CN110116802A - A kind of big loading small-sized unmanned aircraft of high universalizable - Google Patents
A kind of big loading small-sized unmanned aircraft of high universalizable Download PDFInfo
- Publication number
- CN110116802A CN110116802A CN201910370346.3A CN201910370346A CN110116802A CN 110116802 A CN110116802 A CN 110116802A CN 201910370346 A CN201910370346 A CN 201910370346A CN 110116802 A CN110116802 A CN 110116802A
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- China
- Prior art keywords
- strut
- wing
- unmanned aircraft
- sized unmanned
- big
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Classifications
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- 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
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- 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
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
-
- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
Abstract
The present invention provides a kind of big loading small-sized unmanned aircraft of high universalizable.The aircraft includes: blended wing-body body, and two fixed main wings of the body two sides are arranged in, and two below described two main wings struts are arranged in and the modularization fin assembly of two strut rear ends is arranged in.Described two main wings make full machine have lesser stalling speed using the high-lift airfoil after optimization；The body has carried out blended wing-body design, there is biggish stowage in body, multiple-task load can be carried, simultaneously, full machine has flexible landing ability, it can be needed to carry out catapult-assisted take-off, takeoff or VTOL according to task, to improve unmanned vehicle to the adaptability and execution efficiency of different type aerial mission.
Description
Technical field
The present embodiments relate to vehicle technologies more particularly to a kind of high pass to load small-sized unmanned aircraft with big.
Background technique
Small-sized fixed-wing unmanned plane is China is military, civil field is widely used.Such as in military domain, it can be used for battlefield
Scouting, information gathering, information support etc.；In civil field, it can be used for traffic tour, resource exploration, agricultural plant protection etc..Although nothing
Man-machine technology is increasingly mature, but small-sized fixed-wing unmanned plane at present, and majority is both for its special-purpose, in particular flight environment
Lower carrying particular task load carries out actual job.When facing the extraneous factors such as geographical environment, mission requirements, mission payload not
When certainty changes, the limitation of mission payload geometric dimension, the constraint of take-off venue environment and activity duration requirement of leaving a blank
The restriction of the factors such as raising will be substantially reduced existing small-sized fixed-wing unmanned vehicle to the adaptability of aerial mission and hold
Row ability, and then limit unmanned vehicle to a certain extent and be more widely applied.
Summary of the invention
In view of the above-mentioned drawbacks in the prior art, the present invention provides a kind of high pass big loading small-sized unmanned aircraft, energy
Enough variations according to geographical environment and mission requirements, accordingly carry out catapult-assisted take-off, takeoff or VTOL；Meanwhile the wing
Body merges big volume body can carry the mission payload of a variety of larger geometric dimensions simultaneously, to the adaptability of aerial mission and
Executive capability is been significantly enhanced.
The present invention provides a kind of big loading small-sized unmanned aircraft of high universalizable, comprising:
Two wings of the body two sides are arranged in the big volume body of blended wing-body, are arranged in the body tail portion
Thrust propeller, the strut below the wing is set and the fin assembly of strut rear end is set；
The wing is symmetrically distributed in the body two sides along the body longitudinal axis, in the trailing edge, symmetrically
It is provided with integral type flaperon；
The strut is symmetricly set below the wing and at wing wing root position；
There are two vertical tail, two vertical tail rears are symmetrically arranged with rudder for the strut rear end setting；
Tailplane is connected at the vertical tail wing tip, the tailplane rear is provided with elevator.
Optionally, the wing is the straight wing, tapered airfoil or swept-back wing.
Optionally, the host wing is high mounted wing, midsetwing or lower single-blade with respect to body installation site.
Optionally, engine is built-in in body tail portion or exposed, and when being built in body, body back will be provided with
Air intake duct.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described.It should be appreciated that the accompanying drawings in the following description is of the invention
Some embodiments, are used to provide further understanding of the present invention and are not construed as limiting the invention.
