CN204527635U - The double-vane flapping wing aircraft of the controllable buoyancy wing and power wing - Google Patents
The double-vane flapping wing aircraft of the controllable buoyancy wing and power wing Download PDFInfo
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- CN204527635U CN204527635U CN201520211406.4U CN201520211406U CN204527635U CN 204527635 U CN204527635 U CN 204527635U CN 201520211406 U CN201520211406 U CN 201520211406U CN 204527635 U CN204527635 U CN 204527635U
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Abstract
The utility model discloses the double-vane flapping wing aircraft of a kind of controllable buoyancy wing and power wing, aim to provide a kind of power waste little, fly apart from far away, fireballing flapping wing aircraft.Described flapping wing aircraft comprises fuselage (1), the buoyancy wing (2), power wing (3), flapping wing actuating device, empennage (4) and control system, the described buoyancy wing (2) and described power wing (3) are equipped with several foramen alares (5), the described buoyancy wing (2) and described power wing (3) are provided with opening and closing device.The utility model is applied to the technical field of aviation aircraft.
Description
Technical field
The utility model relates to a kind of aircraft, particularly the double-vane flapping wing aircraft of a kind of controllable buoyancy wing and power wing.
Background technology
In order to realize the flight dream of the mankind, just there are people to begin one's study aircraft in early days, and begin one's study from flapping wing aircraft, but being obtain preliminary realization from Fixed Wing AirVehicle.Although the mankind can be served blue sky by Fixed Wing AirVehicle, flapping wing dream is also in continuous effort.Flapping wing aircraft refers to that picture bird-sample produces the aircraft of lift and the power that moves ahead by wing active movement, also known as ornithopter.Because flapping wing aircraft has plurality of advantages, such as flapping wing aircraft be integrated without the need to runway vertical takeoff and landing (VTOL), power system and control system and mechanical efficiency higher than fixed wing aircraft.
The reason that flapping wing aircraft never grows up has as follows:
1, the raw MAT'L of so much lightweight, power and power drive is not had to supply application before Lai Te brother utility model Fixed Wing AirVehicle;
2, after the flight of Lai Te brother utility model fixed-wing, aviation flight attention and the research and development energy of people's main flow have all focused on above the flight of fixed-wing, and although minority developer applies light material and up-to-date scientific and technological achievement technology, the principle of its bionical flight does not have breakthrough.
On August 2nd, 2010, a developer of Toronto aeronautical engineering institute is called todd reichert, and the flapping wing aircraft of a frame manpower of having taken a flight test, this flapping wing aircraft is called snowbird.Its span reaches 32M heavily about 92.59 pounds, uses carbon fiber, glass Sa cork wood, foam to be made; Flying speed can reach 15.91 mph..Thus make flapping wing aircraft obtain a little progress.
But above-mentioned flapping wing aircraft technology also has problem and shortcoming, such as: 1, because its aerodynamics just imitates Bird Flight purely, under existing raw MAT'L and engineering factor, efficient aircraft can not be designed, make this aircraft span too huge, lowly, power capacity consumes excessive for working flight buoyancy and forward flight force efficiency, is unfavorable for bearing a heavy burden and remote and relative high-speed flight; 2, have ignored the limitation of human muscle's kinetic energy, do not increase auxiliary power or use pure mechanical power, to such an extent as to current flapping wing aircraft is when heavy burden and remote high-speed flight relatively, can't become practicality aircraft truly.
Utility model content
Technical problem to be solved in the utility model overcomes the deficiencies in the prior art, provide a kind of power waste little, to fly apart from farther, speed sooner, the double-vane flapping wing aircraft of the highly higher controllable buoyancy wing and power wing.
The technical scheme that the utility model adopts is:
The double-vane flapping wing aircraft of the described controllable buoyancy wing and power wing comprises fuselage, the buoyancy wing, power wing, be arranged on the flapping wing actuating device on described fuselage, be arranged on empennage and the control system of described afterbody, the described buoyancy wing is fixedly installed on described fuselage, described power wing and described flapping wing actuating device are in transmission connection, the described buoyancy wing and described power wing are equipped with several foramen alares, the described buoyancy wing and described power wing are provided with the opening and closing device suitable with several foramen alares described, during flight, control described the logical of several foramen alares by described opening and closing device to close.
