CN205652335U - Oil of big load ratio moves fixed -wing aircraft - Google Patents
Oil of big load ratio moves fixed -wing aircraft Download PDFInfo
- Publication number
- CN205652335U CN205652335U CN201620448891.1U CN201620448891U CN205652335U CN 205652335 U CN205652335 U CN 205652335U CN 201620448891 U CN201620448891 U CN 201620448891U CN 205652335 U CN205652335 U CN 205652335U
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- Prior art keywords
- wing
- underbeam
- oil
- upper beam
- heavy
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Abstract
The utility creatively provides an oil of big load ratio moves fixed -wing aircraft, the reciprocating impact tunnel drilling machine comprises a machine body, fore -body both sides symmetry respectively are provided with a wing, the wing comprises with the mask who sets up in roof beam box front side the roof beam box, the roof beam box includes upper beam, underbeam and web, the roof beam box is inside to be located between upper beam and the underbeam and to hug closely the web and locate evenly to be provided with bracing and pillar, the fore -body downside is provided with the load compartment, the front portion of load compartment lower extreme is provided with the nose -gear, the middle part of load compartment lower extreme is provided with the main landing gear, the load compartment lower part is provided with the hatch door, the fuselage rear portion is provided with tailplane and vertical tail. The utility model discloses create oil of big load ratio moves fixed -wing aircraft structural design reasonable, the wholeness can be good, have good oneself's stability and flight operating characteristic, empty quick -witted structure light in weight, fivefold that the load can nearly be conducted oneself with dignity, and low in manufacturing cost, processing technology is simple.
Description
Technical field
The invention belongs to aircraft manufacturing technical field, and the oil especially relating to a kind of heavy－duty ratio is dynamic solid
Determine wing aircraft.
Background technology
Along with flying to control the development of electronic technology, use ground control cabinet realize complete autonomous or half autonomous landing and
The unmanned plane of flight obtains fast development in recent years, and all kinds of novel unmanned plane numbers of plies are not poor, a hundred flowers blossom,
But the existing most bare weight of loading unmanned plane is relatively big, and load-carrying is smaller, causes loading inefficient,
This optimization and improvement of being accomplished by carrying out structure on the basis of existing unmanned plane.
Summary of the invention
In view of this, the invention is directed to the oil of a kind of heavy－duty ratio and moves fixed wing airplane, to solve
Certainly existing loading unmanned plane bare weight is relatively big, the problem that load-carrying is smaller.
For reaching above-mentioned purpose, the technical scheme of the invention is achieved in that
The oil of a kind of heavy－duty ratio moves fixed wing airplane, and including fuselage, described fore-body both sides are the most right
Claiming to be provided with a wing, described wing is made up of beam box and the mask being covered in beam box upper surface, described
Beam box includes that upper beam, underbeam and web, described upper beam are arranged at above described underbeam, and described upper beam with
Being provided with gap between described underbeam, described web is arranged at two sides before and after described upper beam and underbeam
On, described beam box is internally located between upper beam and underbeam and is close at web be evenly arranged with diagonal brace and prop up
Post；Being provided with attachment lug at the wing root of described wing, described attachment lug side is provided with lug, institute
State and on fuselage, be provided with the draw-in groove matched with described lug, between described lug and draw-in groove by bolt even
Connect；Being provided with load compartment on the downside of described fore-body, the top of described load compartment is connected with the wing root of wing,
Described load compartment is to be formed by carbon fiber bar overlap joint, rises and falls before being provided with in the front portion of described load compartment lower end
Frame, the middle part of described load compartment lower end is provided with main landing gear, and described load compartment bottom is provided with hatch door；
Described fuselage afterbody is provided with tailplane and vertical tail.
Further, described upper beam and underbeam are Lignum paulowniae, and the lower surface of described upper beam and underbeam is respectively provided with
There is the groove extended along wing length direction, in described groove, be provided with steel wire rope, described upper beam and underbeam
Upper and lower surface be all enclosed with carbon cloth.
Further, described upper beam and underbeam are the trapezium structure of slightly taper in width from wing root to the wing, institute
The thickness stating upper beam is 8mm, and the thickness of described underbeam is 5mm.
Further, described web is cork wood, and described web is slightly tapered trapezoidal of thickness from wing root to the wing
Structure, described mask slightly thickness from wing root to the wing reduces, and the wing of described mask is slightly located as hollow out shape.
