CN110498041A - A kind of small-sized Shipborne UAV suitable for the recycling of catapult-assisted take-off lanyard - Google Patents
A kind of small-sized Shipborne UAV suitable for the recycling of catapult-assisted take-off lanyard Download PDFInfo
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- CN110498041A CN110498041A CN201910779364.7A CN201910779364A CN110498041A CN 110498041 A CN110498041 A CN 110498041A CN 201910779364 A CN201910779364 A CN 201910779364A CN 110498041 A CN110498041 A CN 110498041A
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- 238000004064 recycling Methods 0.000 title claims abstract description 65
- 238000013461 design Methods 0.000 claims abstract description 22
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 9
- 239000004917 carbon fiber Substances 0.000 claims description 9
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 9
- 239000000945 filler Substances 0.000 claims description 6
- 239000002131 composite material Substances 0.000 claims description 5
- QTCANKDTWWSCMR-UHFFFAOYSA-N costic aldehyde Natural products C1CCC(=C)C2CC(C(=C)C=O)CCC21C QTCANKDTWWSCMR-UHFFFAOYSA-N 0.000 claims description 5
- ISTFUJWTQAMRGA-UHFFFAOYSA-N iso-beta-costal Natural products C1C(C(=C)C=O)CCC2(C)CCCC(C)=C21 ISTFUJWTQAMRGA-UHFFFAOYSA-N 0.000 claims description 5
- 239000006260 foam Substances 0.000 claims description 4
- 238000004519 manufacturing process Methods 0.000 claims description 4
- 238000000465 moulding Methods 0.000 claims description 3
- 238000003780 insertion Methods 0.000 claims description 2
- 230000037431 insertion Effects 0.000 claims description 2
- 238000003860 storage Methods 0.000 abstract description 8
- 230000008901 benefit Effects 0.000 abstract description 6
- 238000012546 transfer Methods 0.000 abstract description 6
- 238000010586 diagram Methods 0.000 description 11
- 238000011084 recovery Methods 0.000 description 10
- 229910052799 carbon Inorganic materials 0.000 description 8
- 238000012360 testing method Methods 0.000 description 7
- 230000008859 change Effects 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 230000009467 reduction Effects 0.000 description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 241001347978 Major minor Species 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 2
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- 238000005728 strengthening Methods 0.000 description 2
- 230000000007 visual effect Effects 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000005253 cladding Methods 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
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Classifications
-
- 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
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
-
- 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
- B64C1/26—Attaching the wing or tail units or stabilising surfaces
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/68—Arrester hooks
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
-
- 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
- B64D47/00—Equipment not otherwise provided for
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/11—Propulsion using internal combustion piston engines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/13—Propulsion using external fans or propellers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/30—Launching, take-off or landing arrangements for capturing UAVs in flight by ground or sea-based arresting gear, e.g. by a cable or a net
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/70—Launching or landing using catapults, tracks or rails
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U80/00—Transport or storage specially adapted for UAVs
- B64U80/70—Transport or storage specially adapted for UAVs in containers
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Transportation (AREA)
- Catching Or Destruction (AREA)
- Toys (AREA)
Abstract
The invention belongs to aviation aircraft design fields, more particularly to a kind of small-sized Shipborne UAV suitable for the recycling of catapult-assisted take-off lanyard, including head, fuselage, wing, engine, the propeller peace vertical fin wing, head is detachably connected on the front end face of fuselage；Fuselage is the hard shell body structure with strake wing, and lower surface is provided with ejection hook, is equipped with wing on the strake wing of two sides；Wing ending is provided with recovering hook；Engine is mounted on back body face to drive propeller rotational to provide thrust；The flat vertical fin wing is connect by vertical fin shoe pipe with fuselage.Unmanned plane of the present invention has the advantage that structural strength and Path of Force Transfer are excellent, meets the requirement of short distance catapult-assisted take-off and the recycling of lossless lanyard for small drone；Aeroperformance and flight stability is excellent, it can be achieved that the flight of long endurance, wind loading rating is strong, is suitable for marine carrier-borne equal complex scenes operation；Using modularized design, not only it is convenient for assembly or disassembly, but also is conducive to vanning storage and transport.
Description
Technical field
The invention belongs to aviation aircraft design fields, and in particular to it is a kind of suitable for catapult-assisted take-off lanyard recycling
Small-sized Shipborne UAV.