Fig. 1 is the big knot loaded under small-sized unmanned aircraft catapult-assisted take-off mode of high universalizable provided in an embodiment of the present invention
Structure schematic diagram；
Fig. 2 is the big loading small-sized unmanned aircraft catapult-assisted take-off mode flowering structure of high universalizable provided in an embodiment of the present invention
Component assembling schematic diagram
Fig. 3 is the big knot loaded under small-sized unmanned aircraft VTOL mode of high universalizable provided in an embodiment of the present invention
Structure schematic diagram；
Fig. 4 is the big loading small-sized unmanned aircraft VTOL mode flowering structure of high universalizable provided in an embodiment of the present invention
Component assembling schematic diagram
Description of symbols:
1: blended wing-body body；2: host wing；3: vertical tail；4: tailplane；5: tail pushes away propeller；6: flaperon；
7: rudder；8: elevator；9: strut；10: air intake duct；11: exhaust pipe；12: preposition lifting propeller；13: postposition lift spiral shell
Revolve paddle
Specific embodiment
In order to make the object, technical scheme and advantages of the embodiment of the invention clearer, below in conjunction with the embodiment of the present invention
In attached drawing, technical scheme in the embodiment of the invention is clearly and completely described.It should be appreciated that described herein
Specific embodiment is only used to explain the present invention, is not intended to limit the present invention protection content.
The big loading small-sized unmanned aircraft of high pass provided in this embodiment has catapult-assisted take-off, takeoff, vertically rises
Three kinds of landing modes drop.Fig. 1 is that a kind of high pass that present invention implementation provides loads small-sized unmanned aircraft catapult-assisted take-off mould with big
Structural schematic diagram under formula.Fig. 1 provide a kind of big the loadings unmanned vehicle of high universalizable include: body 1, host wing 2, vertically
Empennage 3, tailplane 4, tail push away propeller 5, flaperon 6, rudder 7, elevator 8, strut 9.Body 1 and host wing 2, host
The wing 2 with strut 9 and strut 9 can carry out dismantling connection with vertical tail 3 in order to transport, structure member assembling schematic diagram
As shown in Figure 2.
Host wing 2 is symmetricly set on 1 two sides of body, and strut 9 is arranged below two host wings and at wing root position.
Two vertical tails 3 are symmetricly set on the rear end of strut 9 along the longitudinal axis of body 1.The wing of tailplane 4 and vertical tail 3
Point can carry out dismantling connection.Under VTOL mode, the front end of strut 9 can extend forward, and be provided in the front end of strut
Preposition lifting propeller 12, while the equalising torque to guarantee full machine, are provided with postposition lifting propeller in the rear end of strut 9
13。
Body 1 is designed using blended wing-body, is seamlessly transitted between body 1 and host wing 2, and the full machine cruising phase wing is being reduced
Body loading space is increased while body interference drag again.Head is conducive to improve body using the configuration design of class olecranon
Pitching moment characteristic.It is the leading portion of body 1 from from head to about 1/3 body extension position, is set as mission payload cabin, energy
Enough accommodate the task device of a variety of geometric dimensions such as photoelectricity ball, radar, camera.1 middle section of body is provided with big volume fuel tank, full oil
Under state, fuel weight coefficient can achieve 0.5.1 middle section two sides of body are connect with the forward and backward girder of host wing 2, wing rear spar
It is connected on the bulkhead of 1 middle section rear end of body, bulkhead is solid siding, is sealed using the squab panel as fuel tank to fuel tank.
1 back segment of body is mainly equipped with tail and pushes away propeller 5 and engine, and tail pushes away propeller for providing thrust when full machine is flat to fly.
Optionally, engine is built-in in body tail portion or exposed；When engine embedded when body tail portion, then accordingly exist
Body back and abdomen are provided with air intake duct.
Optionally, the cross-sectional area shape of body 1 can be round, ellipse or other shapes, the cross of 1 back segment of body
Sectional area shape can be identical as body middle section.The present embodiment is not defined the cross-sectional area shape of body 1.
Optionally, body is mainly made of aluminium sash, aluminum reinforcing frame, aluminum stringer with wing structure.Around frame
It is covered with covering, composite material can be selected in skin material, can effectively reduce full machine while enhancing body and wing bearing capacity
Construction weight.
Host wing 2 is symmetricly set on the two sides in 1 middle section of body along the longitudinal axis of body 1, is nobody for cruising phase
Aircraft provides main lift.Host wing 2 can be the geometric shapes such as the straight wing, swept-back wing, tapered airfoil, and the present embodiment is not
The geometric shape of host wing 2 is defined.
Optionally, host wing 2 is bolted or is welded on the middle part of body 1, rib can by high-intensitive aviation foam with
Carbon fiber board is bonded, and coated with covering around rib, covering can be made of carbon fibre material.
2 rear of host wing is provided with flaperon, can be provided simultaneously with the double action of wing flap and aileron, and flaperon is done
It is realized by the built-in steering engine of flaperon shaft and trailing edge junction.When the flaperon of body two sides is same inclined at present, then
With wing flap lift-rising effect so as to improve the takeoff and landing performance of unmanned vehicle；When the differential deflection of the flaperon of body two sides, nothing
People's aircraft will generate rolling moment to change of flight posture.