Further, described beam box is internally located between upper beam and underbeam and is close at web be evenly arranged with
Diagonal brace and pillar, diagonal brace and pillar at the internal close wing root of described beam box use Lignum paulowniae, slightly locate near the wing
Diagonal brace and pillar use cork wood.
Further, described vertical tail uses balsa wood material to make.
Further, described tailplane is slightly trapezoidal layout to the wing by wing root.
Further, described fuselage is to the most thicker trapezoidal shape of head by tail, described fuselage
Four faces are disposed as plane up and down, and described fuselage includes four girders and is arranged between girder
Corbeling, described corbeling uses cork wood to make.
Further, described load compartment is to be formed by carbon fiber bar overlap joint.
Further, the outside of described fuselage, wing, load compartment, vertical tail and tailplane is all wrapped
Being wrapped with one layer of eyelid covering, described eyelid covering uses heat shrinkage film to make.
Relative to prior art, the oil of the heavy－duty ratio described in the invention move fixed wing airplane have with
Lower advantage:
1, reasonable in design, overall performance is good, aeroplane span 4.5 meters, and bare weight 3Kg uses
3.5cc methanol engine, rated speed 37500r/min, it is equipped with 23 cun of Zelkova schneideriana Hand.-Mazz. propellers, working speed
5000r/min, has good self-stability and aircraft handling characteristics, empty machine lightweight construction, load-carrying
Up to five times of deadweight, and low cost of manufacture, processing technique is simple；
2, full dynamic formula horizontal tail is used, the flaperon of larger area, may act as again ground spoiler during landing,
Complete machine has the mobility of height, full load flight speed 45km/h, min. turning radius 40 meters,
Angle of climbing greatly 40 °, full-loaded takeoff distance 30 meters, empty machine landing run is minimum is only 3
Rice, high-strength mobility and lifting capacity are mainly directed towards under the intensive situation of the flight environment of vehicle such as mountain area, city
Short distance goods transport.
Accompanying drawing explanation
The accompanying drawing of the part constituting the invention is used for providing being further appreciated by the invention,
The schematic description and description of the invention is used for explaining the invention, is not intended that this
The improper restriction of bright creation.In the accompanying drawings:
Fig. 1 is the front view of the invention；
Fig. 2 is the side view of the invention；
Fig. 3 is the side view of beam box；
Fig. 4 is the front view of mask；
Fig. 5 is the front view of attachment lug.
Description of reference numerals:
1-fuselage；2-wing；21-beam box；211-upper beam；212-underbeam；213-web；214-steel
Cord；22-mask；3-tailplane；4-vertical tail；5-load compartment；6-nose-gear；7-master
Undercarriage；8-attachment lug；81-lug；82-lightening hole.
Detailed description of the invention
It should be noted that in the case of not conflicting, in embodiment in the invention and embodiment
Feature can be mutually combined.
In the description of the invention, it is to be understood that term " " center ", " longitudinally ", " horizontal stroke
To ", " on ", D score, "front", "rear", "left", "right", " vertically ", " water
Flat ", the orientation that indicates of " top ", " end ", " interior ", " outward " etc. or position relationship be based on attached
Orientation shown in figure or position relationship, be for only for ease of description the invention and simplify description, and not
Be instruction or the hint device of indication or element must have specific orientation, with specific azimuth configuration and
Operation, therefore it is not intended that restriction to the invention.Additionally, term " first ", " second "
Etc. being only used for describing purpose, and it is not intended that instruction or hint relative importance or implicit indicate indication
The quantity of the technical characteristic shown.Thus, the feature defining " first ", " second " etc. can be expressed
Or implicitly include one or more this feature.In the description of the invention, unless otherwise
Illustrating, " multiple " are meant that two or more.
In the description of the invention, it should be noted that unless otherwise clearly defined and limited,
Term " is installed ", " being connected ", " connection " should be interpreted broadly, and connects for example, it may be fixing,
Can also be to removably connect, or be integrally connected；Can be to be mechanically connected, it is also possible to be electrical connection；
Can be to be joined directly together, it is also possible to be indirectly connected to by intermediary, can be the company of two element internals
Logical.For the ordinary skill in the art, can understand that above-mentioned term is at this by concrete condition
Concrete meaning in innovation and creation.
Describe the invention below with reference to the accompanying drawings and in conjunction with the embodiments in detail.