Background technique
Fixed-wing UAV system has the spies such as cruising speed is fast, carrying ability is strong, cruise duration is long, wind loading rating is strong
Point has a wide range of applications space in the fields such as information investigation, frontier defense patrol and emergency management and rescue.Traditional fixed-wing unmanned plane is general
Landing operation is carried out by the way of wheeled sliding race, one section of relatively smooth runway, this landing are needed during landing
Mode limits the application of fixed-wing unmanned plane under many scenes, such as: land complicated landform, islands and reefs, especially deepwater
Under carrier-borne environment.
Currently, the mode of taking off of carrier-borne fixed-wing unmanned plane is mainly catapult-assisted take-off, way of recycling specifically includes that downhill race is hung
Lock, parachuting are salvaged, hit net and lanyard recycling etc. in the air, and majority requires to be equipped with corresponding safe carrier landing system on warship.It can be safe
Easily emit and recycle, is the important indicator for evaluating Shipborne UAV performance, it has also become influence the pass of Shipborne UAV application
One of key point.
It can will be recycled relative to downhill race padlock, aerial ways of recycling, the aerial lanyard way of recycling such as net or parachuting salvaging of hitting
The recycling rope of device is suspended from outside warship, and significant advantage specifically includes that (1) can reduce the occupied deck space of recyclable device, no
Influence the task device arrangement on middle-size and small-size naval vessel；(2) recycling of unmanned plane quick nondestructive can be achieved；(3) can according to recycling route and
Specific operating condition adjusts recovery position to multiple degrees of freedom；(4) safety is higher, can avoid in something unexpected happened on naval vessel
The damage of equipment.
In recent years, it is rapidly developed at home with the Shipborne UAV way of recycling that " hitting net in the air " is representative, such as specially
Benefit number belongs to the unmanned plane of such way of recycling for CN201610025095.1 and CN201310439035.0, all solves existing
There is small drone structural strength not to be able to satisfy the problem of net collision recovery high intensity overload requires, but compared to " lanyard recycling "
This way of recycling, on the one hand, recyclable device needed for " net collision recovery " need to be arranged in deck in ship structure, i.e., in hull space, tool
Standby potential security risk；On the other hand, " net collision recovery " is that unmanned plane integrally flies to recycling network, Wing-Body Configurations leading edge together by
Power, and " lanyard recycling " is then that single recycling rope slides at ending recovering hook along wing side leading edge, passes through the machinery of recovering hook
The self-locking locking to realize unmanned plane.Two kinds of ways of recycling are entirely different, and stress form and Path of Force Transfer are also entirely different, because
This, the corresponding unmanned plane layout of above-mentioned " net collision recovery " mode and organization plan are not particularly suited for the unmanned plane of " lanyard recycling ".
In view of this, considering that the particularity of full landform application, the present invention design a kind of suitable for catapult-assisted take-off and lanyard time
The small-sized Shipborne UAV received, to solve the above problems.
Summary of the invention
In order to solve the above-mentioned problems in the prior art, the present invention provides a kind of suitable for the recycling of catapult-assisted take-off lanyard
Small-sized Shipborne UAV, this unmanned plane use modularized design, both be convenient for assembly or disassembly, be also convenient for store and transport, In
Unmanned aerial vehicle body lower surface is provided with ejection hook, and the costal field in wing ending end face is provided with recycling purchase, in addition to unmanned plane
Fuselage and wing have done creative improvement, meet the requirement of short distance catapult-assisted take-off and the recycling of lossless lanyard.
The technical problem to be solved in the present invention is achieved through the following technical solutions: including head, fuselage, wing, engine,
The propeller peace vertical fin wing；
The unmanned plane is modularized design, and head is detachably connected on the front end face of fuselage, and wing is plugged on fuselage
Left and right sides end face on, engine is mounted on the rear end face of fuselage, dynamic for driving propeller rotational to provide for unmanned plane
Power, the flat vertical fin wing are connect by vertical fin shoe pipe with fuselage；
It is provided with head hatchcover in the middle part of head top-surface camber, the lower surface camber of head is provided with the gondola of concave structure, is used for
Carry executes task device；
Fuselage be the hard shell body structure with strake wing, including fuselage main body, strake wing, fuselage girder, fuselage shoe pipe and
Fuselage skin, strake wing are symmetricly set on fuselage main body two sides, and fuselage girder is arranged in the strake wing of two sides and runs through fuselage master
In the middle part of body, fuselage shoe pipe is symmetricly set on the lower surface of two sides strake wing and integrated with fuselage skin by way of bonding
Change is manufactured, and fuselage skin coats fuselage shoe pipe by setting skirt, and fuselage shoe pipe is connect with vertical fin shoe pipe, fuselage
Lower surface two sides are symmetrically arranged with ejection hook at fuselage shoe pipe, ejection hook by fastener with it is pre-buried in fuselage skin
Part connection, built-in fitting are connected as one with fuselage girder；
Symmetrical wing is installed, wing includes wing girder, wing auxiliary girder, wing cover, wing on the strake wing of two sides
Leading edge, trailing edge, wing ending end face and winglet, wing girder and wing auxiliary girder are arranged in wing wing cover,
Filler is filled at the leading edge of a wing and trailing edge, winglet insertion wing is interior and fixes with wing ending end face, wing
Ending end face is carbon fiber board, and when wing is connect with fuselage, wing girder is inserted into fuselage girder, until wing and strake wing
End face be bonded completely, then pass through fast bolt locking；
Unmanned plane further includes recovering hook, and recycling purchase is arranged in the costal field of wing ending end face and by fastener and machine
Wing ending end face is connected with wing girder；
The flat vertical fin wing includes the left and right vertical fin wing and high horizontalization empennage, is detachably to connect between the horizontal tail wing and the left and right vertical fin wing
It connects, the vertical fin wing includes the vertical fin shoe pipe that lower part is arranged in, and the rudder of setting vertical fin wing rear, horizontal tail wing rear
It is provided with elevator.
