CN110466750A - A kind of Portable vertical landing scouting monitoring unmanned plane - Google Patents
A kind of Portable vertical landing scouting monitoring unmanned plane Download PDFInfo
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- CN110466750A CN110466750A CN201910761901.5A CN201910761901A CN110466750A CN 110466750 A CN110466750 A CN 110466750A CN 201910761901 A CN201910761901 A CN 201910761901A CN 110466750 A CN110466750 A CN 110466750A
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- 229910052799 carbon Inorganic materials 0.000 claims abstract description 15
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- 229920000049 Carbon (fiber) Polymers 0.000 claims description 16
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- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 16
- 238000003825 pressing Methods 0.000 claims description 12
- 238000005192 partition Methods 0.000 claims description 9
- 230000008878 coupling Effects 0.000 claims description 4
- 238000010168 coupling process Methods 0.000 claims description 4
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- 230000000694 effects Effects 0.000 description 5
- 238000000034 method Methods 0.000 description 5
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- 238000007689 inspection Methods 0.000 description 3
- 238000012806 monitoring device Methods 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000002156 mixing Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical group C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
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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
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The present invention relates to a kind of Portable vertical landings to scout monitoring unmanned plane, and four groups of quadrotor Power Components are symmetrically mounted on the rotor arm on wing, enables unmanned plane VTOL.The tail pusher propeller layout of tail portion can decline to avoid propellerslip bring wing lifting resistance characteristic.Empennage is laid out using the tail of falling V, is had the function of vertical fin and horizontal tail concurrently, be can reduce aero-structure weight.And the multistage design of empennage, wing and rotor, it can be realized folder function, it is easy to disassemble.Carbon fibre material is used on multiple components, mitigates weight, so that unmanned plane of the invention is easy to carry.Advantage is: can VTOL, be not necessarily to runway；Fast demountable, easy to operate, portable convenience；Mission payload modularization can be changed quickly.
Description
Technical field
The invention belongs to air vehicle technique fields, are related to a kind of Portable vertical landing scouting monitoring unmanned plane, especially relate to
And a kind of Portable vertical landing fixed-wing unmanned plane for executing fire behavior and scouting monitoring task.
Background technique
When fire occurs for forest, its scale and range can quickly be spread in a short time, and domestic many forest zones are not all because can
It controls forest fire in time in a relatively short period of time and causes to receive serious damage in the forest zone, it is gloomy in order to be effectively reduced
The probability that forest fires calamity occurs, advanced unmanned air vehicle technique has all been introduced in many forest zones.Compared with traditional artificial regular inspection, nothing
The application of man-machine technology can not only be effectively reduced workload of the staff in forest fire inspection work, while can also have
Effect ground improves inspection effect, reduces the probability that forest fire occurs to the full extent, and use the operation of unmanned air vehicle technique
Mode is very simple, and efficiency of patrolling and quality have all obtained significant raising.When forest fire occurs, unmanned plane can be reached
Fire extinguishing personnel are difficult to the position reached, positioning and analysis fire risk region, and operating personnel can be allowed to have tentatively forest fire
Assessment, makes science judgment to the intensity of a fire, replaces fireman to do initial reconnaissance to fire behavior by unmanned plane in this way, has ensured fire fighter
Life security.
Application No. is the patent of invention of 201610760845.X propose a kind of intelligent positioning scout fire behavior fire-fighting nobody
Wing is arranged in machine, including fuselage, GPS locator, battery pack, fuselage two sides, and propeller, wing center top is arranged in fuselage head
Antenna is set, and headlamp, carry water tank below wing is arranged in wing front.The advantages of invention is that carrying water tank storage is a certain amount of
Water, fire source can be promptly put out when the intensity of a fire is not very big, can remote control equipment, intelligence degree is high；The disadvantage is that rising
It is high to drop site requirements, can not achieve VTOL.
Application No. is 201610968601.0 patents of invention to propose a kind of fixed-wing unmanned plane for fire fighting monitoring, packet
Include fixed-wing unmanned plane body, aviation mechanism, flight control units, remote control receiver, sensor module etc..Monitoring device peace
On fixed-wing unmanned plane body, Infrared Image Information and color image information are sent to by monitoring device by communication module
Monitoring device acquired image information is transmitted to remote monitoring center by master controller, master controller.The advantages of invention is
Using binocular vision structure, the problem of clear image under several scenes acquires can solve, it is easy to use, it is at low cost；Disadvantage
It is that unmanned plane is integrally non-dismountable, it is inconvenient to carry.
