim 2 control flight and flight attitude; The malleable plastic body covering (27) of described low speed safe aircraft apparatus wraps up the outside face of the fuselage (1) of whole aircraft, wing (19), tailplane (29), vertical tail (15), car bonnet (22); Some ring flexible frames (4) are provided with in plastic body covering (27) inside, flexible frame (4) is provided with some expansion joints (45), the covering telescopic band (44) left by cutting by plastic body covering (27) stretches into expansion joint (45), again two of elastic component (42) are connected at respectively the hanging hole (40) of hook (43) on flexible frame (4) and covering telescopic band (44), tighten up plastic body covering (27); Flexible frame (4) inner ring connects the bulkhead (6) be made up of elastic web composite material, cavity (3) interior filling helium capsule (30) formed in bulkhead (6), hole (41) fastened by the helium capsule that the line (46) of helium capsule (30) connects on flexible frame (4); The internal cavities (3) that the wing (19) of described low speed safe aircraft, tailplane (29), vertical tail (15) are wrapped up by plastic body covering (27) is provided with the spar (35) that air heave type membrane structure is formed, and improves its rigidity; Described low speed safe aircraft, namely have plastic body covering (27), flexible frame (4), bulkhead (6), helium capsule (30), spar (35) form and conform to aerodynamic flexible machine body structure, this structure is subject to resilient after external force collision.
4. according to low speed safe aircraft according to claim 3, it is characterized in that: at fuselage (1) the back center-of-gravity position of aircraft, by folded airbag (49), quantitative helium tank (50), control cock (52), gas piping (51), elastic hinge (48), the Security Module that safe hatchcover (2) is formed, under emergency conditions, open helium control cock (52), the helium of quantitative helium tank (50) injects through gas piping (51) folded airbag (49) being in rugosity makes it expand, back down the safe hatchcover (2) connected by elastic hinge (48), after the helium of quantitative helium tank (50) all injects, after inflation, safety air bag (47) reaches the required buoyancy of design volume generation, delay the descending speed of aircraft, guarantee the safety of driver and crew.
5. according to low speed safe aircraft according to claim 3, it is characterized in that: bulkhead (6) internal cavity (3) position, the helium capsule (30) of filling is made up of the helium balloon that fills of football size, each helium capsule (30) has a line (46), line (46) the subregion boundling helium capsule be connected on flexible frame (4) of helium capsule (30) is fastened hole (41), and connects folded airbag (49) and the driving compartment (16) of Security Module by bulkhead (6), plastic body covering (27); When whole aircraft falls apart because strong External Force Acting causes, the personnel of driving compartment also can not be fast whole born, in order to reduce aircraft deadweight as far as possible, helium capsule (30) is also filled into cavity (3) position of wing (19), tailplane (29), vertical tail (15), car bonnet (22).
6. according to low speed safe aircraft according to claim 3, it is characterized in that: fuselage (1) front portion is provided with the driving compartment (16) that separate space is formed, driver and crew's seat (17) of the longitudinal arrangement of favourable aircraft balance in roll is provided with in driving compartment (16), again by fuselage (1) movable in mobile box (23) of the Fuel Tank (31) that is provided with of pars infrasegmentalis afterwards, carry out trimmed flight and think highly of the heart and the unlikely displacement of lift center of gravity, the proportional numerical value of the miles of relative movement of Fuel Tank (31) in movable case solution (23) can be set according to the full weight of upper machine personnel, performed by screw body.
7. according to low speed safe aircraft according to claim 3, it is characterized in that: at the admission port of car bonnet (22), if by the fan (21) of flexiplast injection mo(u)lding, the axle of fan (21) freely can rotate upper work of powered support (33), when car bonnet (22) admission port has air current flow, fan (21) can rotate, the true effect of large-scale fanjet can be played, and when car bonnet (22) is subject to external force deformation, fan (21) can corresponding change shape, when external force loses, restore to the original state again.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510127436.1A CN104787306A (en) | 2015-03-23 | 2015-03-23 | Low-speed safety aircraft capable of controlling flight attitude by aerodynamic force |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510127436.1A CN104787306A (en) | 2015-03-23 | 2015-03-23 | Low-speed safety aircraft capable of controlling flight attitude by aerodynamic force |
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| CN104787306A true CN104787306A (en) | 2015-07-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510127436.1A Pending CN104787306A (en) | 2015-03-23 | 2015-03-23 | Low-speed safety aircraft capable of controlling flight attitude by aerodynamic force |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105539816A (en) * | 2015-12-20 | 2016-05-04 | 张彬 | Wing structure and propeller blade structure |
| CN109579637A (en) * | 2018-12-07 | 2019-04-05 | 中国人民解放军国防科技大学 | Missile attitude control mechanism without control surface |
| CN110313653A (en) * | 2019-07-01 | 2019-10-11 | 无锡市联合力动车业有限公司 | A kind of super air damping riding pants |
| WO2020201644A3 (en) * | 2019-04-01 | 2021-03-18 | Olivier Lamaille | High-lift device |
| CN112989500A (en) * | 2021-04-23 | 2021-06-18 | 中国空气动力研究与发展中心高速空气动力研究所 | Inlet flow-dividing stability-expanding design method suitable for contra-rotating lift fan |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102951289A (en) * | 2011-08-29 | 2013-03-06 | 顾一明 | Low speed safety aircraft capable of controlling flight attitude by utilizing aerodynamic force |
-
2015
- 2015-03-23 CN CN201510127436.1A patent/CN104787306A/en active Pending
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102951289A (en) * | 2011-08-29 | 2013-03-06 | 顾一明 | Low speed safety aircraft capable of controlling flight attitude by utilizing aerodynamic force |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105539816A (en) * | 2015-12-20 | 2016-05-04 | 张彬 | Wing structure and propeller blade structure |
| CN109579637A (en) * | 2018-12-07 | 2019-04-05 | 中国人民解放军国防科技大学 | Missile attitude control mechanism without control surface |
| WO2020201644A3 (en) * | 2019-04-01 | 2021-03-18 | Olivier Lamaille | High-lift device |
| CN110313653A (en) * | 2019-07-01 | 2019-10-11 | 无锡市联合力动车业有限公司 | A kind of super air damping riding pants |
| CN112989500A (en) * | 2021-04-23 | 2021-06-18 | 中国空气动力研究与发展中心高速空气动力研究所 | Inlet flow-dividing stability-expanding design method suitable for contra-rotating lift fan |
| CN112989500B (en) * | 2021-04-23 | 2021-07-23 | 中国空气动力研究与发展中心高速空气动力研究所 | Inlet flow-dividing stability-expanding design method suitable for contra-rotating lift fan |
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