CN205221094U - Big unmanned fixed wing aircraft of aspect ratio - Google Patents
Big unmanned fixed wing aircraft of aspect ratio Download PDFInfo
- Publication number
- CN205221094U CN205221094U CN201520836037.8U CN201520836037U CN205221094U CN 205221094 U CN205221094 U CN 205221094U CN 201520836037 U CN201520836037 U CN 201520836037U CN 205221094 U CN205221094 U CN 205221094U
- Authority
- CN
- China
- Prior art keywords
- wing
- reinforced rib
- pipe link
- slave
- mounting hole
- 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
Links
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The utility model provides a pair of big unmanned fixed wing aircraft of aspect ratio, including the aircraft, the aircraft include the fuselage, wing and tail, the wing includes the host computer wing, host computer wing both ends are equipped with the auxiliary engine wing, the tail includes the elevator, the rudder, horizontal tail and vertical fin, moreover, the steam generator is simple in structure, and reasonable design, increase wing intensity and rigidity in the wing weight that is not markedly increased, the wing is great, the performance of leaving a blank is good, it is chronic to leave a blank, and the present invention has higher safety, the stress is more even, be difficult to produce the phenomenon of rupture, the installed and disassembled of being convenient for, the operation is thus simple, portable is in the maintenance, the service life of it is whole is prolonged, wider applicability is realized.
Description
Technical field
The utility model relates to vehicle technology field, particularly the unmanned Fixed Wing AirVehicle of a kind of high aspect ratio.
Background technology
Aircraft is the apparatus flyer in endoatmosphere or exoatmosphere spaceflight being manufactured by the mankind, can fly away from ground, control in spaceflight and by people.Be called aerocraft in endoatmosphere flight, be called spacecraft in space flight.And the aircraft that aspect ratio is large, performance of leaving a blank will be got well.Covering skeleton type fixed-wing unmanned vehicle mostly is girder structure, and rib trailing edge easily ruptures, cause In-Flight Performance decline even aircraft damage, without reinforcing rib design, cause wing Stiffness, easy torsional deflection.High aspect ratio fixed-wing unmanned vehicle mostly is standard aerofoil profile, shows each variant in a practical situation.Multi element wing many employings rigid connection, as bolt etc., is inconvenient to dismantle.
Utility model content
Problem to be solved in the utility model is to provide the unmanned Fixed Wing AirVehicle of a kind of high aspect ratio, solve the aircraft that aspect ratio is large, performance of leaving a blank will be got well, covering skeleton type fixed-wing unmanned vehicle mostly is girder structure, rib trailing edge easily ruptures, cause In-Flight Performance decline even aircraft damage, without reinforcing rib design, cause wing Stiffness, easy torsional deflection, high aspect ratio fixed-wing unmanned vehicle mostly is standard aerofoil profile, show each variant in a practical situation, multi element wing many employings rigid connection, as bolt etc., inconvenient dismounting problem.
For overcoming the above problems the scheme that the utility model adopts:
The unmanned Fixed Wing AirVehicle of a kind of high aspect ratio, comprise aircraft, described aircraft comprises fuselage, wing and tail, described wing comprises host wing, host wing two ends are provided with the slave wing, described host wing is provided with the first reinforced rib mounting hole, second reinforced rib mounting hole, main slotting mounting hole and host wing spar, described host wing spar is provided with locating dowel pin mounting hole, described host wing one end is provided with the first leading edge carbon beam, the other end is provided with the first trailing edge carbon beam, the described slave wing is provided with the first reinforced rib pipe link, second reinforced rib pipe link and secondary wing spar, described secondary wing spar is provided with main slotting pipe link, described master inserts pipe link and is provided with draw-in groove, described draw-in groove by the locating dowel pin mounting hole on locating dowel pin and host wing spar with the use of, the first reinforced rib pipe link on the described slave wing and the first reinforced rib mounting hole on host wing with the use of, the second reinforced rib pipe link on the slave wing and the second reinforced rib mounting hole on host wing with the use of, described slave wing one end is provided with the second leading edge carbon beam, the other end is provided with the second trailing edge carbon beam, described tail comprises elevating rudder, yaw rudder, horizontal tail and vertical fin.
The above-mentioned unmanned Fixed Wing AirVehicle of a kind of high aspect ratio, wherein, described host wing comprises the thriving block of main frame, and the slave wing comprises the thriving block of slave, and the thriving block of described main frame is identical with slave thriving block size shape.
The above-mentioned unmanned Fixed Wing AirVehicle of a kind of high aspect ratio, wherein, described wing length is 2600mm, and fuselage length is 1200mm.
The above-mentioned unmanned Fixed Wing AirVehicle of a kind of high aspect ratio, wherein, the first described reinforced rib pipe link, the second reinforced rib pipe link, main slotting pipe link and locating dowel pin are rectangular configuration.