Summary of the invention
Technical problems to be solved
In order to avoid the shortcomings of the prior art, the present invention proposes that a kind of Portable vertical landing scouting monitors nobody
Machine solves the problems, such as to exist in the prior art using limiting to, carry and use inconvenience.
Technical solution
Monitoring unmanned plane is scouted in a kind of Portable vertical landing, it is characterised in that including fuselage 1, wing 2, rotor arm 13,
Empennage 3, nose-gear 4, rear undercarriage 5, quadrotor Power Component 6 and fixed-wing Power Component 7；Fuselage 1 is streamlined, head
Shape is parabola, and posterior segment is gradually tapered up to tail portion；Fuselage two sides are equipped with wing 2, and wing 2 is equipped with perpendicular rotor
Arm 13, sets that there are two quadrotor Power Component 6, the two sides for the wing 2 that is placed in, four quadrotor power packages on each rotor arm 13
Part 6 is symmetrically mounted on the rotor arm 13 of 2 two sides of wing relative to fuselage 1；Empennage 3 is laid out using the tail of falling V, the both ends of V word
Tail supporting rod 34 is connect with rotor arm 13；Fixed-wing Power Component 7 is laid out using tail pusher propeller, 11 axis connection carbon of driving motor
Fiber thrust paddle 12, positioned at the tail portion of fuselage 1；The fuselage interior is divided into two bay sections, is followed successively by equipment compartment 14 from front to back
With battery flat 15；The quadrotor Power Component 6 includes carbon fiber spiral paddle 8, brshless DC motor 9 and motor cabinet 10, carbon fiber
Propeller 8 and 9 axis connection of brshless DC motor are tieed up, brshless DC motor 9 is connected on rotor arm 13 by motor cabinet 10；Before rise and fall
Frame 4 and rear undercarriage 5 are respectively arranged on the front-end and back-end of 1 bottom of fuselage.
The wing 2 includes middle section wing 24 and two sides wing 25, and middle section wing 24 is merged with fuselage 1, two sides wing 25
On aileron 26 is installed.
The two sides wing 25 is segmentation structure, and pressing lock 28 is fixed in the wing of middle section close to section part, bolt
29 are fixed at the aerofoil contour of two sides, are connect by the carbon pipe 27 that can be plugged with middle section wing 24, by pressing lock 28 with
Middle section rotor arm 13 is locked；The pressing lock 28 is latched using spring press formula.
The empennage 3 includes middle section empennage 30 and two sides empennage 31, passes through conjunction between middle section empennage 30 and two sides empennage 31
Page 33 connects, and two sides empennage can be rotated down folding around hinge, and two sides empennage lower end is fixed with tail supporting rod 34 by gluing；Two
Rudder face 32 is installed on the empennage of side.
The tail supporting rod 34 at the both ends of the V word is connect with rotor arm 13 uses quick-release coupling 35, including rotor arm connection 36,
Shoe knock-off joint 37 and hand twist adapter sleeve 38；36 one end of rotor arm connection is fixed by bolt and rotor arm, outside other end cylinder
There is screw thread on surface；37 one end of shoe knock-off joint is fixed by bolt and tail supporting rod 34, and the other end is inserted into rotor arm connection 36；Hand is twisted
The inner surface of adapter sleeve 38 has screw thread, twists being screwed on the external screw thread of rotor arm connection 36 of adapter sleeve by hand.
The fixation of the rotor arm 13 and wing 2 uses pipe clamp 40, and pipe clamp is made of two semicircular rings, semicircular ring two sides
Excircle is equipped with link block, has the connecting hole of perforation on link block, and make the connection for being located at two semicircular ring the same sides
Hole is concentric；The aperture of the pipe clamp inner hole and the outer diameter of rotor arm 13 are interference fitted.
The rotor arm 13 is multistage carbon fiber pipe composition, is connected between two sections using rotary shaft folded piece 39.
There are partition 16 and frame 17 made of carbon fibre material in the battery flat, for accommodating and supporting battery.
