CN201745748U - Bionic aircraft - Google Patents
Bionic aircraft Download PDFInfo
- Publication number
- CN201745748U CN201745748U CN2010205156812U CN201020515681U CN201745748U CN 201745748 U CN201745748 U CN 201745748U CN 2010205156812 U CN2010205156812 U CN 2010205156812U CN 201020515681 U CN201020515681 U CN 201020515681U CN 201745748 U CN201745748 U CN 201745748U
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- CN
- China
- Prior art keywords
- wing
- frame
- air
- spine
- air bag
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Abstract
The utility model discloses a bionic aircraft, which comprises a backbone frame, wing frames which are respectively arranged on the two sides of the middle part of the backbone frame and extend outward, support frames which are arranged along the longitudinal direction of the backbone frame, and braces, wherein the middle part of the backbone frame is provided with a cabin, and the cabin is internally provided with an outer air chamber, an air pump, a storage battery and an electromagnet; the power output end of the storage battery is respectively electrically connected with the power input ends of the electromagnet and the air pump; the air outlet of the air pump is communicated with the outer air chamber through an exhaust one-way valve; the outer air chamber is internally provided with an inner elastic air bag, and the inner elastic air bag is respectively communicated with a backbone frame elastic pipe, a wing frame elastic pipe and a brace elastic pipe; a vacuum elastic leather-covered bag positioned on the wing support is internally provided with two strings of air bags and a magnetic plate, a wing bag is communicated with the balance air bag, and the inner cavity of the balance air bag is communicated with external air through the exhaust one-way valve. The utility model has the advantages that compared with the traditional aircraft, since the action of the wing is opposite to the direction of motion of the aircraft, the bionic aircraft can fly like living beings and can fly in a direct and effective way.
Description
Technical field
The utility model relates to aircraft, especially relates to bionical flight.
Background technology
Present aircraft such as aircraft, flight dynamic devices mostly is air engine.Draw the oxidizer that air acts as a fuel and burns by air engine, promote fuselage and do sporting flying.And the biological aircraft as the bionical flight of birds dependence wing flapping wing of imitation flight is also rare at present.
Summary of the invention
The utility model purpose is to provide a kind of flapping wings type bionic Aircraft.
For achieving the above object, the utility model can be taked following technical proposals:
Bionic Aircraft described in the utility model, it comprises spine, is separately positioned on the wing frame that outwards stretch both sides, described spine middle part, vertically is arranged on the bracing frame of its both sides and leg frame along spine; Spine is by spring tube and be serially connected in the ridge piece that more piece middle part on the described spring tube has a through hole and constitute; Described wing frame is made of by the spring tube serial connection at least two joint wing bars; Described leg frame is made of by the spring tube serial connection two to three joint poles; One end of wing frame is hinged with cooresponding bracing frame upper end respectively, and an end of leg frame joins mutually with cooresponding bracing frame bottom respectively; Spine, bracing frame, wing frame, leg frame respectively sealing shroud be loaded on the corresponding vacuum elasticity of its shape covering capsule in; Be provided with the cabin, air chamber, air pump, storage battery, electromagnet outside in described cabin, being provided with at the spine middle part; Described battery feed mouth is connected with air pump, electromagnet power supply input outage respectively; The air pump air extractor duct is connected with outer air chamber by check valve; Be provided with air bag in the elasticity outside in the air chamber, air bag is connected with spine spring tube, wing frame spring tube, leg frame spring tube respectively in the described elasticity; Bracing frame is provided with magnetic sheet; Be provided with two string capsules and magnetic sheet at the vacuum elasticity covering capsule that is positioned at wing frame, wherein a string capsule communicates with air bag in the elasticity; The admission port of another string capsule is connected with outer air chamber by check valve, the air extractor duct wing envelope interior with being arranged on wing frame root vacuum elasticity covering capsule communicates, wing envelope is connected with balance air bag in being arranged on bracing frame position vacuum elasticity covering capsule by one-way exhaust valve, and described balance air bag inner chamber communicates with atmosphere by exhaust check valve.