The described buoyancy wing is folding wings or telescopic wing.
Described power wing is folding wings or telescopic wing.
The described buoyancy wing is positioned at the top of described power wing.
Described flapping wing actuating device comprises the fork, slide block with described fork sliding block joint, dwang that one end and described slide block are hinged and the wheel word that is fixedly connected with the described dwang other end that are hinged with described fuselage, described wheel word is fixedly installed on described fuselage, and described power wing is fixedly connected with described fork.
Opening and closing device on described power wing is the plate with described power wing sliding block joint, described plate is connected with described slide block, described plate is provided with air extractor vent, described air extractor vent is identical with the hole of described foramen alare, and the pitch-row I between two adjacent described air extractor vents is identical with the pitch-row II between adjacent two described foramen alares.
Described pitch-row I and described pitch-row II is three times of the hole of described air extractor vent or described foramen alare, the hole of described air extractor vent or described foramen alare is the half of the stroke of described slide block, when described power wing is positioned at upper summit, described foramen alare and described air extractor vent stagger mutually, and the pitch-row III of the described foramen alare in described air extractor vent and adjacent outside is the twice in the hole of described air extractor vent or described foramen alare, the pitch-row IV of the described foramen alare of described air extractor vent and adjacent inner side is the size in the hole of described air extractor vent or described foramen alare.
The beneficial effects of the utility model are: because the utility model have employed the controlled design of double-vane, the double-vane flapping wing aircraft of the described controllable buoyancy wing and power wing comprises fuselage, the buoyancy wing, power wing, be arranged on the flapping wing actuating device on described fuselage, be arranged on empennage and the control system of described afterbody, the described buoyancy wing is fixedly installed on described fuselage, described power wing and described flapping wing actuating device are in transmission connection, the described buoyancy wing and described power wing are equipped with several foramen alares, the described buoyancy wing and described power wing are provided with the opening and closing device suitable with several foramen alares described, during flight, control described the logical of several foramen alares by described opening and closing device to close, so, the utility model can fill up the defect of the aerodynamic force theory of flapping wing aircraft, have from heavy and light, span ratio is little, rise and fall without runway very-short-reach, power system and control system integration, mechanical efficiency is higher than fixed wing aircraft, bear a heavy burden large, flying distance is far away, safety performance is high, simple operation and other advantages.
Meanwhile, because the utility model adopts the biconjugate wing opening and closing foramen alare formula flight theory to fly, i.e. a pair power wing, keeps the buoyancy wing of trimmed flight for a pair.The antagonistic force that power wing pats air using the effective sq m span, and can according to the needs of flight as lift and move ahead, control break flapping wing frequency and moment of torsion, collapsiblely when not flying pack up.The described buoyancy wing provides the available buoyancy needed for flight, and it required for flight, can carry out controls flexible, collapsiblely when not flying packs up.The double-vane flapping wing aircraft of the described controllable buoyancy wing and power wing also has an advantage, be exactly when flying et out of order, it can become two Double-protective safety launching appliances, and it can be widely used in the fields such as communications and transportation, rescue and relief work, national defense and military, sports campaign.
Accompanying drawing explanation
Fig. 1 is the structural representation of the double-vane flapping wing aircraft of the described controllable buoyancy wing and power wing;
Fig. 2 is the structural representation of the described buoyancy wing 2 and described power wing 3 and described flapping wing actuating device;
Fig. 3 is the opening and closing situation schematic diagram of described foramen alare 5 under different conditions.
Detailed description of the invention
As shown in Figure 1, the double-vane flapping wing aircraft of the described controllable buoyancy wing and power wing comprises fuselage 1, the buoyancy wing 2, power wing 3, be arranged on the flapping wing actuating device on described fuselage 1, be arranged on empennage 4 and the control system of described fuselage 1 afterbody, the described buoyancy wing 2 is fixedly installed on described fuselage 1, described power wing 3 is in transmission connection with described flapping wing actuating device, the described buoyancy wing 2 and described power wing 3 are equipped with several foramen alares 5, the described buoyancy wing 2 and described power wing 3 are provided with the opening and closing device suitable with several foramen alares 5 described, during flight, control described the logical of several foramen alares 5 by described opening and closing device to close.
In the present embodiment, the described buoyancy wing 2 is folding wings or telescopic wing.