As Figure 1-5, the oil of a kind of heavy－duty ratio moves fixed wing airplane, including fuselage 1, described machine
Body 1 is that four faces up and down of described fuselage 1 are equal to the most thicker trapezoidal shape of head by tail
Being set to plane, described fuselage 1 includes four girders and the corbeling being arranged between girder, described
Corbeling uses cork wood to make, and has preferable bending resistance, antitorque function and weight loss effect；
Described fuselage 1 front part sides is respectively symmetrically and is provided with a wing 2, and described wing 2 is by beam box 21
Be covered in beam box 21 upper surface mask 22 constitute, described beam box 21 includes upper beam 211, underbeam
212 and web 213, described upper beam 211 is arranged at above described underbeam 212, and described upper beam 211
And being provided with gap between described underbeam 212, described web 213 is arranged at described upper beam 211 and underbeam
Before and after 212 on two sides, described beam box 21 is internally located between upper beam 211 and underbeam 212 and is close to
Be evenly arranged with diagonal brace and pillar at web 213, the internal diagonal brace at wing root of described beam box 21 and
Pillar uses Lignum paulowniae, and the diagonal brace slightly located near the wing and pillar use cork wood, and box structure beam has well
Bending resistance, shearing resistance, antitorque function, the transmission of the whole lift of aircraft wing in flight course, maneuvering flight
Time overload, especially during full-load run, all of power all concentrates at wing root girder, and the design of spar is several
Determine the strength character of aircraft completely；
According to material mechanics principle, wing is awing primarily subjected to pressure, and underbeam bears pulling force, length
Bigger beam element structure, although the generally compressive property of material is better than tensile property, and test proves upper beam
211 are easier to occur unstability to fracture, so upper beam 211 uses the Lignum paulowniae that 8mm is thick, underbeam 212 uses
The Lignum paulowniae that 5mm is thick, described upper beam 211 and underbeam 212 are from wing root to the wing the trapezoidal of slightly taper in width
Structure；
The lower surface of described upper beam 211 and underbeam 212 is carved with the groove extended along wing length direction,
Being provided with steel wire rope 214 in described groove, the neutral gear part wood flour in groove tamps, and then penetrates into glue
Water, wood flour hardens, steel wire rope 214 can the most embedding in a groove, relatively big according to wing root portion stress,
The feature that the wing slightly stress is less, is imbedding two steel wire ropes near wingstub, is imbedding a steel at interlude
Cord, no longer imbeds near the wing slightly section, after embedment steel wire rope, at described upper beam 211 and underbeam 212
Upper and lower surface all wraps up one layer of carbon cloth, is adhered to surface with glue, increases upper beam 211 and underbeam 212
Intensity；
Described web 213 is cork wood, and described web 213 is the trapezoidal knot that slightly thickness is tapered from wing root to the wing
Structure, and the wing of described web 213 slightly section is hollow out shape, described mask 22 slightly thickness from wing root to the wing subtracts
Contract, and the wing of described mask 22 is slightly located as hollow out shape；
The attachment lug 8 of aluminum alloy material, described attachment lug 8 it is provided with at the wing root of described wing 2
Side is provided with lug 81, and described fuselage 1 is provided with the draw-in groove matched with described lug 81, institute
Stating and be bolted between lug 81 and draw-in groove, described attachment lug 8 is additionally provided with lightening hole 82；
Described fuselage 1 underside of forward is provided with load compartment 5, the top of described load compartment 5 and wing 2
Wing root is connected, and described load compartment 5 is to be formed by carbon fiber bar overlap joint, and carbon fiber bar has light weight, ratio
The feature that intensity is high, varies in size according to diverse location stress and selects the carbon fiber bar of respective diameters, reach
Optimal Intensity Design；
The front portion of described load compartment 5 lower end is provided with nose-gear 6, and it is sliding that nose-gear is used primarily in aircraft
Turning to during row, shock-absorbing function, itself also have subtract pendulum and the most fixed in function, the design uses 56mm
The foam tire of diameter, light weight and have good shock-absorbing function, course changing control mechanism uses a number
Word steering wheel, and rudder of aircraft steering wheel mixing, when remote controller steering rudder turns to, nose-gear is simultaneously
Turning to, described nose-gear is arranged on undercarriage leg, and undercarriage leg is 12mm diameter fluid bullet
Spring formula shock strut, spring plays cushioning effect to clashing into kinetic energy, and described shock strut is by inner core and urceolus
Constituting, hydraulic oil is absorbed by the throttle orifice of inner core and clashes into kinetic energy, can mutually rotate between inner/outer tube,