Beneficial effect
Monitoring unmanned plane is scouted in a kind of Portable vertical landing proposed by the present invention, and four groups of quadrotor Power Components are symmetrically pacified
On rotor arm on wing, enable unmanned plane VTOL.The tail pusher propeller layout of tail portion can be to avoid spiral shell
Revolve the decline of paddle slip-stream bring wing lifting resistance characteristic.Empennage is laid out using the tail of falling V, is had the function of vertical fin and horizontal tail concurrently, can be subtracted
Flivver construction weight.And the multistage design of empennage, wing and rotor, it can be realized folder function, it is easy to disassemble.Multiple
Carbon fibre material is used on component, mitigates weight, so that unmanned plane of the invention is easy to carry.
Scouting monitoring unmanned plane proposed by the present invention has the advantage that compared with tradition scouts monitoring unmanned plane
(1) can VTOL, be not necessarily to runway
Scout monitoring unmanned plane using VTOL fixed-wing layout, by more rotors can VTOL, not by landing
The advantage of point limitation and fixed-wing unmanned plane during flying speed is fast, the advantage of long endurance and long voyage organically combines, reduces
Requirement and limitation when fixed-wing unmanned plane landing to place, realize the VTOL and fixed-wing high-performance cruise of unmanned plane
Function.
(2) fast demountable, easy to operate, portable convenience
The equal fast demountable of wing, empennage of monitoring unmanned plane is scouted, rotor arm can fold 90 °, folding and unfolding to wing two
Side, empennage can also substantially reduce unmanned plane and store the space occupied, the task devices such as video camera of carrying can with folding and retraction
With according to different mission requirements quick-replaceables, unmanned plane carries very easy to use quick.
(3) mission payload modularization can be changed quickly
Mission payload modularized design, reconnaissance UAV can need quick-replaceable different task load mould according to different task
Block, such as high-resolution digital camera, five camera lens inclined cameras, single-lens camera, infrared scanner, laser scanner and magnetic survey
The equipment such as instrument, realize the diversification of task ability, and working service is simple.
Detailed description of the invention
Fig. 1 is the axonometric drawing of unmanned plane；
Fig. 2 is the top view of unmanned plane；
Fig. 3 is the side view of unmanned plane；
Fig. 4 is the front view of unmanned plane；
Fig. 5 is fuselage interior structural schematic diagram；
Fig. 6 is that wing docks schematic diagram；
Fig. 7 is pressing lock schematic diagram；
Fig. 8 is tail structure schematic diagram；
Fig. 9 is 35 structural schematic diagram of quick-release coupling；
Figure 10 is motor cabinet schematic diagram；
Figure 11 is 39 schematic diagram of folded piece；
Figure 12 is 40 schematic diagram of pipe clamp；
Figure 13 is 41 schematic diagram of hanger.
In figure:
1. fuselage；2. wing；3. empennage；4. nose-gear；Undercarriage after 5.；6. quadrotor Power Component；7. fixed-wing
Power Component；8. carbon fiber spiral paddle；9. brshless DC motor；10. motor cabinet；11. driving motor；12. thrust paddle；13. rotation
Wing arm；14. equipment compartment；15. battery flat；16. partition；17. frame；18. mission payload；19. flight controller；20. battery；
21. equipment hatchcover；22. battery hatch；23. assembling lid；24. middle section wing；25. two sides wing；26. aileron；27. carbon pipe；
28. pressing lock；29. bolt；30. middle section empennage；31. two sides empennage；32. rudder face；33. hinge；34. tail supporting rod；35. quick-release
Connector；36. rotor arm connection；37. shoe knock-off joint；38. hand twists adapter sleeve；39. folded piece；40. pipe clamp；41. hanger；42.
Upper link block；43. lower connecting block；44. spring clip.
Specific embodiment
Now in conjunction with embodiment, attached drawing, the invention will be further described:
The present embodiment is a kind of Portable vertical landing scouting monitoring unmanned plane, including fuselage 1, wing 2, empennage 3, preceding
Fall frame 4, rear undercarriage 5, quadrotor Power Component 6, fixed-wing Power Component 7.