Be provided with solar panel at described spine upper surface, wing frame upper surface; Described storage battery is a chargeable storage; Described solar panel power output end is electrically connected with described chargeable storage charging end by mu balanced circuit.
The utility model advantage is to compare with conventional aircraft, because of the application force of wing is opposite with the aircraft movements direction, can be biological as flight, and with the most direct effective and efficient manner flight.Inflate by controlling in the string capsule that described air pump communicates with it in described wing frame vacuum elasticity covering capsule, when air pressure during greater than the spring tube internal gas pressure that is serially connected in the wing bar, wing frame upwards launches, when air pressure reaches setting value, the one-way exhaust valve that is communicated with wing envelope and balance air bag is opened exhaust in balance air bag, when this string capsule internal gas pressure less than another during with string capsule that air bag in the elasticity communicates, the contraction of calming the anger downwards of wing frame; When this string capsule internal gas pressure dropped to the one-way exhaust valve close value that is communicated with wing envelope and balance air bag, this string capsule internal gas pressure rose when one-way exhaust valve was closed, and wing frame upwards launches again.Said process goes round and begins again to realize flapping flight.Control the switching electricity of described electromagnet, the magnetic force by its generation makes the magnetic sheet that is arranged on the bracing frame push, decontrol described balance air bag, adjusts the flight attitude of empennage.Therefore, save a large amount of transmissions, speed reduction gearing, alleviated the aircraft deadweight, improved airworthiness.Be provided with solar panel at described spine upper surface, wing frame upper surface; And described solar panel power output end is electrically connected with described chargeable storage charging end by mu balanced circuit, can utilize solar power to improve flying power of the present utility model like this.
Description of drawings
Fig. 1 is a structural representation of the present utility model.
Fig. 2 is a cabin described in the utility model vertical profile structural representation.
Fig. 3 is a local structure for amplifying scheme drawing of the present utility model.
The specific embodiment
As shown in Figure 1, 2, 3, bionic Aircraft described in the utility model, it comprises spine 1, is separately positioned on the wing frame 2,3 that outwards stretch both sides, described spine 1 middle part, vertically is arranged on the bracing frame 4,5 of its both sides and leg frame 6,7 along spine 1; Spine 1 is by spring tube and be serially connected in the ridge piece that more piece middle part on the described spring tube has a through hole and constitute; Described wing frame 2,3 is made of by the spring tube serial connection at least two joint wing bars; Described leg frame 6,7 is made of by the spring tube serial connection two to three joint poles; One end of wing frame 2,3 is hinged with cooresponding bracing frame 4,5 upper ends respectively, and an end of leg frame 6,7 joins mutually with cooresponding bracing frame 4,5 bottoms respectively; Described spine 1, bracing frame 4,5, wing frame 2,3, leg frame 6,7 respectively sealing shroud be loaded on the corresponding vacuum elasticity of its shape covering capsule in; Be provided with cabin 8 at spine 1 middle part, air chamber 9, air pump 10, storage battery 11, electromagnet 12 outside in described cabin 8, being provided with; Described storage battery 11 power output ends are connected with air pump 10, electromagnet 12 power supplys input outage respectively; Air pump 10 air extractor ducts are connected with outer air chamber 9 by check valve; Be provided with air bag 13 in the elasticity outside in the air chamber 9, air bag 13 is connected with spine 1 spring tube, wing frame 2,3 spring tubes, leg frame 6,7 spring tubes respectively in the described elasticity; Bracing frame 4,5 is provided with magnetic sheet; Be provided with two capsule 14,15 magnetic sheets 18 of collaborating at the vacuum elasticity covering capsule that is positioned at wing frame 2,3, wherein a string air bag 14 communicates with air bag 13 in the elasticity; The admission port of another capsule 15 of collaborating is connected with outer air chamber 9 by check valve, the air extractor duct wing envelope 16 interior with being arranged on wing frame 3 root vacuum elasticity covering capsules communicates, wing envelope 16 is connected with balance air bag 17 in being arranged on bracing frame 4,5 position vacuum elasticity covering capsules by one-way exhaust valve, and described balance air bag 17 inner chambers communicate with atmosphere by exhaust check valve.Be provided with solar panel at described spine 1 upper surface, wing frame 2,3 upper surfaces; Described storage battery 11 is a chargeable storage; Described solar panel power output end is electrically connected with described chargeable storage charging end by mu balanced circuit.
