CN106697259A - Fixed wing unmanned plane - Google Patents
Fixed wing unmanned plane Download PDFInfo
- Publication number
- CN106697259A CN106697259A CN201611258959.0A CN201611258959A CN106697259A CN 106697259 A CN106697259 A CN 106697259A CN 201611258959 A CN201611258959 A CN 201611258959A CN 106697259 A CN106697259 A CN 106697259A
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- unmanned plane
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- empennage
- assembling
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims 1
- 238000005507 spraying Methods 0.000 abstract description 18
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- 238000012423 maintenance Methods 0.000 description 9
- 230000006378 damage Effects 0.000 description 5
- 239000006260 foam Substances 0.000 description 5
- 239000007921 spray Substances 0.000 description 5
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/28—Leading or trailing edges attached to primary structures, e.g. forming fixed slots
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/04—Arrangement or disposition on aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/02—Tailplanes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/16—Dropping or releasing powdered, liquid, or gaseous matter, e.g. for fire-fighting
- B64D1/18—Dropping or releasing powdered, liquid, or gaseous matter, e.g. for fire-fighting by spraying, e.g. insecticides
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Life Sciences & Earth Sciences (AREA)
- Pest Control & Pesticides (AREA)
- Catching Or Destruction (AREA)
Abstract
The invention relates to a fixed wing type unmanned plane. A wing of the unmanned plane is of a three-section type wing-shaped structure. Forward pulling type propellers are installed on the front end of a plane body of the unmanned plane; the unmanned plane is provided with protecting devices, the protecting devices comprise a propeller protecting device, a wingtip protecting device and an empennage protecting device; and the unmanned plane is provided with a spraying system, the spraying system comprises a container, a pump, a spraying pipe and a spraying nozzle, the spraying nozzle is connected with the pump through the spraying pipe, and the pump is connected with the container through the spraying pipe. The fixed wing type unmanned plane has the advantages that various aspects of performance including spraying performance, collision resistance and the maximum lift coefficient is greatly improved.
Description
Technical field
The present invention relates to unmanned vehicle field, and in particular to a kind of fixed-wing unmanned plane.
Background technology
In recent years, with the development and the reduction of cost of unmanned vehicle technology, fixed-wing unmanned plane is in military, peace
The every field extensive use such as guarantor, traffic, exploration, mapping, meteorology.In military domain, fixed-wing unmanned plane is generally used for height
The investigation of outage speed, strike etc..On civil area, fixed-wing unmanned plane is generally used for taking photo by plane, surveys and draws, patrols and examines.
The various applications of unmanned plane have different technical requirements.For example, cruise of the unmanned plane of long-range scouting to aircraft
It is required that it is high, and the unmanned plane of landing in the wild requirement aircraft must adapt to simple and crude landing place.For the nothing taken photo by plane and survey and draw
Man-machine load-carrying requirement is shooting tripod head, and the unmanned plane for being used for pesticide spraying then needs big drugloading rate to improve single sortie
Spray area.
Although these unmanned planes have different applications and requirement, they have some common performance hopes.For example, big carry
Weight, short landing distance, impact resistant, low maintenance cost, high security are the desirable characteristics of most of unmanned plane.
The content of the invention
The purpose of the present invention is directed to deficiency of the prior art, there is provided a kind of fixed-wing unmanned plane, is significantly increased
Many performances, including sprinkler performance, crash worthiness energy and maximum lift coefficient.
To achieve the above object, the invention discloses following technical scheme：
A kind of fixed-wing unmanned plane, the wing of the unmanned plane is three-stage airfoil structure, including is arranged on the leading edge of a wing
Slat, the main wing being arranged in the middle of wing and the wing flap for being arranged on trailing edge, main wing include central wing and the centrally disposed wing
The outer wing of both sides, wing flap includes the wing flap of centrally disposed wing trailing edge and is arranged on the flaperon of outer wing trailing edge；
The pull-type propeller before the unmanned aerial vehicle body front end is provided with, protection device includes that propeller protection device, wingtip are protected
Protection unit, empennage protection device：Propeller protection device is located at the both sides and front of propeller, including skeleton and buffer unit,
Buffer unit is attached at skeleton outside, and skeleton includes the of the first vertical pole on the left of the propeller, the cross bar in front and right side
Two vertical poles, the first vertical pole and second vertical pole one end are fixedly connected on wing, and the other end extends forward, is connected with cross bar；Wingtip
Protection device is located at wing wingtip, including left wing's tip wipes ground piece and the right flank tip wipes ground piece, is separately mounted under the wingtip of left and right
Side, when aircraft side wing contacts to earth, wipes ground piece and contacts to earth at first；Empennage protection device is located at the bottom of unmanned plane tailplane,
Empennage protection device is that empennage wipes ground piece, and when aircraft excessively comes back and afterbody is contacted to earth, empennage is wiped ground piece and contacted to earth at first；
Sprinkling system is provided with the unmanned plane, sprinkling system includes container, pump, jet pipe and shower nozzle, and shower nozzle passes through jet pipe
It is connected with pump, pump is connected by jet pipe with container：
Container is symmetrical along the plane of symmetry of wing, and is arranged on unmanned plane center of gravity；
Shower nozzle is distributed along wing span, and connection shower nozzle is located at wing bottom with the jet pipe of pump；
Jet pipe includes the two sections of overhanging jet pipes in left and right, and overhanging jet pipe stretches out along spanwise from wingtip.
Further, between the central wing and outer wing it is detachable structure, central wing is with outer wing by some assembly and disassembly dresses
Put installation wing.
Further, the unmanned plane also includes empennage, and empennage includes that the empennage attachment structure and empennage at wing rear connect
Tailplane, the vertical tail at binding structure rear, empennage attachment structure are connected by assembling and disassembling device with wing, tailplane, hang down
Fin is connected by assembling and disassembling device with empennage attachment structure.