Fuselage 1 is streamlined, and head configuration is parabola, and posterior segment is gradually tapered up to tail portion；Fuselage two sides are equipped with wing
2, wing 2 is equipped with perpendicular rotor arm 13, sets that there are two quadrotor Power Components 6 on each rotor arm 13, is placed in
The two sides of wing 2, four quadrotor Power Components 6 are symmetrically mounted on the rotor arm 13 of 2 two sides of wing relative to fuselage 1；Tail
The wing 3 is laid out using the tail of falling V, and the tail supporting rod 34 at the both ends of V word is connect with rotor arm 13；Fixed-wing Power Component 7 uses tail pushing-type
Propeller layout, 11 axis connection carbon fiber thrust paddle 12 of driving motor, positioned at the tail portion of fuselage 1；The fuselage interior is divided into two
A bay section is followed successively by equipment compartment 14 and battery flat 15 from front to back；The quadrotor Power Component 6 include carbon fiber spiral paddle 8,
Brshless DC motor 9 and motor cabinet 10, carbon fiber spiral paddle 8 and 9 axis connection of brshless DC motor, brshless DC motor 9 pass through
Motor cabinet 10 connects on rotor arm 13；Nose-gear 4 and rear undercarriage 5 are respectively arranged on the front-end and back-end of 1 bottom of fuselage.
The quadrotor Power Component 6 includes carbon fiber spiral paddle 8, brshless DC motor 9 and motor cabinet 10, the carbon fiber
For dimension propeller 8 by connecting at the top of bolt and brshless DC motor 9,9 lower surface of brshless DC motor is mounted on motor cabinet 10
Upper surface, blending bolt connection.
There is motor installing hole in the upper surface of the motor cabinet 10, is clipped on the carbon pipe of rotor arm 13 below, and blending bolt is twisted
Tightly, prevent motor cabinet from sliding on rotor arm.
The fixed-wing Power Component 7 includes driving motor 11 and thrust paddle 12, and thrust paddle 12 is carbon fiber spiral paddle, is led to
It crosses bolt to be connected with driving motor 11, driving motor 11 is bolted on the tail portion of the fuselage 1, using tail pushing-type spiral
Paddle layout can decline to avoid propellerslip bring wing lifting resistance characteristic.
The fuselage 1 is streamlined fuselage, and fuselage head uses traditional parabolic profile, and fuselage posterior segment gradually tapers up
To tail portion.Fuselage interior is divided into two bay sections, is followed successively by equipment compartment 14 and battery flat 15 from front to back, places electricity in battery flat 15
Pond 20, the battery 20 are lithium polymer battery, are mainly used for electric energy needed for providing unmanned plane during flying, using existing
Finished product；There are partition 16 and frame 17 made of carbon fibre material in battery flat, for accommodating and supporting battery.It is same in equipment compartment 14
Sample has partition and frame made of carbon fibre material, and mission payload 18 is mounted on partition lower surface, the flight by hanger 41
Controller 19 is bolted on the upper surface of partition, control when for unmanned plane during flying, using existing finished product.
Fuselage upper surface opening is successively equipment hatchcover 21, battery hatch 22 and assembly lid 23, equipment compartment from front to back
Lid 21 flies control and mission payload for the ease of installing, and battery hatch 22 assembles lid 23 for the ease of the placement and taking-up of battery
Facilitate the installation of wing and afterbody driving motor.
The wing 2 includes middle section wing 24 and two sides wing 25, and the middle section wing 24 is merged with fuselage 1, and described two
Aileron 26 is installed, the two sides wing 25 is connect with middle section wing 24 by pluggable carbon pipe 27, passed through on side wing 25
Pressing lock 28 is locked with middle section wing.Pressing lock 28 is fixed in the wing of middle section close to section part, and bolt 29 is fixed
At the aerofoil contour of two sides.When wing is installed, carbon pipe is first inserted into middle section wing, then pressing lock button, bolt is caught in
In lock, release button completes the docking and locking of wing.
The pressing lock 28 latches for spring press formula, and shell is made of aluminium alloy, is fixedly connected with card slot below button,
It is fixed with spring between card slot two sides and shell, when push button, card slot is moved down, the circular open in alignment housings, spiral shell
Card slot is protruded on the head of bolt, then release button, and the elastic force of spring holds out against card slot upwards, blocks bolt, reaches locking wing
Effect.
The empennage 3 is laid out using the tail of falling V, and inverted V type empennage has the function of vertical fin and horizontal tail concurrently, can reduce aircaft configuration
Weight, it is easy to disassemble, reduce empennage between and the interference drag between empennage and fuselage, avoid the influence of wing air-flow as far as possible.