In the present embodiment, described power wing 3 is folding wings or telescopic wing.
In the present embodiment, the described buoyancy wing 2 is positioned at the top of described power wing 3.
In the present embodiment, described flapping wing actuating device comprises the fork 6, slide block 7 with described fork 6 sliding block joint, dwang 8 that one end and described slide block 7 are hinged and the wheel word 9 that is fixedly connected with described dwang 8 other end that are hinged with described fuselage 1, described wheel word 9 is fixedly installed on described fuselage 1, and described power wing 3 is fixedly connected with described fork 6.
As shown in Figure 2, in the present embodiment, opening and closing device on described power wing 3 is the plate 10 with described power wing 3 sliding block joint, described plate 10 is connected with described slide block 7, described plate 10 is provided with air extractor vent 11, described air extractor vent 11 is identical with the hole of described foramen alare 5, and the pitch-row IL1 between adjacent two described air extractor vents 11 is identical with the pitch-row IIL2 between adjacent two described foramen alares 5.
In the present embodiment, described pitch-row IL1 and described pitch-row IIL2 is three times of the hole of described air extractor vent 11 or described foramen alare 5, the hole of described air extractor vent 11 or described foramen alare 5 is the half of the stroke of described slide block 7, when described power wing 3 is positioned at upper summit A, described foramen alare 5 staggers mutually with described air extractor vent 11, and described air extractor vent 11 and the pitch-row IIIL3 of the described foramen alare 5 in adjacent outside are the twice in the hole of described air extractor vent 11 or described foramen alare 5, described air extractor vent 11 and the pitch-row IVL4 of the described foramen alare 5 of adjacent inner side are the size in the hole of described air extractor vent 11 or described foramen alare 5.
As shown in Figure 3, in the present embodiment, the method for operation of the double-vane flapping wing aircraft of the described controllable buoyancy wing and power wing is as follows:
When a, described power wing 3 are positioned at summit A, described foramen alare 5 staggers mutually with described air extractor vent 11, and described air extractor vent 11 and the pitch-row IIIL3 of the described foramen alare 5 in adjacent outside are the twice in the hole of described air extractor vent 11 or described foramen alare 5, described air extractor vent 11 and the pitch-row IVL4 of the described foramen alare 5 of adjacent inner side are the size in the hole of described air extractor vent 11 or described foramen alare 5, and the hole of described air extractor vent 11 or described foramen alare 5 is the half of the stroke of described slide block 7; When described power wing 3 moves from upper summit A to mid point IB, described slide block 7 promotes described plate 10, and described plate 10 outwards moves relative to described power wing 3; When described power wing 3 moves from the downward summit C of mid point IB, described slide block 7 pulls described plate 10, and described plate 10 inwardly moves relative to described power wing 3, and all described foramen alare 5 on described power wing 3 is closed in the process of motion; Open all described foramen alare 5 on the described buoyancy wing 2 simultaneously;
When b, described power wing 3 are positioned at lower summit C, described foramen alare 5 staggers mutually with described air extractor vent 11, and described air extractor vent 11 and the pitch-row IIIL3 of the described foramen alare 5 in adjacent outside are the twice in the hole of described air extractor vent 11 or described foramen alare 5, described air extractor vent 11 and the pitch-row IVL4 of the described foramen alare 5 of adjacent inner side are the size in the hole of described air extractor vent 11 or described foramen alare 5, and the hole of described air extractor vent 11 or described foramen alare 5 is the half of the stroke of described slide block 7; When upwards working motion is to mid point IID from lower summit C for described power wing 3, described slide block 7 promotes described plate 10, and described plate 10 inwardly moves relative to described power wing 3; When described power wing 3 from mid point IID upwards working motion supreme summit A time, described slide block 7 pulls described plate 10, and described plate 10 outwards moves relative to described power wing 3; All described foramen alare 5 on described power wing 3 is opened in the process of motion; The all described foramen alare 5 of the described buoyancy wing 2 is closed simultaneously.
Below the double-vane flapping wing aircraft of the described controllable buoyancy wing and power wing is analyzed:
One, under identical atmospheric pressure: when the described foramen alare 5 of described power wing 3 is closed, within the downward unit time of upper summit, motion can produce the lift of F1, so when described power wing 3 also can produce F2 down-force on lower summit with upward movement in the identical unit time, i.e. F1=F2; Two power sums equal zero, and namely aircraft acting equals zero, and jumps in aircraft original place.