Below host wing 2 at wing root, the strut 9 there are two equal length is symmetrical arranged along body longitudinal axis.
The connection type of strut and host wing can be connected by screw bolts, weld or hookup is attached, and can use high-strength
The aeronautical material of degree, lightweight, such as aluminium alloy or titanium alloy are manufactured, and can also be reduced while enhancing strut bearing capacity
The weight of strut.
The rear end of strut 9 is provided with vertical tail 3, wherein fixed fin there is course to increase steady make unmanned vehicle
With；Fixed fin rear is provided with rudder, and in order to the directional control of unmanned vehicle, rudder is deflected through direction
The built-in steering engine of rudder shaft and fixed fin junction is realized.Vertical tail 3 and strut 9 can fast assembling-disassembling, transporting
Cheng Zhongke individually stores it, is conducive to reduce the damage to vertical tail component.
Tailplane 4, the connection of vertical tail wing tip and tailplane wing tip are connected at the wing tip of two vertical tails 3
By the way of rounding off.The rear of tailplane 4 is provided with elevator, thus longitudinal pitching movement to unmanned vehicle
It is manipulated, elevator is deflected through the built-in steering engine reality being installed at the tailplane plane of symmetry close to horizontal stabilizer rear
It is existing.
Optionally, a kind of high pass provided in an embodiment of the present invention can be adopted with big loading its takeoff phase of small-sized unmanned aircraft
With catapult-assisted take-off mode, landing modes can be used parachuting mode and recycle.Recovery system is by parachute deployment means, main chute, falling-off connector etc.
It constitutes, parachute is circular parachute, is mounted in body 1 after fuel tank position.If because certain specific factors do not allow catapult-assisted take-off
It is recycled with parachuting, also can choose the sliding mode for running landing.
Fig. 3 is the structural schematic diagram under VTOL mode provided in this embodiment.Under VTOL mode, nobody flies
Row device is in addition to including: that body 1, host wing 2, vertical tail 3, tailplane 4, tail push away propeller 5, flaperon 6, rudder 7, rise
It further include preposition lifting propeller 12 and postposition lifting propeller 13 outside drop rudder 8, strut 9.It is dismounted under catapult-assisted take-off mode
Mode is similar, VTOL mode lower body 1 and host wing 2, host wing 2 and strut 9 and strut 9 and vertical tail 3 into
For row dismantling connection in order to transport, structure member assembling schematic diagram is as shown in Figure 4.
When the big loading unmanned vehicle of a kind of high universalizable provided in this embodiment carries out VTOL, preposition lift spiral
Paddle 12 and the thrust axis of postposition lifting propeller 13 are perpendicular to the ground, and it is vertical to provide simultaneously that the two constitutes quadrotor mode
Upward lift drives full machine to realize VTOL rapidly.After the completion of taking off, by adjusting preposition lifting propeller 12 and postposition
The revolving speed of lifting propeller 13 realizes the hovering of full machine so that the lift for generating the two balances each other with aircraft gravity.When complete
Machine needs to come back, bows and when lateral movement, can make its generation by controlling the revolving speed of preposition propeller and rear-mounted propeller
Lift come back/bow or lateral rolling moment to generate in front, rear, left and right difference, and then realize aircraft
Pitching movement or lateral rolling.
It is loaded after small-sized unmanned aircraft completion takes off vertically in a kind of high pass provided in this embodiment with big, tail pushes away spiral shell
It revolves paddle 5 and starts high speed rotation, providing forward thrust for full machine makes its acceleration is flat to fly, hence into the transition and conversion stage, at this point, preceding
It sets lifting propeller 12 and postposition lifting propeller 13 still provides lift for full machine, but revolving speed is with the increase of full machine forward flight speed
It is gradually reduced, then stops working wait be greater than after stalling speed；Or preposition lifting propeller 12 and postposition lifting propeller 13
It is remained unchanged in the revolving speed in transition and conversion stage, is greater than after stalling speed to full machine level speed and stops working rapidly.
When a kind of small-sized unmanned aircraft that embodiment provides enters flat winged mode, preposition lifting propeller 12 and postposition
Lifting propeller 13 stops working, and propeller blade is locked by locking mechanism.Full machine lift master needed for the flat winged stage
It to be provided by wing 2, by corresponding pneumatic rudder face, such as flaperon is risen for pitching movement, rolling movement and the yawing rotation of full machine
Drop rudder and elevator are manipulated and are controlled.