Urceolus is fixed on aircaft configuration, and inner core connects nose-gear wheel down, overlaps one again and live outside urceolus
Moving sleeve, it is connected at the wheel of inner core lower end by an anti-twisted arm configuration, and servos control is in addition just
Sleeve transmits moment of torsion by anti-twisted arm, drives front-wheel steer；
The middle part of described load compartment 5 lower end is provided with main landing gear 7, and described load compartment 5 bottom is provided with
Hatch door；
Described fuselage 1 rear portion is provided with tailplane 3 and vertical tail 4, described vertical tail 4 and water
The horizontal tail wing 3 all uses balsa wood material to make, and tailplane 3 is all-moving tail, uses conventional
NACA0012 aerofoil profile, described tailplane 3 is slightly trapezoidal layout to the wing by wing root, for lateral symmetry
Tapered wing, the pneumatic focus of symmetrical airfoil is positioned at 25% chord length and does not changes with the angle of attack, therefore sets
Meter horizontal tail rotating shaft is herein, and the tailplane also participating in undertaking major part in addition to as rotating shaft function is pneumatic
Moment of flexure, tailplane is the least with wing its tangential stress the same, uses the cork wood of band hollow out to do rib,
During aircraft maneuvering, by horizontal tail surface aerodynamic force be delivered to rib be delivered to again rotating shaft carbon beam from
And be applied to rear body and control aircraft pitch, rib is relatively big with power transmission at spar or carbon pipe, therefore fills out herein
Putting boss, the tailplane wing is slightly little due to edge effect aerodynamic force, design herein as far as possible weak with
Alleviating construction weight, the control link of tailplane arranges present half wing root rib leading edge and extends forward
Place, this rib uses the aviation laminate that intensity is high, rib leading edge extended spot 10mm length, opens 3mm
Hole, uses this hole of band hole rivet riveting master, and rivet and rib are tightly fitted, and the rivet hole of metal is as even
Bar junction, so good by force intensity, rub resistance, dependability is high；
The outside of described fuselage 1, wing 2, load compartment 5, vertical tail 4 and tailplane 3 is all wrapped up
Having one layer of eyelid covering, described eyelid covering uses heat shrinkage film to make；
The rated speed of the electromotor that aircraft is selected is 37500r/min, and discharge capacity is 3.5cc, belongs to high and turns
The little moment of torsion service behaviour of speed, is not suitable for direct-driven airscrew, has preferably after certain deceleration
Efficiency plays, and on structure designs, is parallel to engine output shaft and installs a deboost axle, and deboost axle is pressed
Being divided into two parts according to effect, front section mainly has propeller, reduction gearing to be power section, and rear end is
The worm gear connected by unilateral bearing, worm gear is driven by the worm screw on brushless electric machine, and this part is electromotor
Electrically activate part；
The Performance Parameters of the application is as follows:
Type is single-shot piston-propeller transporter；Bare weight 3Kg；Span 4.5m；Captain 1.75m；
Machine height 0.82m；Maximum take-off weight 18Kg；Engine model 3.5cc；Methanol engine rated speed
37500r/min；Fully loaded cruising speed 45Km/h；Design flying height 100m；Fully loaded takeoff sliding run away from
From 30m.
The foregoing is only the preferred embodiment of the invention, not in order to limit present invention wound
Make, within all spirit in the invention and principle, any modification, equivalent substitution and improvement made
Deng, within should be included in the protection domain of the invention.
Claims (10)
1. the oil of a heavy－duty ratio moves fixed wing airplane, it is characterised in that: include fuselage (1),
Described fuselage (1) front part sides is respectively symmetrically and is provided with a wing (2), described wing (2)
By beam box (21) be covered in the mask (22) of beam box (21) upper surface and constitute, described beam box (21)
Including upper beam (211), underbeam (212) and web (213), described upper beam (211) is arranged at institute
State underbeam (212) top, and between being provided with between described upper beam (211) and described underbeam (212)
Gap, described web (213) is arranged at two sides before and after described upper beam (211) and underbeam (212)
On；
Attachment lug (8) it is provided with at the wing root of described wing (2), described attachment lug (8)
Side is provided with lug (81), described fuselage (1) is provided with and matches with described lug (81)
Draw-in groove, be bolted between described lug (81) and draw-in groove；
Described fuselage (1) underside of forward is provided with load compartment (5), the top of described load compartment (5)
Being connected with the wing root of wing (2), the front portion of described load compartment (5) lower end is provided with nose-gear (6),
The middle part of described load compartment (5) lower end is provided with main landing gear (7), described load compartment (5) bottom
It is provided with hatch door；
Described fuselage (1) rear portion is provided with tailplane (3) and vertical tail (4).