Further, the assembling and disassembling device includes wing assembling and disassembling device, tail supporting rod-wing assembling and disassembling device and tail supporting rod-tail
Wing assembling and disassembling device, wing assembling and disassembling device is distributed in wing exhibition upwards, and wing is divided into three sections of left, center, right, and three sections of wings pass through machine
Wing assembling and disassembling device carries out assembly and disassembly；
Wing assembling and disassembling device is ear sheet type connecting structure, and ear sheet type connecting structure is provided with assembly and disassembly hole, and assembly and disassembly hole is bolt
Connecting hole, ear sheet type connecting structure is provided with the installation sheet for being fixedly connected with wing；
Or
Wing assembling and disassembling device is tubular type attachment structure, and central wing is connected with outer wing by the form of pipe fitting sleeving, one section of pipe
It is affixed with outer wing, and the segment length of outer wing one is stretched out, another section of pipe is embedded in central wing；
Tail supporting rod-wing assembling and disassembling device is tubular type attachment structure, and pipe is provided with mounting hole, is passed through with fuselage by mounting hole
Bolt connection；Positioning lock tieholen is additionally provided with pipe；Pipe end is additionally provided with locking hoop；
Tail supporting rod-empennage assembling and disassembling device is the rectangle structure with fluting, is provided with tail supporting rod mounting hole, shoe rod locking
Hole, horizontal tail mounting hole and vertical fin mounting hole.
Further, the container is freestanding container, is built in inside the wing, and container has curved upper surface,
Fitted with covering on wing；Container has arcuate lower surface, is fitted with covering under wing；
Or
Container is freestanding container, is built in inside the wing, and container has curved upper surface, is pasted with covering on wing
Close；Container has arcuate lower surface, is fitted with covering under wing.
Further, the container inside has at least one dividing plate, near at least one hole of container bottom on dividing plate,
The hole causes fluid connection in container.
Further, the jet pipe of connection shower nozzle and the pump is embedded in wing lower surface, shower nozzle spout towards with away from
The aircraft plane of symmetry and it is progressively outside；
Or
The jet pipe of connection shower nozzle and pump is located at wing lower section, shower nozzle spout horizontally toward rear.
Further, the overhanging jet pipe at wingtip be bendable folded structure, during sprinkling, jet pipe with launch shape, parallel to
Horizontal plane, during non-sprinkling, jet pipe is rugosity, is folded up perpendicular to horizontal plane, or is folded back in the horizontal plane, is folded
Jet pipe afterwards no longer reaches the scope beyond wingtip.
Further, the unmanned plane also includes front three-point wheel undercarriage, and undercarriage includes that nose-gear and master rise and fall
Frame, nose-gear is arranged on the cross bar of propeller protection device, and main landing gear is arranged on fuselage bottom.
Further, the cross bar includes two the first cross bars and the second cross bar for having certain longitudinal separation, nose-gear
Inclined support bar including main support rod and both sides, main support rod one end is fixed on the second cross bar of rear end, two inclined support bars
One end is symmetrically fixed on main support rod, and the other end is fixedly connected with the first cross bar for being set in front end respectively, main support rod, tiltedly
Support bar, the first cross bar, the second cross bar constitute tetrahedral structure.
A kind of fixed-wing unmanned plane disclosed by the invention, has the advantages that：
1. an innovative point of the invention is to use three-stage air-foil.Relative to the unistage type of current unmanned plane
Or two-part aerofoil profile, three-stage aerofoil profile has maximum lift coefficient higher, and this causes that aircraft has maximum lift higher.Most rise higher
The raising of power allows that aircraft has load capacity and lower stalling speed higher, can the landing on shorter runway, have more
Good low-speed operations performance.
2. the present invention carries out multi-faceted protection to unmanned plane, to lower use and maintenance cost.Unmanned plane take off and
It is susceptible to collide during land and wipes ground.Except front protection device above, the present invention also enters from both sides and afterbody to unmanned plane
Row protection, so as to reach the protection in four orientation, it is to avoid impact, scraping damage wing when wingtip and empennage contact to earth, before improve
The security of pull-type fixed-wing unmanned plane, reduces maintenance cost, reduces application risk.
3. agricultural application is upper, and the fixed-wing unmanned plane can be applicable to pesticide spraying and the prevention and control of plant diseases, pest control is first-class, and the present invention is logical
The overhanging jet pipe for adding is crossed, can extend spray area, improve sprinkler performance, realize that high efficiency is sprayed.
Brief description of the drawings
Fig. 1 a:A kind of agricultural spraying unmanned plane with three sections of aerofoil profiles, propeller protection device.
Fig. 1 b:Another angle of Fig. 1 b, it is shown that nose-gear wipes ground with the connection of propeller protection device and empennage
Piece.
Fig. 2 a：A kind of horizontal tail aerofoil profile.
Fig. 2 b：Another horizontal tail aerofoil profile.
Fig. 3 a：A kind of cross section of propeller protection device.
Fig. 3 b：Another cross section of propeller protection device.
Fig. 4:The double cross bar protection devices of nose-gear.
Fig. 5 a:Three-stage aerofoil profile wing and preposition nozzle.
Fig. 5 b:Three-stage aerofoil profile wing and postposition nozzle.
Fig. 6：Sprinkling system connection figure
Fig. 7：The built-in schematic diagram of container
Fig. 8：Structure of container schematic diagram
Fig. 9：Shower nozzle, jet pipe connection front view
Figure 10：Another jet pipe, nozzle layout of sprinkler schematic diagram
Figure 11：Aircraft broken away view
Figure 12 a：A kind of wing mounting mechanism
Figure 12 b：Another wing assembling-disassembling structure
Figure 13：A kind of wing-tail supporting rod attachment structure
Figure 14：A kind of empennage assembling-disassembling structure
Figure 15：Anury fixed-wing agricultural spraying unmanned plane with three sections of aerofoil profiles, propeller protection device.
Specific embodiment
The technical scheme in the embodiment of the present invention will be clearly and completely described below, it is clear that described implementation
Example is only a part of embodiment of the invention, rather than whole embodiments.Based on the embodiment in the present invention, this area is common
The every other embodiment that technical staff is obtained under the premise of creative work is not made, belongs to the model of present invention protection
Enclose.
Core of the invention is to provide a kind of fixed-wing unmanned plane, and many performances, including sprinkling is significantly increased
Performance, crash worthiness energy and maximum lift coefficient.
A kind of fixed-wing unmanned plane, the wing of the unmanned plane is three-stage airfoil structure, including is arranged on the leading edge of a wing
Slat 107, the main wing being arranged in the middle of wing and the wing flap for being arranged on trailing edge, main wing include central wing 106 and are arranged on
The outer wing 105 of the both sides of central wing 106, after wing flap includes the wing flap 103 of the trailing edge of the centrally disposed wing 106 and is arranged on outer wing 105
The flaperon 101 of edge.
In an embodiment of the present invention, the fixed-wing is rectangular wing, and middle central wing 106 is flat segments,
Left right lateral outer wing 105 carries the upper counterangle.