Similarly, unmanned vehicle provided in an embodiment of the present invention by flat winged state be transferred to the transition and conversion stage subsequently into
When VTOL process, it is vertical that preposition lifting propeller 12, postposition lifting propeller 13 and tail, which push away the course of work of propeller 5,
It directly takes off and turns the flat inverse process for flying over journey, to complete the vertical landing movement of full machine, details are not described herein again.
Finally, it should be noted that the above various embodiments is only the explanation to technical solution of the present invention, rather than its limitations；To the greatest extent
Present invention has been described in detail with reference to the aforementioned embodiments for pipe, for a person skilled in the art, still may be used
To modify the technical solutions described in the foregoing embodiments, or some or all of the technical features are carried out etc.
With replacement；And these are modified or replaceed, technical solution of various embodiments of the present invention that it does not separate the essence of the corresponding technical solution
Range.
Claims (6)
1. a kind of big loading small-sized unmanned aircraft of high universalizable characterized by comprising the big volume fuselage of blended wing-body, if
Two fixed main wings in the body two sides are set, the tail pusher propeller of the body tail portion is set, are arranged in host wing
The strut of two equal lengths of lower section, and full machine has three kinds of catapult-assisted take-off, takeoff and VTOL modes of taking off.
The strut of described two equal lengths is symmetricly set below the host wing along the body longitudinal axis；
The strut rear end is symmetrical arranged along the body longitudinal axis there are two vertical tail；
The wing tip of described two vertical tails is attached by tailplane；
Described two vertical tails and tailplane comprising modules fin assembly, are detachably connected with the strut.
2. the big loading small-sized unmanned aircraft of high universalizable according to claim 1, it is characterised in that: blended wing-body great Rong
It is provided with big volume fuel tank in the middle part of product body, fuel weight coefficient maximum is up to 0.5.
3. the big loading small-sized unmanned aircraft of high universalizable according to claim 1, it is characterised in that: before and after the strut
End is provided with two pairs of lifting propellers to complete VTOL mode.
4. the big loading small-sized unmanned aircraft of high universalizable according to claim 1, it is characterised in that: engine is installed on
Body tail portion, it is both built-in can also be external.When engine embedded when body tail portion, body back is correspondingly provided with air inlet
Road.
5. the big loading small-sized unmanned aircraft of high universalizable according to claim 2, it is characterised in that two wings of connection
The body bulkhead of the back rest constitutes the rear wall of fuel tank.
6. the big loading small-sized unmanned aircraft of high universalizable according to claim 3, it is characterised in that: the strut and institute
Dismantling connection can be carried out by stating host wing, and the strut can be dismantled flexibly with two pairs of lifting propellers.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910370346.3A CN110116802A (en) | 2019-05-06 | 2019-05-06 | A kind of big loading small-sized unmanned aircraft of high universalizable |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910370346.3A CN110116802A (en) | 2019-05-06 | 2019-05-06 | A kind of big loading small-sized unmanned aircraft of high universalizable |
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| CN110116802A true CN110116802A (en) | 2019-08-13 |
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|---|---|---|---|
| CN201910370346.3A Pending CN110116802A (en) | 2019-05-06 | 2019-05-06 | A kind of big loading small-sized unmanned aircraft of high universalizable |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111137446A (en) * | 2019-12-26 | 2020-05-12 | 中国空气动力研究与发展中心 | Pneumatic layout of multi-rotor vertical take-off and landing unmanned aerial vehicle with stalling function |
| CN112373685A (en) * | 2020-11-23 | 2021-02-19 | 北京海利天梦科技有限公司 | V-shaped empennage unmanned aerial vehicle |
| WO2022121444A1 (en) * | 2020-12-11 | 2022-06-16 | 上海法兰曼航空服务有限公司 | Hybrid light manned aircraft having fixed wings and rotor wings, and aircraft |
-
2019
- 2019-05-06 CN CN201910370346.3A patent/CN110116802A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111137446A (en) * | 2019-12-26 | 2020-05-12 | 中国空气动力研究与发展中心 | Pneumatic layout of multi-rotor vertical take-off and landing unmanned aerial vehicle with stalling function |
| CN112373685A (en) * | 2020-11-23 | 2021-02-19 | 北京海利天梦科技有限公司 | V-shaped empennage unmanned aerial vehicle |
| CN112373685B (en) * | 2020-11-23 | 2023-01-03 | 北京海利天梦科技有限公司 | V-shaped empennage unmanned aerial vehicle |
| WO2022121444A1 (en) * | 2020-12-11 | 2022-06-16 | 上海法兰曼航空服务有限公司 | Hybrid light manned aircraft having fixed wings and rotor wings, and aircraft |
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