Two, suppose that described power wing 3 does periodic motion and moves, the described foramen alare 5 of described power wing 3 open account for described power wing 3 developable surface long-pending 50%, when described power wing 3 moves downward, the described foramen alare 5 of described power wing 3 is closed, producible lift F1; Described power wing 3 upward movement, the described foramen alare 5 of described power wing 3 is opened, account for 50% of power wing span area, just can be considered the drag reduction 50% of described power wing 3 upward movement, aircraft obtains the half to raising force F1, but due to the existence of acceleration due to gravity, the speed of rising is still not enough to offset the speed declined, and aircraft crashes into original place.
Three, additional have the described buoyancy wing 2 that can control opening and closing hole and also enough keep neutral buoyancy for a pair, and method is as follows:
1, establish when described power wing 3 have account for its hole to be opened/closed of 50% time, at the downward working motion in upper summit, when moving to lower summit in the unit time, the described foramen alare 5 of described power wing 3 whole process is closed; Meanwhile, whole described foramen alare 5 whole process of the described buoyancy wing 2 of enough buoyancy can be provided to open.If now the motion of described foramen alare 5 can produce the lift of F1, and the described buoyancy wing 2 does not produce resistance, and under described power wing 3 arrives during summit, at once close the whole described foramen alare 5 of the described buoyancy wing 2, now the visual described buoyancy wing 2 obtains the lift of F1 indirectly.
2, so described power wing 3 on lower summit to move up to summit in the identical unit time time, the omnidistance whole described foramen alare 5 of described power wing 3 is opened; Meanwhile, whole described foramen alare 5 whole process of the described buoyancy wing 2 of enough buoyancy can be provided to close.Now the upward movement of visual described power wing 3 can produce the resistance of 1/2nd F1, after the F1 that now the described buoyancy wing 2 obtains, effectively keeps buoyancy and has resisted acceleration due to gravity G, can be considered and do not have buoyancy to lose.
3, described power wing 3 upward movement can produce the resistance of 1/2nd F1, and the buoyancy of the F1 that the described buoyancy wing 2 obtains, namely having: F1+(-1/2F1) the orbit period flapping wing aircraft buoyancy of=1/2F1 and flight forces produce., flapping wing aircraft upward flight.
Four, the useful work process that airborne period produces is:
(1) described power wing 3 moves downwardly to the whole described foramen alare 5 in lower summit and closes, and the whole described foramen alare 5 of the described buoyancy wing 2 is opened and obtained F lift;
(2) described power wing 3 upwards dynamic supreme summit, the described foramen alare 5 of 50% is opened and is produced resistance 1/2F
(3) the whole described foramen alare 5 of the described buoyancy wing 2 is closed, and obtains the described buoyancy wing 2 after F buoyancy and effectively keeps buoyancy force counters acceleration due to gravity G.
Namely having: F+(-1/2F) the flapping wing aircraft cycle buoyancy of=1/2F and flight forces produce.
Five, the described buoyancy wing 2 and the described foramen alare 5 of described power wing 3 close the relation of opening movement:
(1) the described foramen alare 5 of described power wing 3 is closed, the described foramen alare 5 of the described buoyancy wing 2 opens simultaneously; The described foramen alare 5 of described power wing 3 is opened, the described foramen alare 5 of the described buoyancy wing 2 is closed simultaneously, loop cycle.
The utility model is applied to the technical field of aviation aircraft.
Although embodiment of the present utility model describes with practical solution, but the restriction do not formed the utility model implication, the shape of such as described foramen alare 5 can be square hole, oblong aperture, positive circular hole, elliptical aperture, polygon hole and the empty footpath of taper etc., and be necessary to offer aperture number as much as possible, in order to aerodynamic force realizes maximal efficiency, the open and close methods in such as hole again: lever principle, electromagnetic principle, the hybrid mode method etc. of traction principle of confounding and multiple principle, for those skilled in the art, according to this specification sheets to the amendment of its embodiment and and the combination of other schemes be all apparent.