In an embodiment of the present invention, the wing flap is fixed structure, removable or turntable with respect to main wing；
The slat is fixed structure, removable or rotational structure with respect to main wing.
In an embodiment of the present invention, it is detachable structure, central wing between the central wing 106 and outer wing 105
106 with outer wing 105 by some assembling and disassembling device installation wings.
In an embodiment of the present invention, the unmanned plane also includes empennage, and empennage includes that the empennage at wing rear connects
The tailplane 203 at binding structure 205 and the rear of empennage attachment structure 205, vertical tail 201, empennage attachment structure 205 is by dress
Dismantling device is connected with wing, and tailplane 203, vertical tail 201 are connected by assembling and disassembling device with empennage attachment structure 205.
In an embodiment of the present invention, the tailplane is stabilator, and aerofoil profile neutrality line 211 is centre
Recessed camber line, the chord length of the chord length more than or equal to taper of the root of tailplane 203.
In an embodiment of the present invention, the vertical tail 201 is complete dynamic vertical tail, the root of vertical tail
Chord length of the chord length more than or equal to taper.
In an embodiment of the present invention, the empennage attachment structure 205 is a rod member, and bar cross section is constant or becomes
Change, when bar cross section is for change structure, is more than near an end section of head and leans on a caudal end section.
In an embodiment of the present invention, the assembling and disassembling device includes wing assembling and disassembling device 601, tail supporting rod-wing dress
Dismantling device 605 and tail supporting rod-empennage assembling and disassembling device 607, wing assembling and disassembling device 301 are distributed in wing exhibition upwards, and wing is divided into
Three sections of left, center, right, three sections of wings carry out assembly and disassembly by wing assembling and disassembling device 601；
Wing assembling and disassembling device 601 is ear sheet type connecting structure, and ear sheet type connecting structure is provided with assembly and disassembly hole 613,611, dress
Hole is torn open for bolt connecting hole, ear sheet type connecting structure is provided with the installation sheet 615,617 for being fixedly connected with wing；
Or
Wing assembling and disassembling device 601 is tubular type attachment structure, and central wing 106 is connected with outer wing 105 by the form of pipe fitting sleeving
Connect, one section of pipe 605 is affixed with outer wing, and stretch out the segment length of outer wing one, another section of pipe is embedded in central wing 106；
Tail supporting rod-wing assembling and disassembling device is tubular type attachment structure, and pipe is provided with mounting hole 611, by mounting hole 611 and machine
Body is bolted；Positioning lock tieholen 613 is additionally provided with pipe；Pipe end is additionally provided with locking hoop 615；
Tail supporting rod-empennage assembling and disassembling device is the rectangle structure with fluting, is provided with tail supporting rod mounting hole 625, shoe lever lock
Tieholen 621, horizontal tail mounting hole 623 and vertical fin mounting hole 627.
In an embodiment of the present invention, the slat 107 is made of changeability energy-absorbing material.
The pull-type propeller before the unmanned aerial vehicle body front end is provided with, the unmanned plane is provided with protection device, and protection device includes
Propeller protection device, wingtip protection device, empennage protection device：
Propeller protection device is located at the both sides and front of propeller, including skeleton 408 and buffer unit, buffer unit patch
The outside of skeleton 408 is invested, cross bar 407 and right side of the skeleton 408 including the first vertical pole 409, front on the left of propeller
Second vertical pole 411, the first vertical pole 409 and the one end of the second vertical pole 411 are fixedly connected on wing, and the other end extends forward, with horizontal stroke
Bar 407 is connected；
Wingtip protection device is located at wing wingtip, including left wing's tip wipes ground piece 413 and the right flank tip wipes ground piece 415, respectively
Installed in the lower section of left and right wingtip, when aircraft side wing contacts to earth, wipe ground piece and contact to earth at first；
Empennage protection device is located at the bottom of unmanned plane tailplane, and empennage protection device is that empennage wipes ground piece 417, when winged
When machine excessively comes back and afterbody is contacted to earth, empennage is wiped ground piece 417 and is contacted to earth at first.
In an embodiment of the present invention, buffer unit is the foam being attached on skeleton 408.
In an embodiment of the present invention, it is to fly along unmanned plane that left wing's tip wipes ground piece 413 and right flank tip wiping ground piece 415
The streamlined structure of direction of flow during row；Empennage wipes the streamlined of direction of flow when ground piece 417 is along unmanned plane during flying
Structure.
In an embodiment of the present invention, it is the laminated structure that unmanned plane is connected to by fastener to wipe ground piece.
In an embodiment of the present invention, the unmanned plane also includes front three-point wheel undercarriage, and undercarriage includes preceding
Undercarriage and main landing gear, nose-gear are arranged on the cross bar 407 of propeller protection device, and main landing gear is arranged on fuselage bottom
Portion.
In an embodiment of the present invention, the cross bar 407 include two the first cross bars for having certain longitudinal separation and
Second cross bar (Fig. 4), nose-gear includes the inclined support bar 408 of main support rod 401 and both sides, and the one end of main support rod 401 is fixed
On the second cross bar of rear end, two one end of inclined support bar 408 are symmetrically fixed on main support rod 401, the other end respectively with set
The first cross bar for being scheduled on front end is fixedly connected, and main support rod 401, inclined support bar 408, the first cross bar, the second cross bar constitute four sides
Body structure.
Be provided with sprinkling system on the unmanned plane, sprinkling system include container 300, pump 331, jet pipe (303,305,321,
323) with shower nozzle (307,309,311,313,315,317,319), shower nozzle is connected by jet pipe with pump 331, and pump 331 passes through jet pipe
It is connected with container 300：
Container 300 is symmetrical along the plane of symmetry of wing, and is arranged on unmanned plane center of gravity；
Shower nozzle is distributed along wing span, and connection shower nozzle is located at wing bottom with the jet pipe of pump 331；
Jet pipe includes the two sections of overhanging jet pipes 303,305 in left and right, and overhanging jet pipe stretches out along spanwise from wingtip.
In an embodiment of the present invention, the container 300 is freestanding container, is built in inside the wing, is held
Device 300 has curved upper surface, is fitted with covering on wing；Container 300 has arcuate lower surface, is fitted with covering under wing.
In an embodiment of the present invention, the container 300 and wing are integral type container, and the integrated container is by machine
Spar, rib, covering are constituted, and skeleton is formed by wingbar, rib, and covering is coated on and container is formed on skeleton.