Empennage 3 includes middle section empennage 30 and two sides empennage 31, is equipped with rudder face 32, middle section empennage 30 and two sides empennage 31 on the empennage of two sides
Between connected by hinge 33, two sides empennage can be rotated down folding around hinge, and two sides empennage lower end passes through with tail supporting rod 34
Gluing is fixed, and when storage can fold empennage, reduces memory space.
The quick-release coupling 35 includes that rotor arm connection 36, shoe knock-off joint 37 and hand twist adapter sleeve 38.Rotor arm connection
36 one end are fixed by the carbon pipe of bolt and rotor arm, and the other end cylindrical outer surface being relatively large in diameter has screw thread, shoe knock-off joint
37 one end are fixed by bolt and tail supporting rod, and the other end is inserted into rotor arm connection 36, and the inner surface that the hand twists adapter sleeve 38 has
Screw thread twists being screwed on rotor arm connection of adapter sleeve by hand, and effect is fixed tail supporting rod, after preventing connector to be inserted into
It skids off outward.Hand is twisted adapter sleeve when dismantling empennage to back-out, extracts shoe knock-off joint.
The rotor arm 13 is process using carbon fiber pipe, and rotor arm carbon pipe is connected by folded piece 39, every rotor
It is equipped with folded piece before and after arm, 90 ° can be folded before and after rotor arm, is retractable in wing two sides, reduces parking space.The folding
Overlapping piece 39 is rotary shaft folded piece, and using existing finished product, folded piece both ends sleeve is bolted with carbon fiber pipe respectively, is led to
The shaft crossed among two sleeves can be with rotary folding.
The pipe clamp 40 is used to for rotor arm 13 being fixed on the lower surface of the wing 2.The pipe clamp is by two semicircular ring groups
At.External peripheral surface in each semicircular ring two sides has link block respectively, there is the connecting hole of perforation on each link block respectively, and
Keep the connecting hole for being located at two semicircular ring the same sides concentric.After two semicircular rings are to full circle is combined into, pipe clamp is formed.It is described
The aperture of pipe clamp inner hole and the outer diameter of rotor arm 13 are interference fitted.
The undercarriage of unmanned plane uses first three point type, and the nose-gear 4 is installed on the nosing lower surface；It is described
Undercarriage 5 is installed on the aft body lower surface afterwards；Undercarriage is not used in takeoff, only in the VTOL stage for branch
Aircraft is supportted, nose-gear and rear undercarriage are all made of aluminum alloy materials, and design has mounting hole on undercarriage top platform, pass through spiral shell
Bolt is connect with fuselage lower surface.
The hanger 41 is used to mission payload 18 being mounted on partition lower surface, and hanger is by upper link block 42, lower connecting block
43 and spring clip 44 form.Upper link block top is bolted on partition lower surface, and sliding slot is arranged at lower part；Lower connecting block it is upper
Portion is sliding block, is matched with sliding slot, can be slided in sliding slot, lower part is bolted with mission payload；Spring picks up limit
The effect of position first presses spring clip when replacing mission payload, and the sliding block of lower connecting block is slid into sliding slot, and trip spring presss from both sides,
Spring clip clamping slide mission payload will not.
The specifically used mode proposed by the present invention for scouting monitoring unmanned plane are as follows:
When unmanned plane, which needs to be implemented, scouts monitoring task, by staff then unmanned plane Fast Installation is grasped first
Vertical unmanned plane is taken off with quadrotor mode, is transformed into fixed-wing mode from quadrotor mode and is flown to mission area, in fixed-wing mould
Cruise, which executes, under formula scouts monitoring task, and customized type course line settable for scope of reconnaissance makes unmanned plane according to scheduled course line
It is monitored；In the higher particular time of some temperature, unmanned plane circulatory monitoring without interruption can the discovery within first time
Fire behavior, and it is handled in time, it avoids causing more serious consequence because of the fire behavior within the scope of partial region, when
When there is the case where fire in certain in forest zone, unmanned plane by the computer of conflagration area video real-time transmission to commanding,
The specific location that fire occurs is determined convenient for staff, and forest fire is controlled within the shortest time.