The above-mentioned unmanned Fixed Wing AirVehicle of a kind of high aspect ratio, wherein, described wing is provided with one deck covering.
The beneficial effect of this programme:
The unmanned Fixed Wing AirVehicle of a kind of high aspect ratio that the utility model provides, structure is simple, reasonable in design, reinforcing rib design, wing strength and stiffness are increased while obviously not increasing wing weight, wing is larger, performance of leaving a blank is good, airborne period is long, the first reinforced rib pipe link when mounted on the slave wing and the second reinforced rib pipe link achieve a fixed connection through the first reinforced rib mounting hole on host wing and the second reinforced rib mounting hole, master on secondary wing spar inserts pipe link and inserts mounting hole through main, by orienting pin, master is inserted pipe link locked, safety is higher, overall stressed more even, be not easy to produce the phenomenon fractureed, be convenient to install and remove, simple to operate, be easy to carry in maintenance, improve overall service life, applicability is wider.
Accompanying drawing explanation
Fig. 1 is the utility model integral structure figure.
Fig. 2 is the utility model host wing and slave wing structure figure.
Fig. 3 is the utility model host wing constructional drawing.
Fig. 4 is the utility model slave wing structure figure.
Detailed description of the invention
As shown in the figure, the unmanned Fixed Wing AirVehicle of a kind of high aspect ratio, comprise aircraft 1, described aircraft 1 comprises fuselage 2, wing 3 and tail 4, described wing 3 comprises host wing 5, host wing 5 two ends are provided with the slave wing 6, described host wing 5 is provided with the first reinforced rib mounting hole 7, second reinforced rib mounting hole 8, main slotting mounting hole 9 and host wing spar 10, described host wing spar 10 is provided with locating dowel pin mounting hole 11, described host wing 5 one end is provided with the first leading edge carbon beam 12, the other end is provided with the first trailing edge carbon beam 13, the described slave wing 6 is provided with the first reinforced rib pipe link 14, second reinforced rib pipe link 15 and secondary wing spar 16, described secondary wing spar 16 is provided with main slotting pipe link 17, described master inserts pipe link 17 and is provided with draw-in groove 18, described draw-in groove 18 by locating dowel pin 19 and the locating dowel pin mounting hole 11 on host wing spar 10 with the use of, the first reinforced rib pipe link 14 on the described slave wing 6 and the first reinforced rib mounting hole 7 on host wing with the use of, the second reinforced rib pipe link 15 on the slave wing and the second reinforced rib mounting hole 8 on host wing with the use of, the described slave wing 6 one end is provided with the second leading edge carbon beam 20, the other end is provided with the second trailing edge carbon beam 21, described tail 4 comprises elevating rudder 22, yaw rudder 23, horizontal tail 24 and vertical fin 25, described host wing 5 comprises the thriving block 26 of main frame, the slave wing 6 comprises the thriving block 27 of slave, the thriving block of described main frame 26 is identical with slave thriving block 27 size shape, described wing 3 length is 2600mm, fuselage 4 length is 1200mm, the first described reinforced rib pipe link 14, second reinforced rib pipe link 15, main pipe link 17 of inserting is rectangular configuration with locating dowel pin 19, described wing 3 is provided with one deck covering 28.
The unmanned Fixed Wing AirVehicle of a kind of high aspect ratio that the utility model provides, structure is simple, reasonable in design, reinforcing rib design, wing strength and stiffness are increased while obviously not increasing wing weight, wing is larger, performance of leaving a blank is good, airborne period is long, the first reinforced rib pipe link when mounted on the slave wing and the second reinforced rib pipe link achieve a fixed connection through the first reinforced rib mounting hole on host wing and the second reinforced rib mounting hole, master on secondary wing spar inserts pipe link and inserts mounting hole through main, by orienting pin, master is inserted pipe link locked, safety is higher, overall stressed more even, be not easy to produce the phenomenon fractureed, be convenient to install and remove, simple to operate, be easy to carry in maintenance, improve overall service life, applicability is wider.
Be only the utility model preferably detailed description of the invention; but protection domain of the present utility model is not limited thereto; anyly be familiar with those skilled in the art in the technical scope that the utility model discloses; the change that can expect easily or replacement, all should be encompassed in protection domain of the present utility model.Therefore, protection domain of the present utility model should be as the criterion with the protection domain of claims.