In an embodiment of the present invention, the inside of the container 300 has at least one dividing plate 302, is leaned on dividing plate 302
Nearly at least one hole of container bottom, the hole causes fluid connection in container.
In an embodiment of the present invention, the dividing plate 302 includes longitudinal baffle and lateral partitions.
In an embodiment of the present invention, connection shower nozzle is embedded in wing lower surface, shower nozzle spout with the jet pipe of pump 300
Towards with progressively outside (such as Fig. 9) away from the aircraft plane of symmetry.
In an embodiment of the present invention, connection shower nozzle is located at wing lower section, shower nozzle spout level court with the jet pipe of pump
Rearward (such as Figure 10).
In an embodiment of the present invention, overhanging jet pipe 305,303 is bendable folded structure at wingtip, during sprinkling, spray
Pipe and expansion shape, parallel to horizontal plane, during non-sprinkling, jet pipe is rugosity, is folded up perpendicular to horizontal plane, or in level
Folded back in face, the jet pipe after folding no longer reaches the scope beyond wingtip.
Specifically：
Specifically：
A kind of fixed-wing unmanned plane of the present invention, the unmanned plane air-foil is three-stage aerofoil profile, including slat, main wing and the flap
The wing；The unmanned plane also has Multidirectional protection device, including propeller protection device, wingtip protection device and empennage protection dress
Put；The unmanned plane can carry sprinkling system, for spraying operation；The unmanned plane also has assembling and disassembling device, including wing assembly and disassembly dress
Put and empennage assembling and disassembling device.The fixed-wing UAV system is great, low-speed characteristics are good, impact resistant, safe to use, is easy to
Transport, can be used for agricultural spray operation.
Relative to the unistage type or two-part aerofoil profile of current unmanned plane, three-stage aerofoil profile has maximum lift higher
Coefficient, this causes that aircraft has maximum lift higher.Maximum lift coefficient is the important technology index of an airplane, is affected winged
The multiple performance of machine.For example, maximum lift coefficient higher causes that aircraft has lower stalling speed (to keep putting down winged lowest speed
Degree).Lower flying speed causes that unmanned plane has resolution ratio higher in investigation, shooting, exploration.Maximum lift coefficient is carried
Height is liftoff earlier when enabling that unmanned plane takes off simultaneously to soar, and realizes short distance of taking off.Lower flying speed also causes to fly
Can brake stopping during machine landing landing in shorter distance, reduce landing distance.In the air during flight, lift coefficient higher
So that aircraft there can be bigger weight under same uniform velocity, payload is improved.Three sections of aerofoil profiles make to get stream preferably close to
The upper surface of aerofoil profile, postpones upper surface flow field and separates and obtain lift coefficient higher.
Wing uses three sections of aerofoil profiles near the main wing of the aircraft plane of symmetry in one embodiment of the present of invention.Another embodiment
Middle outer wing uses three sections of aerofoil profiles.Because the outer wing of fixed wing aircraft typically has aileron to control the rolling of aircraft, using three sections of wings
Aileron turns into flaperon 101 during type.The difference of flaperon 101 plays the rolling control function of aileron, flap pair when not deflecting when deflecting
The wing 101 is wing flap, improves the lift coefficient of aircraft.Slat 107 has used deformable energy-absorbing in another embodiment of the invention
Material, such as foam.So slat 107 is sacrificed oneself and protects the miscellaneous part of aircraft in an impact.This slat 107 is
It is easy to what is repaired or directly replace, to reduce maintenance cost.
The need for difference, slat 107 and wing flap 103 can be fixed or moveable.A reality of the invention
Applying slat 107 or wing flap 103 in example can move relative to main wing.Such scheme allows that aircraft will in high-performance cruise
Slat 107 and wing flap 103 withdraw and are combined into single hop aerofoil profile with main wing, reduce cruise drag.Stitched in an alternative embodiment of the invention
The wing 107 is fixed, to reduce movable device, reduces cost and weight.Wing flap 103 is solid in another embodiment of the invention
Fixed, to reduce movable device, reduces cost and weight.
The size of fixed-wing unmanned plane causes that transport is inconvenient sometimes, limits and is used into using scope or improve
This.Some innovations of the invention reduce transportation clearance.Wing has assembly and disassembly to fill along spanwise in one embodiment of the present of invention
Put, some wing sections can be splitted into.Wing is divided into port wing, central wing and starboard wing three in an alternative embodiment of the invention
Section, this three sections of wings can be taken apart.Central machine wing panel is flat segments in another embodiment, and left and right wing has anhedral.
In some embodiments of the present invention, the unmanned plane includes the empennage attachment structure 205 and position positioned at wing rear
Tailplane 203, vertical tail 201 in the rear of empennage attachment structure 205.Wherein, empennage attachment structure 205 is a rod member.
In one embodiment, this bar cross section is change, and the end section near head is larger, and leans on caudal one end to cut
Face is smaller.This Bars with Variable Cross-Section mitigates weight, material-saving while intensity, rigidity needed for ensureing.In one embodiment
Middle vertical tail 201 includes fixed fin and rudder 202, and vertical tail 201 is complete dynamic vertical in another embodiment
Empennage.The chord length of vertical fin root can be more than the chord length of taper, it is also possible to equal to the chord length of taper.Level in certain embodiments
Empennage 203 is stabilator, and the aerofoil profile neutrality line of tailplane 203 is middle recessed camber line, such aerofoil profile
Lower pressure (such as Fig. 2 b) higher is provided.Tailplane 203 includes horizontal stabilizer and elevator 204 in certain embodiments.
The chord length of horizontal tail root can be more than the chord length of taper, it is also possible to equal to the chord length of taper.
One of the invention is innovated the convenient transportation for further improving tail on fixed-wing unmanned plane.In an implementation
Empennage and the rod member of main wing (or empennage and fuselage) are connected in example can separate from main wing/fuselage.In another embodiment
In this rod member can be separated from empennage.Vertical fin can be separated with horizontal tail In yet another embodiment.In another implementation
Example in horizontal tail the left side can with horizontal tail on the right of separate.These schemes cause that a frame unmanned plane is segmented into polylith, are easy to
Transport, reaches and is used using being assembled again behind ground.