The oil of heavy－duty ratio the most according to claim 1 moves fixed wing airplane, it is characterised in that:
Described upper beam (211) and underbeam (212) are Lignum paulowniae, described upper beam (211) and underbeam (212)
Lower surface be provided with along wing length direction extend groove, be provided with steel wire rope in described groove
(214), the upper and lower surface of described upper beam (211) and underbeam (212) is all enclosed with carbon cloth.
The oil of heavy－duty ratio the most according to claim 1 moves fixed wing airplane, it is characterised in that:
Described upper beam (211) and underbeam (212) are the trapezium structure of slightly taper in width from wing root to the wing, institute
The thickness stating upper beam (211) is 8mm, and the thickness of described underbeam (212) is 5mm.
The oil of heavy－duty ratio the most according to claim 1 moves fixed wing airplane, it is characterised in that:
Described web (213) is cork wood, and described web (213) is slightly tapered trapezoidal of thickness from wing root to the wing
Structure, from wing root to the wing, slightly thickness reduces described mask (22), and the wing of described mask (22) is slightly located
For hollow out shape.
The oil of heavy－duty ratio the most according to claim 1 moves fixed wing airplane, it is characterised in that:
Described beam box (21) is internally located between upper beam (211) and underbeam (212) and is close to web (213)
Place is evenly arranged with diagonal brace and pillar, and diagonal brace and pillar at the internal close wing root of described beam box (21) are adopted
Cork wood is used with Lignum paulowniae, the diagonal brace slightly located near the wing and pillar.
The oil of heavy－duty ratio the most according to claim 1 moves fixed wing airplane, it is characterised in that:
Described vertical tail (4) uses balsa wood material to make.
The oil of heavy－duty ratio the most according to claim 1 moves fixed wing airplane, it is characterised in that:
Described tailplane (3) is slightly trapezoidal layout to the wing by wing root.
The oil of heavy－duty ratio the most according to claim 1 moves fixed wing airplane, it is characterised in that:
Described fuselage (1) is to the most thicker trapezoidal shape of head by tail, described fuselage (1) upper and lower
Four faces, left and right are disposed as plane, and described fuselage (1) includes four girders and is arranged between girder
Corbeling, described corbeling use cork wood make.
The oil of heavy－duty ratio the most according to claim 1 moves fixed wing airplane, it is characterised in that:
Described load compartment (5) is to be formed by carbon fiber bar overlap joint.
The oil of heavy－duty ratio the most according to claim 1 moves fixed wing airplane, it is characterised in that:
Described fuselage (1), wing (2), load compartment (5), vertical tail (4) and tailplane (3)
Outside be all enclosed with one layer of eyelid covering, described eyelid covering uses heat shrinkage film to make.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620448891.1U CN205652335U (en) | 2016-05-17 | 2016-05-17 | Oil of big load ratio moves fixed -wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620448891.1U CN205652335U (en) | 2016-05-17 | 2016-05-17 | Oil of big load ratio moves fixed -wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205652335U true CN205652335U (en) | 2016-10-19 |
Family
ID=57402496
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620448891.1U Expired - Fee Related CN205652335U (en) | 2016-05-17 | 2016-05-17 | Oil of big load ratio moves fixed -wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205652335U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105775105A (en) * | 2016-05-17 | 2016-07-20 | 中国民航大学 | Oil-driven fixed wing aircraft with high load ratio |
| CN110606188A (en) * | 2019-09-12 | 2019-12-24 | 青岛度丘新能源技术有限公司 | Large-wing airplane |
| WO2021128674A1 (en) * | 2019-12-27 | 2021-07-01 | 南京祖航航空科技有限公司 | High-strength wing structure |
-
2016
- 2016-05-17 CN CN201620448891.1U patent/CN205652335U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105775105A (en) * | 2016-05-17 | 2016-07-20 | 中国民航大学 | Oil-driven fixed wing aircraft with high load ratio |
| CN110606188A (en) * | 2019-09-12 | 2019-12-24 | 青岛度丘新能源技术有限公司 | Large-wing airplane |
| WO2021128674A1 (en) * | 2019-12-27 | 2021-07-01 | 南京祖航航空科技有限公司 | High-strength wing structure |
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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: 20161019 Termination date: 20170517 |