Claims (5)
1. the unmanned Fixed Wing AirVehicle of high aspect ratio, comprise aircraft, it is characterized by, described aircraft comprises fuselage, wing and tail, described wing comprises host wing, host wing two ends are provided with the slave wing, described host wing is provided with the first reinforced rib mounting hole, second reinforced rib mounting hole, main slotting mounting hole and host wing spar, described host wing spar is provided with locating dowel pin mounting hole, described host wing one end is provided with the first leading edge carbon beam, the other end is provided with the first trailing edge carbon beam, the described slave wing is provided with the first reinforced rib pipe link, second reinforced rib pipe link and secondary wing spar, described secondary wing spar is provided with main slotting pipe link, described master inserts pipe link and is provided with draw-in groove, described draw-in groove by the locating dowel pin mounting hole on locating dowel pin and host wing spar with the use of, the first reinforced rib pipe link on the described slave wing and the first reinforced rib mounting hole on host wing with the use of, the second reinforced rib pipe link on the slave wing and the second reinforced rib mounting hole on host wing with the use of, described slave wing one end is provided with the second leading edge carbon beam, the other end is provided with the second trailing edge carbon beam, described tail comprises elevating rudder, yaw rudder, horizontal tail and vertical fin.
2. the unmanned Fixed Wing AirVehicle of a kind of high aspect ratio as claimed in claim 1, is characterized by, and described host wing comprises the thriving block of main frame, and the slave wing comprises the thriving block of slave, and the thriving block of described main frame is identical with slave thriving block size shape.
3. the unmanned Fixed Wing AirVehicle of a kind of high aspect ratio as claimed in claim 1, is characterized by, and described wing length is 2600mm, and fuselage length is 1200mm.
4. the unmanned Fixed Wing AirVehicle of a kind of high aspect ratio as claimed in claim 1, is characterized by, and the first described reinforced rib pipe link, the second reinforced rib pipe link, main slotting pipe link and locating dowel pin are rectangular configuration.
5. the unmanned Fixed Wing AirVehicle of a kind of high aspect ratio as claimed in claim 1, it is characterized by, described wing is provided with one deck covering.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520836037.8U CN205221094U (en) | 2015-10-27 | 2015-10-27 | Big unmanned fixed wing aircraft of aspect ratio |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520836037.8U CN205221094U (en) | 2015-10-27 | 2015-10-27 | Big unmanned fixed wing aircraft of aspect ratio |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205221094U true CN205221094U (en) | 2016-05-11 |
Family
ID=55896176
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520836037.8U Expired - Fee Related CN205221094U (en) | 2015-10-27 | 2015-10-27 | Big unmanned fixed wing aircraft of aspect ratio |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205221094U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105270603A (en) * | 2015-10-27 | 2016-01-27 | 镇江顺宇飞行器有限公司 | Unmanned fixed-wing aircraft with large aspect ratio |
-
2015
- 2015-10-27 CN CN201520836037.8U patent/CN205221094U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105270603A (en) * | 2015-10-27 | 2016-01-27 | 镇江顺宇飞行器有限公司 | Unmanned fixed-wing aircraft with large aspect ratio |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106061841A (en) | Engine pylon structure | |
| CN203958601U (en) | The I-shaped beam type airframe structure of depopulated helicopter | |
| BR102014009274B1 (en) | Winglet attachment connection for attaching a broken winglet to a wing and aircraft | |
| CN204399465U (en) | A kind of anury all-wing aircraft many controlsurfaces unmanned plane | |
| CN204433041U (en) | Vehicle rudder drive mechanism | |
| CN106585982A (en) | Combined type micro air vehicle driven by flapping wings | |
| CN105398561A (en) | Solar aircraft | |
| CN105270603A (en) | Unmanned fixed-wing aircraft with large aspect ratio | |
| US9056671B2 (en) | Fixed wing of an aircraft | |
| CN103204236B (en) | Multi-purpose plug-in device for helicopter | |
| CN105857579A (en) | Propeller airplane | |
| CN202429344U (en) | Unmanned aerial vehicle | |
| CN104943850A (en) | Main wing retractable type fixed wing airplane | |
| CN205221094U (en) | Big unmanned fixed wing aircraft of aspect ratio | |
| CN102963521A (en) | Central wing of horizontal tail of civil airplane | |
| US8888039B2 (en) | Method and device for the lateral stabilization of an aircraft | |
| US8740139B1 (en) | Leading edge snag for exposed propeller engine installation | |
| CN218112970U (en) | Winglet connection structure and wingtip winglet and unmanned aerial vehicle using same | |
| CN107512382A (en) | One kind combination aircraft | |
| CN102849218A (en) | Mounting beam for auxiliary power unit of aircraft | |
| CN103538717A (en) | Aircraft lifting surface with variable sweep distribution along the span | |
| CN102765472B (en) | Modular connection device for airplane body | |
| CN202506125U (en) | Quick-dismounting structure for wings | |
| CN202879789U (en) | Petrol-electric hybrid type unmanned aerial vehicle | |
| CN205406707U (en) | Aircraft antenna setting support and quick -witted connection structure who carries on back |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160511 Termination date: 20181027 |