A key factor of the unmanned plane in is security, and another key factor is maintenance cost.In-flight
Once there is personnel and the property that deviation is possible to damage periphery in unmanned plane.Propeller in operating is also potential safety hazard.Preceding drawing
Formula fixed-wing unmanned plane due to its propeller be located at forefront, be most susceptible to destruction, and to the personnel around it, other move
Plant also has certain danger.Reasonable Protection to propeller and engine makes as pull-type fixed-wing unmanned plane before reducing
With, maintenance cost, the key of application risk is reduced.An innovation of the invention is filled in the both sides of preceding pull-type propeller and front
Standby protection device, accordingly even when unmanned plane has collided personnel, propeller directly will not be got on the person.This both protects personnel,
Maintenance cost is also reduced, because propeller and engine are usually aircraft components costly.In one embodiment this
Protection device is made up of rod member.Protection device is by rod member skeleton and the buffer unit group of skeleton both sides in another embodiment
Into.Buffer unit is the foam being attached on rod member In yet another embodiment.Foam is shaped such that propeller front rod member
Total profile for streamlined, reduce resistance.The innovation improves the security of preceding pull-type fixed-wing unmanned plane, reduces maintenance cost
With.
In some embodiments, the unmanned plane undercarriage is front three-point wheel undercarriage.Another innovation of the invention
It is that nose-gear is arranged in propeller protection device.This causes that nose-gear can protect propeller in itself, while spiral
The protection device of oar provides support tie point for nose-gear so that compact conformation, aircraft weight is low.
Some innovations of the invention carry out multi-faceted protection to unmanned plane, to lower use and maintenance cost.Unmanned plane
It is susceptible to collide during take-off and landing and wipes ground.Except front protection device above, the present invention is also from both sides and afterbody pair
Unmanned plane is protected, so as to reach the protection in four orientation.In one embodiment, the unmanned plane is filled at wing wingtip
There is wingtip protection device, it is to avoid impact, scraping damage wing when wingtip contacts to earth.In another embodiment, the unmanned plane is also
Including the empennage protection device positioned at tailplane bottom, it is to avoid impact, scraping damage empennage when horizontal tail is contacted to earth.In some implementations
Example in, these protection devices for ease of change wiping ground piece.
The size of fixed-wing unmanned plane is generally large, especially the fixed-wing unmanned plane of load-carrying high.The size of unmanned plane makes
Its transport inconvenience is obtained, cost of transportation is high or even cannot transport, this limits and have impact on the range of application of unmanned plane and is applied to
This.Another innovation of the invention reduces the transportation clearance of fixed-wing unmanned plane, so as to overcome this difficulty.
Agriculturally fixed-wing unmanned plane is applied in Grain Growth Situation, insect pest detection etc., and with greater need for the agricultural chemicals spray of labour
Spill, the spraying operations such as sprinkling major part of pollinating uses depopulated helicopter or many rotors.An application of the invention is to improve solid
Determine load-carrying, flight and the sprinkler performance of wing unmanned plane so that fixed wing aircraft has more preferable spraying efficiency.Such unmanned plane can
For forestry, agricultural and grass cultivation irrigation, moisten, spill medicine, fertilising and pollination etc..The unmanned plane includes a set of sprinkling system,
Including：Container, pump, jet pipe, shower nozzle, shower nozzle are connected by jet pipe with pump, and pump is connected by jet pipe with container.
Improving sprinkling breadth can improve spraying efficiency, and jet pipe includes that two sections of left and right is overhanging in one embodiment of the present of invention
Section jet pipe, overhanging section of jet pipe stretches out along spanwise from wingtip.Overhanging section of jet pipe can bend at wingtip.By overhanging section
Jet pipe bends upwards or posteriorly or anteriorly can reduce jet pipe in the upward length of aircraft exhibition, and reduction aircraft is in takeoff and landing
Length, reduces the requirement to landing place.
An alternative embodiment of the invention changes the sprinkling direction of shower nozzle, increases actual breadth.The axis and wing of shower nozzle
The angle of the plane of symmetry is big with the change of shower nozzle and the distance of the wing plane of symmetry and change is big.This causes the sprinkling direction of shower nozzle progressively guide vane
The outside deflection of the tip, obtains breadth higher.
Another object of the present invention is the flight resistance for reducing sprinkling Fixed Wing AirVehicle, to reduce the requirement of power
With the loss of energy.Container is exposed at general sprinkling unmanned plane the surface of aircraft, or increase fuselage volume and
Surface area disposes container.These methods both increase the flight resistance of aircraft.An innovation of the invention is by container
It is placed in inside wing, and in the vicinity of full machine center of gravity.So with the position of centre of gravity of the full machine of change of liquid weight in container
Change is little.In one embodiment, container is freestanding container, is built in inside wing, symmetrical along the wing plane of symmetry.
In some embodiments, container has curved upper surface, is fitted with covering on wing；Container has arcuate lower surface, with machine
Covering laminating under the wing.Freestanding container is conveniently replaceable.In another embodiment, container is integral type container, the integral type
Container is made up of wingbar, rib, covering.Integrated container takes full advantage of original wing structure, saves material and aircraft
Weight.In order to further reduce flight resistance, shower nozzle is distributed along wing span in another embodiment of the invention, connects shower nozzle
Wing lower surface is embedded in the jet pipe of pump, can be embedded as needed installed in slat lower surface or main wing lower surface.The present invention
Another embodiment pump is built in inside wing.
Because liquid can flow back and forth in a reservoir, or even agitate, the flight of the change of its inertia force and center of gravity to aircraft
Attitude is impacted, and interference even destroys normal state of flight.It is an object of the invention to reducing and suppressing this liquid
Body flows.Container inside has at least one dividing plate, at least one close container on dividing plate in one embodiment of the present of invention
Base apertures.This hole causes that liquid is connection.
In sum, fixed-wing unmanned plane has a wide range of applications, and the present invention improves multiple performances of aircraft, including most
Rise higher force coefficient, security, load-carrying, takeoff and landing performance, crash worthiness energy, security etc..Application of the invention will cause fixed-wing
Aircraft has wider market in agricultural and other field.
Fig. 1 a and Fig. 1 b are a kind of embodiment of the invention.It is a kind of that there is three sections of aerofoil profiles, protection device and sprinkling systems
Detachable agricultural spraying unmanned plane.The present embodiment is, to the schematically illustrate of partial content of the present invention, should not inadequately to limit
The scope of claim is made.