Claims (7)
1. the double-vane flapping wing aircraft of a controllable buoyancy wing and power wing, it is characterized in that: the double-vane flapping wing aircraft of the described controllable buoyancy wing and power wing comprises fuselage (1), the buoyancy wing (2), power wing (3), be arranged on the flapping wing actuating device on described fuselage (1), be arranged on empennage (4) and the control system of described fuselage (1) afterbody, the described buoyancy wing (2) is fixedly installed on described fuselage (1), described power wing (3) and described flapping wing actuating device are in transmission connection, the described buoyancy wing (2) and described power wing (3) are equipped with several foramen alares (5), the described buoyancy wing (2) and described power wing (3) are provided with the opening and closing device suitable with described several foramen alares (5), during flight, logical the closing of described several foramen alares (5) is controlled by described opening and closing device.
2. the double-vane flapping wing aircraft of the controllable buoyancy wing according to claim 1 and power wing, is characterized in that: the described buoyancy wing (2) is folding wings or telescopic wing.
3. the double-vane flapping wing aircraft of the controllable buoyancy wing according to claim 1 and power wing, is characterized in that: described power wing (3) is folding wings or telescopic wing.
4. the controllable buoyancy wing according to any one of claims 1 to 3 and the double-vane flapping wing aircraft of power wing, is characterized in that: the described buoyancy wing (2) is positioned at the top of described power wing (3).
5. the controllable buoyancy wing according to any one of claims 1 to 3 and the double-vane flapping wing aircraft of power wing, it is characterized in that: described flapping wing actuating device comprises the fork (6), slide block (7) with described fork (6) sliding block joint, dwang (8) that one end and described slide block (7) are hinged and the wheel word (9) that is fixedly connected with described dwang (8) other end that are hinged with described fuselage (1), described wheel word (9) is fixedly installed on described fuselage (1), and described power wing (3) is fixedly connected with described fork (6).
6. the double-vane flapping wing aircraft of the controllable buoyancy wing according to claim 5 and power wing, it is characterized in that: the opening and closing device on described power wing (3) is the plate (10) with described power wing (3) sliding block joint, described plate (10) is connected with described slide block (7), described plate (10) is provided with air extractor vent (11), described air extractor vent (11) is identical with the aperture of described foramen alare (5), the pitch-row I(L1 between two adjacent described air extractor vents (11)) with the pitch-row II(L2 between adjacent two described foramen alares (5)) identical.
7. the double-vane flapping wing aircraft of the controllable buoyancy wing according to claim 6 and power wing, it is characterized in that: described pitch-row I(L1) and described pitch-row II(L2) be three times of the aperture of described air extractor vent (11) or described foramen alare (5), the aperture of described air extractor vent (11) or described foramen alare (5) is the half of the stroke of described slide block (7), when described power wing (3) is positioned at upper summit (A), described foramen alare (5) and described air extractor vent (11) stagger mutually, and the pitch-row III(L3 of the described foramen alare (5) in described air extractor vent (11) and adjacent outside) be the twice in the aperture of described air extractor vent (11) or described foramen alare (5), the pitch-row IV(L4 of the described foramen alare (5) of described air extractor vent (11) and adjacent inner side) be the size in the aperture of described air extractor vent (11) or described foramen alare (5).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201520211406.4U CN204527635U (en) | 2015-04-10 | 2015-04-10 | The double-vane flapping wing aircraft of the controllable buoyancy wing and power wing |
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| CN201520211406.4U CN204527635U (en) | 2015-04-10 | 2015-04-10 | The double-vane flapping wing aircraft of the controllable buoyancy wing and power wing |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104787331A (en) * | 2015-04-10 | 2015-07-22 | 张晓赫 | Double-wing ornithopter provided with controllable buoyancy wings and power wings and operation method of double-wing ornithopter |
| CN112046743A (en) * | 2020-09-15 | 2020-12-08 | 李得正 | Flight control device and control method of bionic bird aircraft |
-
2015
- 2015-04-10 CN CN201520211406.4U patent/CN204527635U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104787331A (en) * | 2015-04-10 | 2015-07-22 | 张晓赫 | Double-wing ornithopter provided with controllable buoyancy wings and power wings and operation method of double-wing ornithopter |
| CN112046743A (en) * | 2020-09-15 | 2020-12-08 | 李得正 | Flight control device and control method of bionic bird aircraft |
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