Claims (8)
1. monitoring unmanned plane is scouted in a kind of Portable vertical landing, it is characterised in that including fuselage (1), wing (2), rotor arm
(13), empennage (3), nose-gear (4), rear undercarriage (5), quadrotor Power Component (6) and fixed-wing Power Component (7)；Machine
Body (1) is streamlined, and head configuration is parabola, and posterior segment is gradually tapered up to tail portion；Fuselage two sides are equipped with wing (2), wing
(2) it is equipped with perpendicular rotor arm (13), sets that there are two quadrotor Power Component (6) on each rotor arm (13), is split
In the two sides of wing (2), four quadrotor Power Components (6) are symmetrically mounted on the rotor of wing (2) two sides relative to fuselage (1)
On arm (13)；Empennage (3) is laid out using the tail of falling V, and the tail supporting rod (34) at the both ends of V word is connect with rotor arm (13)；Fixed-wing is dynamic
Power component (7) is laid out using tail pusher propeller, driving motor (11) axis connection carbon fiber thrust paddle (12), is located at fuselage (1)
Tail portion；The fuselage interior is divided into two bay sections, is followed successively by equipment compartment (14) and battery flat (15) from front to back；Four rotation
Wing Power Component (6) includes carbon fiber spiral paddle (8), brshless DC motor (9) and motor cabinet (10), carbon fiber spiral paddle (8)
With brshless DC motor (9) axis connection, brshless DC motor (9) passes through in motor cabinet (10) connection rotor arm (13)；Before rise and fall
Frame (4) and rear undercarriage (5) are respectively arranged on the front-end and back-end of fuselage (1) bottom.
2. monitoring unmanned plane is scouted in Portable vertical landing according to claim 1, it is characterised in that: wing (2) packet
Middle section wing (24) and two sides wing (25) are included, middle section wing (24) is merged with fuselage (1), and two sides wing is equipped with pair on (25)
The wing (26).
3. monitoring unmanned plane is scouted in Portable vertical landing according to claim 3, it is characterised in that: the two sides wing
It (25) is segmentation structure, pressing lock (28) is fixed in the wing of middle section close to section part, and bolt (29) is fixed on two sides machine
Wing section part is connect by the carbon pipe (27) that can be plugged with middle section wing (24), and pressing lock (28) and middle section rotor are passed through
Arm (13) is locked；The pressing lock (28) is latched using spring press formula.
4. monitoring unmanned plane is scouted in Portable vertical landing according to claim 1, it is characterised in that: empennage (3) packet
Middle section empennage (30) and two sides empennage (31) are included, is connected between middle section empennage (30) and two sides empennage (31) by hinge (33),
Two sides empennage can be rotated down folding around hinge, and two sides empennage lower end is fixed with tail supporting rod (34) by gluing；Two sides empennage
On rudder face (32) are installed.
5. monitoring unmanned plane is scouted in Portable vertical landing according to claim 1, it is characterised in that: the both ends of the V word
Tail supporting rod (34) connect with rotor arm (13) using quick-release coupling (35), including rotor arm connection (36), shoe knock-off joint
(37) and hand twists adapter sleeve (38)；Rotor arm connection (36) one end is fixed by bolt and rotor arm, other end cylindrical outer surface
There is screw thread；Shoe knock-off joint (37) one end is fixed by bolt and tail supporting rod (34), and the other end is inserted into rotor arm connection (36)；Hand
The inner surface for twisting adapter sleeve (38) has screw thread, and the external screw thread for being screwed at rotor arm connection (36) of adapter sleeve is twisted by hand
On.
6. monitoring unmanned plane is scouted in Portable vertical landing according to claim 1, it is characterised in that: the rotor arm (13)
Fixation with wing (2) uses pipe clamp (40), and pipe clamp is made of two semicircular rings, and the excircle of semicircular ring two sides is equipped with connection
Block has the connecting hole of perforation on link block, and keeps the connecting hole for being located at two semicircular ring the same sides concentric；In the pipe clamp
The aperture in hole and the outer diameter of rotor arm (13) are interference fitted.
7. monitoring unmanned plane is scouted in Portable vertical landing according to claim 1, it is characterised in that: the rotor arm (13)
It forms for multistage carbon fiber pipe, is connected between two sections using rotary shaft folded piece (39).
8. monitoring unmanned plane is scouted in Portable vertical landing according to claim 1, it is characterised in that: have in the battery flat
Partition made of carbon fibre material (16) and frame (17), for accommodating and supporting battery.
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