Unmanned plane shown in Fig. 1 includes power set, wing, tailplane, vertical tail, tail supporting rod, protection device, sprinkling
System.Wherein：
Air-foil is three-stage aerofoil profile, including：The slat 107 for being arranged on the leading edge of a wing, the master being arranged in the middle of wing
The wing and the wing flap for being arranged on trailing edge, main wing include the outer wing 105 of central wing 106 and the both sides of the centrally disposed wing 106, wing flap
Wing flap 103 and the flaperon 101 for being arranged on the trailing edge of outer wing 105 including the trailing edge of the centrally disposed wing 106.Three-stage aerofoil profile has
High coefficient of lift combined characteristic, improves unmanned plane lifting capacity and low-speed characteristics.Flaperon 101,102 can differential deflection control nothing
Man-machine rolling, can deflect down as high lift device simultaneously, can also upward deflect simultaneously as flap.In another embodiment
Middle flaperon 101,102 can only carry out difference deflection, it is impossible to be deflected in the same direction.When flaperon 101,102 is in the neutral position,
And when being deflected without difference, they have gap and rotation relative to main wing, the lift-rising effect of wing flap is played.Wing flap 103 plays lift-rising work
With.In one embodiment, the deflection angle of wing flap 103 is adjustable, to adapt to the pneumatic need of different loads, aerial mission
Ask.For example, using large deflection angle that deflection angle is reduced or eliminated to improve lift, during cruise to reduce resistance during takeoff and landing.
In another embodiment, the deflection angle of wing flap 103 is changeless.Such design need not change work during deflection angle
Motivation structure, it is fairly simple, and material-saving and weight.
Wing is rectangular wing in Fig. 1, and middle central wing is flat segments, and left right lateral outer wing carries the upper counterangle, carries
Unmanned plane lateral stability high.The advantage of rectangular wing is easy for manufacture.In another embodiment, wing carries contraction coefficient,
Chord length at the aircraft plane of symmetry is more than the chord length at wingtip.When mean chord is constant, the wing with contraction coefficient has lower
Aerodynamic drag and bigger medicine-chest capacity.
Empennage is connected by empennage attachment structure 205 with wing, including vertical tail (201,202) and tailplane
(203、204)；Vertical tail 201 includes fixed fin and rudder 202；Tailplane 203 includes horizontal stabilizer and liter
Drop rudder 204.In another embodiment, vertical tail is all moving fin.In another embodiment, tailplane is complete dynamic flat
Tail.Chord length of chord length of the vertical tail with contraction coefficient, i.e. root more than taper in Fig. 1.In another embodiment, vertically
Empennage is flat segments, and the chord length of each exhibition position is the same.Chord length of the tailplane with contraction coefficient, i.e. root in Fig. 1 is more than taper
Chord length.In another embodiment, tailplane is flat segments, and the chord length of each exhibition position is the same.
Fig. 2 shows the different airfoil profiles of tailplane.Fig. 2 a show symmetrical tailplane aerofoil profile.Symmetrical airfoil is upper and lower
Symmetrically, neutrality line is straight line.Fig. 2 b show recessed tailplane aerofoil profile.The neutrality line 211 of recessed aerofoil profile is curved under centre
Camber line.Recessed aerofoil profile has lower pressure higher, strengthens the trim ability of full machine.
Protection device includes propeller protection device, wingtip protection device and empennage protection device.Propeller protection device
Cross bar 407 and second vertical pole 411 on right side including the first vertical pole 409, front positioned at the left side of power set 501.First indulges
The one end of 409 and second vertical pole of bar 411 is fixedly attached on wing, and the other end extends forward, is connected with cross bar 407.Protection rod member
A kind of cross section of structure such as Fig. 3 a, only rod member skeleton 408, another cross section such as Fig. 3 b, including rod member skeleton 408 ease up
Flushing device 406.Elastomeric material of the buffer unit 406 with energy reserve ability or energy absorption, such as foam, are attached to skeleton
408 outside.This open attached structure is convenient to the replacement of buffer unit 406.Wingtip protection device includes left wing's tip
Wipe ground piece 413 and the right flank tip wipes ground piece 415, be separately mounted to the lower section of left and right wingtip, when aircraft side wing contacts to earth, left wing
The tip wipes ground piece 413 or the right flank tip 415 contacts to earth at first, protects miscellaneous part.Wipe the structure of ground piece flowing when being along flight
Direction, front face area and aerodynamic drag are small.Empennage protection device is that empennage wipes ground piece 417, positioned at the lower section of horizontal tail 203.When winged
When machine excessively comes back and afterbody is contacted to earth, empennage is wiped ground piece and is contacted to earth at first, protects miscellaneous part.Empennage wipes the knot of ground piece 417
Direction of flow when structure is along flight, front face area and aerodynamic drag are small.The structure for wiping ground piece 413,415,417 is conveniently replaceable,
The laminated structure of aircraft is e.g. connected to by fastener.
As shown in Fig. 1 b, the nose-gear of aircraft is connected on the main support rod 401 of propeller.This innovation is on the one hand
So that nose-gear protects propeller in itself, while main support rod 401 is again for nose-gear provides tie point.
Fig. 4 shows a kind of new preceding guard bar and nose-gear structure.In the structure, propeller cross bar 407 includes two
Root has the transverse bar member of certain longitudinal separation, and nose-gear includes middle main support rod 401 and both sides inclined support bar 408.Main branch
Strut 401 is fixedly connected with the one end of inclined support bar 408, and the other end is fixedly connected with the first cross bar respectively.The main support of nose-gear
Bar 401, inclined support bar 408 and propeller cross bar 407 constitute tetrahedral structure, the structure in fore-and-aft direction, left and right directions simultaneously
With strength and stiffness higher, it is ensured that nose-gear it is durable in use.
It is an object of the invention to a frame is efficient, reliable sprinkling fixed-wing unmanned plane.Fig. 5 shows a kind of sprinkling
System, including container 300, pump 331, jet pipe (303,305,321,323) and shower nozzle (307,309,311,313,315,317,
319).Fig. 7 is shown inside the centrally located wing of container 300, symmetrical.Compared to external container and increase body volume
Container, such built-in container maintains the clean streamline of aircraft configuration, and the resistance of aircraft is not increased additionally.Container 300
At the center of gravity and centre of lift of aircraft, the influence of the change of such amount of liquid medicine to center of gravity is little so that aircraft easily keeps
Good state of flight.Pump 331 is located inside main wing 105, and container 300 is connected with pump 331 by jet pipe 323.Shower nozzle (307,
309th, 311,313,315,317,319) it is connected by jet pipe (303,305,321) with pump 331.Jet pipe 321 is embedded in slat 107
Lower surface.