Claims (2)
1. bionic Aircraft, it is characterized in that: it comprises spine (1), be separately positioned on the wing frame (2,3) that outwards stretch both sides, described spine (1) middle part, vertically be arranged on the bracing frame (4,5) of its both sides and leg frame (6,7) along spine (1); Spine (1) is by spring tube and be serially connected in the ridge piece that more piece middle part on the described spring tube has a through hole and constitute; Described wing frame (2,3) is made of by the spring tube serial connection at least two joint wing bars; Described leg frame (6,7) is made of by the spring tube serial connection two to three joint poles; One end of wing frame (2,3) is hinged with cooresponding bracing frame (4,5) upper end respectively, and an end of leg frame (6,7) joins mutually with cooresponding bracing frame (4,5) bottom respectively; Described spine (1), bracing frame (4,5), wing frame (2,3), leg frame (6,7) respectively sealing shroud be loaded on the corresponding vacuum elasticity of its shape covering capsule in; Be provided with cabin (8), air chamber (9), air pump (10), storage battery (11), electromagnet (12) outside in described cabin (8), being provided with at spine (1) middle part; Described storage battery (11) power output end is connected with air pump (10), electromagnet (12) power supply input outage respectively; Air pump (10) air extractor duct is connected with outer air chamber (9) by check valve; Be provided with air bag (13) in the elasticity outside in the air chamber (9), air bag (13) is connected with spine (1) spring tube, wing frame (2,3) spring tube, leg frame (6,7) spring tube respectively in the described elasticity; Bracing frame (4,5) is provided with magnetic sheet; Be provided with two capsule (14, the 15) magnetic sheets (18) of collaborating at the vacuum elasticity covering capsule that is positioned at wing frame (2,3), wherein a string air bag (14) communicates with air bag (13) in the elasticity; The admission port of another capsule of collaborating (15) is connected with outer air chamber (9) by check valve, the air extractor duct wing envelope (16) interior with being arranged on wing frame (3) root vacuum elasticity covering capsule communicates, wing envelope (16) is connected by the one-way exhaust valve balance air bag (17) interior with being arranged on bracing frame (4,5) position vacuum elasticity covering capsule, and described balance air bag (17) inner chamber communicates with atmosphere by exhaust check valve.
2. bionic Aircraft according to claim 1 is characterized in that: be provided with solar panel at described spine (1) upper surface, wing frame (2,3) upper surface; Described storage battery (11) is a chargeable storage; Described solar panel power output end is electrically connected with described chargeable storage charging end by mu balanced circuit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010205156812U CN201745748U (en) | 2010-09-03 | 2010-09-03 | Bionic aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010205156812U CN201745748U (en) | 2010-09-03 | 2010-09-03 | Bionic aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201745748U true CN201745748U (en) | 2011-02-16 |
Family
ID=43580420
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010205156812U Expired - Fee Related CN201745748U (en) | 2010-09-03 | 2010-09-03 | Bionic aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201745748U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102602537A (en) * | 2012-03-31 | 2012-07-25 | 西北工业大学 | Micro flapping rotor aircraft |
| CN111099016A (en) * | 2018-10-25 | 2020-05-05 | 青岛海洋科学与技术国家实验室发展中心 | Bionic flapping wing system and bionic flapping wing robot |
-
2010
- 2010-09-03 CN CN2010205156812U patent/CN201745748U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102602537A (en) * | 2012-03-31 | 2012-07-25 | 西北工业大学 | Micro flapping rotor aircraft |
| CN111099016A (en) * | 2018-10-25 | 2020-05-05 | 青岛海洋科学与技术国家实验室发展中心 | Bionic flapping wing system and bionic flapping wing robot |
| CN111099016B (en) * | 2018-10-25 | 2021-05-14 | 青岛海洋科学与技术国家实验室发展中心 | Bionic flapping wing system and bionic flapping wing robot |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110216 Termination date: 20120903 |