Jet pipe 303, jet pipe 305 are bent connection with the connection of jet pipe 321, and during sprinkling, jet pipe 303, jet pipe 305 are exhibition
Shape is opened, parallel to horizontal plane, during non-sprinkling, jet pipe 303, jet pipe 305 are rugosity, are folded up perpendicular to horizontal plane, or
Fold back in the horizontal plane.Jet pipe after folding no longer reaches the scope beyond wingtip, is easy to the takeoff and landing of aircraft.
During sprinkling, the axis of shower nozzle 319 perpendicular to horizontal plane, the axis of shower nozzle 311 and the axis of shower nozzle 313 and horizontal plane angle compared with
Greatly, the axis of shower nozzle 315 and the axis of shower nozzle 317 are smaller with horizontal plane angle, the axis of shower nozzle 307 and the axis of shower nozzle 309 and horizontal plane
Angle is minimum.The sprinkling direction of shower nozzle is with progressively outside away from the aircraft plane of symmetry so that sprinkling breadth is more than left and right outermost
The distance between end shower nozzle, improves spraying efficiency.
In one embodiment, the upper surface of container 300 is arcwall face, is fitted with Skinning Surfaces on main wing 107；Container 300
Lower surface is arcwall face, is fitted with 107 times coverings of main wing.Under the conditions of same volume, the thickness of container is reached maximum, reduce
Container anterior-posterior length and left and right length, further reduce the gravity center shift scope of liquid.
The mobile meeting of the liquid in container causes that the center of gravity of aircraft changes, therefore influences the flight of aircraft.Fig. 8 shows
There is dividing plate 302 laterally, longitudinal inside container 300, several perforates are arranged at dividing plate bottom.These dividing plates slow down the shifting of liquid
It is dynamic, improve the flight stability of aircraft.
Figure 10 illustrates another jet pipe, nozzle layout of sprinkler form.Jet pipe 321 is arranged on wing lower section by support 312,
Shower nozzle 310 is distributed along jet pipe, and spout is backwards.Spout causes that liquid has a speed backward, the speed with respect to aircraft backwards
All or part of flying speed for offsetting aircraft, reduces horizontal velocity of the liquid with respect to ground, so as to reduce the further mist of liquid
Change.
The size of fixed-wing unmanned plane causes that transport is inconvenient sometimes.It is an object of the invention to reduce fixed-wing nobody
The transportation clearance of machine so that convenient transportation, reduces cost of transportation, expands range of application.Fig. 1 shows multiple dresses of the unmanned plane
Tear mechanism, including wing assembling and disassembling device (601,603), tail supporting rod-wing assembling and disassembling device 605, tail supporting rod-empennage assembling and disassembling device open
607.Figure 11 shows all parts of the aircraft after taking apart.Wing assembling and disassembling device 601 and 603 is distributed in wing exhibition upwards, by machine
Gap is into three sections of left, center, right.Three sections of wings carry out assembly and disassembly by wing assembling and disassembling device 601 and 603.Figure 12 a are illustrated
A kind of assembling-disassembling structure, the structure is ear sheet type connecting structure, and assembly and disassembly hole 611,613 is bolt connecting hole.Installation sheet 615,617 is used
It is fixedly connected with wing in auricle.Figure 12 b show the wing assembling-disassembling structure of another tubular type, and central wing passes through pipe fitting with outer wing
The form connection of socket, one section of pipe 605 is affixed with outer wing, and stretches out the segment length of outer wing one, and another section of pipe 607 is affixed with central wing
It is embedded in central wing.Pipe 605 stretches out the external cylindrical surface of outer panel and the inner cylinder face of pipe 607 coordinates.Shoe rod assembling and disassembling device position
In tail supporting rod and wing link position, for the assembly and disassembly of wing and tail supporting rod.Figure 13 is connected for a kind of tubular type tail supporting rod
Structure, wherein mounting hole 611 are the structure and fuselage bolt connection；Positioning lock tieholen 613 is tail supporting rod positioning, locking
Hole；615 is tail supporting rod locking hoop.As belonging to Figure 14, the structure is the rectangle structure with fluting to empennage assembling-disassembling structure.Wherein
Hole 625 is tail supporting rod mounting hole, and hole 621 is tail supporting rod locking hole, and hole 623 is horizontal tail mounting hole, and hole 627 is vertical fin mounting hole.
Figure 15 is another embodiment of the invention, and a kind of anury with three sections of aerofoil profiles, propeller protection device is agricultural
Sprinkling unmanned plane schematic diagram.
The present embodiment is essentially consisted in the difference of first embodiment：Fixed-wing unmanned plane shown in the present embodiment is anury
Fixed-wing unmanned plane.The size of tailless UAV is smaller, more convenient for transporting and using.The unmanned plane includes：Power set, spiral shell
Rotation oar protection device, undercarriage, wing, double vertical tails 201.
Double vertical tails 201 include fixed fin and rudder 203.Double vertical tails 201 are leaned on installed in wing both sides
At nearly wingtip.
The above is only the preferred embodiment of the present invention, rather than its limitations；Although it should be pointed out that with reference to above-mentioned each
Embodiment has been described in detail to the present invention, it will be understood by those within the art that, it still can be to above-mentioned each
Technical scheme described in embodiment is modified, or carries out equivalent to which part or all technical characteristic；And this
A little modifications and replacement, do not make the scope of the essence disengaging various embodiments of the present invention technical scheme of corresponding technical scheme.
Claims (10)
1. a kind of fixed-wing unmanned plane, it is characterised in that the wing of the unmanned plane is three-stage airfoil structure, including is arranged on machine
The slat of nose of wing, the main wing being arranged in the middle of wing and the wing flap for being arranged on trailing edge, main wing include central wing and setting
In the outer wing of central wing both sides, wing flap includes the wing flap of centrally disposed wing trailing edge and is arranged on the flaperon of outer wing trailing edge；
The pull-type propeller before the unmanned aerial vehicle body front end is provided with, the unmanned plane is provided with protection device, and protection device includes spiral
Oar protection device, wingtip protection device, empennage protection device：Propeller protection device is located at the both sides and front of propeller, bag
Skeleton and buffer unit are included, buffer unit is attached at skeleton outside, and skeleton includes the first vertical pole, the front on the left of propeller
Cross bar and right side the second vertical pole, the first vertical pole and second vertical pole one end be fixedly connected on wing, and the other end extends forward,
It is connected with cross bar；Wingtip protection device is located at wing wingtip, including left wing's tip wipes ground piece and the right flank tip wipes ground piece, is respectively mounted
The lower section of wingtip in left and right, when aircraft side wing contacts to earth, wipes ground piece and contacts to earth at first；Empennage protection device is located at unmanned plane water
The bottom of the horizontal tail wing, empennage protection device is that empennage wipes ground piece, and when aircraft excessively comes back and afterbody is contacted to earth, empennage wipes ground piece
Contact to earth at first；
Sprinkling system is provided with the unmanned plane, sprinkling system includes container, pump, jet pipe and shower nozzle, and shower nozzle passes through jet pipe and pump
Connection, pump is connected by jet pipe with container：
Container is symmetrical along the plane of symmetry of wing, and is arranged on unmanned plane center of gravity；
Shower nozzle is distributed along wing span, and connection shower nozzle is located at wing bottom with the jet pipe of pump；
Jet pipe includes the two sections of overhanging jet pipes in left and right, and overhanging jet pipe stretches out along spanwise from wingtip.
2. a kind of fixed-wing unmanned plane according to claim 1, it is characterised in that for can between the central wing and outer wing
Assembling-disassembling structure, central wing is with outer wing by some assembling and disassembling device installation wings.
3. a kind of fixed-wing unmanned plane according to claim 2, it is characterised in that the unmanned plane also includes empennage, tail
The wing includes the empennage attachment structure at wing rear and tailplane, the vertical tail at empennage attachment structure rear, empennage connection knot
Structure is connected by assembling and disassembling device with wing, and tailplane, vertical tail are connected by assembling and disassembling device with empennage attachment structure.
4. a kind of fixed-wing unmanned plane according to claim 3, it is characterised in that the assembling and disassembling device includes wing assembly and disassembly
Device, tail supporting rod-wing assembling and disassembling device and tail supporting rod-empennage assembling and disassembling device, wing assembling and disassembling device are distributed in wing exhibition upwards, will
Wing is divided into three sections of left, center, right, and three sections of wings carry out assembly and disassembly by wing assembling and disassembling device；
Wing assembling and disassembling device is ear sheet type connecting structure, and ear sheet type connecting structure is provided with assembly and disassembly hole, and assembly and disassembly hole is bolt connection
Hole, ear sheet type connecting structure is provided with the installation sheet for being fixedly connected with wing；
Or
Wing assembling and disassembling device is tubular type attachment structure, and central wing is connected with outer wing by the form of pipe fitting sleeving, one section of pipe with it is outer
The wing is affixed, and stretches out the segment length of outer wing one, and another section of pipe is embedded in central wing；
Tail supporting rod-wing assembling and disassembling device is tubular type attachment structure, and pipe is provided with mounting hole, and bolt is passed through by mounting hole and fuselage
Connection；Positioning lock tieholen is additionally provided with pipe；Pipe end is additionally provided with locking hoop；
Tail supporting rod-empennage assembling and disassembling device is the rectangle structure with fluting, is provided with tail supporting rod mounting hole, tail supporting rod locking hole, puts down
Tail mounting hole and vertical fin mounting hole.
5. a kind of fixed-wing unmanned plane according to claim 1, it is characterised in that the container is freestanding container, interior
It is placed in inside the wing, container has curved upper surface, is fitted with covering on wing；Container has arcuate lower surface, with machine
Covering laminating under the wing；
Or
Container is freestanding container, is built in inside the wing, and container has curved upper surface, is fitted with covering on wing；
Container has arcuate lower surface, is fitted with covering under wing.
6. a kind of fixed-wing unmanned plane according to claim 5, it is characterised in that the container inside has at least one
Dividing plate, near at least one hole of container bottom on dividing plate, the hole causes fluid connection in container.
7. a kind of fixed-wing unmanned plane according to claim 1, it is characterised in that in the connection shower nozzle and the jet pipe of pump
Wing lower surface is embedded in, shower nozzle spout is towards with progressively outside away from the aircraft plane of symmetry；
Or
The jet pipe of connection shower nozzle and pump is located at wing lower section, shower nozzle spout horizontally toward rear.
8. a kind of fixed-wing unmanned plane according to claim 1, it is characterised in that the overhanging jet pipe is at wingtip for can
Bending structure, during sprinkling, jet pipe with launch shape, parallel to horizontal plane, during non-sprinkling, jet pipe is rugosity, is folded up vertical
In horizontal plane, or fold back in the horizontal plane, the jet pipe after folding no longer reaches the scope beyond wingtip.
9. a kind of fixed-wing unmanned plane according to claim 1, it is characterised in that the unmanned plane also includes front three-point wheel
Formula undercarriage, undercarriage includes nose-gear and main landing gear, and nose-gear is arranged on the cross bar of propeller protection device, main
Undercarriage is arranged on fuselage bottom.
10. a kind of fixed-wing unmanned plane according to claim 1, it is characterised in that the cross bar has certain including two
First cross bar and the second cross bar of longitudinal separation, nose-gear include the inclined support bar of main support rod and both sides, main support rod one
End be fixed on the second cross bar of rear end, two inclined support bar one end are symmetrically fixed on main support rod, the other end respectively with set
The first cross bar for being scheduled on front end is fixedly connected, and main support rod, inclined support bar, the first cross bar, the second cross bar constitute tetrahedral structure.
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| CN201611258959.0A CN106697259A (en) | 2016-12-30 | 2016-12-30 | Fixed wing unmanned plane |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611258959.0A CN106697259A (en) | 2016-12-30 | 2016-12-30 | Fixed wing unmanned plane |
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| CN106697259A true CN106697259A (en) | 2017-05-24 |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107856838A (en) * | 2017-11-10 | 2018-03-30 | 肇庆市高新区晓靖科技有限公司 | A kind of unmanned plane wingfold mechanism |
| CN110203373A (en) * | 2019-05-24 | 2019-09-06 | 成都飞机工业（集团）有限责任公司 | A kind of vertical horizontal tail detaching structure of unmanned plane |
| CN110203373B (en) * | 2019-05-24 | 2022-04-08 | 成都飞机工业（集团）有限责任公司 | Structure is dismantled to unmanned aerial vehicle tail of hanging down |
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Effective date of registration: 20200409 Address after: 710000 1st floor, R & D building, No. 21, Yingbin Avenue, Xi'an Aviation base, Shaanxi Province Applicant after: Xi'an riding Aviation Technology Co.,Ltd. Address before: 710089 No. 2116, No. 21, 9 Yingbin Road, Yanliang District, Xi'an, Shaanxi, Yanliang Applicant before: Ma Xiaohui |
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