Further, each wing further includes aileron and wing flap, and aileron and wing flap are all disposed within the posterior marginal zone and pair of wing
The wing is close to wing ending end face side.
Further, head, fuselage girder, fuselage shoe pipe, fuselage skin, wing cover and wing girder are all made of height
The production of strength carbon fiber composite material.
Further, filler is rigid foam at the leading edge of a wing and trailing edge.
Further, ejection hook is arranged in the inside of fuselage shoe pipe, is 5cm~20cm apart from fuselage shoe pipe.
Further, the wingspan length of wing is 3.6m.
Further, the leading edge sweep of wing is 7 °.
Further, the length of the horizontal tail wing is 0.78m.
Further, the leading edge sweep of the horizontal tail wing is 0 °
Further, the leading edge sweep of the vertical fin wing is 25 °.
Compared with prior art, beneficial effects of the present invention:
1, unmanned plane of the present invention, is provided with ejection hook at left and right sides of fuselage lower surface, ejection hook by fastener with
Built-in fitting connection in fuselage skin, built-in fitting periphery are laid with carbon fibre material and carry out structural strengthening, while built-in fitting and fuselage
Girder is connected as one；In catapult-assisted take-off, the forward thrust launched on hook will all pass to " built-in fitting and fuselage girder "
This global facility, and fuselage skin and fuselage main body are further carried and pass to, to disperse all forward thrusts, protect
Housing construction.Excellent partial structurtes intensity and Path of Force Transfer will so that unmanned plane of the present invention while realizing light weight, it is complete
Structural strength calls of the maximum overload produced by full up foot catapult-assisted take-off for unmanned plane.
2, costal field of the unmanned plane of the present invention in wing ending end face is provided with recovering hook, passes through fastener and wing ending
End face carbon fiber board is connected with wing girder；In lanyard recycling, when recycling rope slides to recovering hook along the leading edge of a wing and realizes lock
After only, greatly export-oriented pulling force can be generated on recovering hook along spanwise, unmanned plane restore to it is static during, will also produce
Raw great moment of flexure and torque, respective loads will pass to wing girder by recovering hook, and wing girder is as direct load knot
On the one hand fractional load is transferred to wing cover and is carried together by itself and wing auxiliary girder etc., on the other hand by moment of flexure by component
Fuselage girder is passed to pulling force, be carried by it and further passes to the components such as fuselage skin and fuselage main body.Excellent office
Portion's structural strength and Path of Force Transfer will be so that unmanned plane of the present invention while realizing light weight, fully meet lanyard recycling and produced
Structural strength calls of the raw maximum overload for unmanned plane.
3, unmanned plane of the present invention uses modularized design, when carrying out storage storage after completing flight operation, it is only necessary to quickly
Disassembly is head, fuselage, the wing peace vertical fin wing totally four modules, the connection of head-fuselage, the grafting of Wing-fuselage, machine
The bindiny mechanisms such as the connection of the flat vertical fin wing of body-are Fast Installation/disassembly type design, are convenient for outdoor operations, can fill after fractionation
Enter in pre-designed aircraft case, convenient for being stored and being transported in the spaces such as naval vessel, car body, realizes space resources most
Optimum utilization.
4, fixed-wing unmanned plane of the present invention uses H-type twin vertical fin, tail motive force formula total arrangement, using the height of autonomous Design
Lift resistance ratio laminar flow airfoil has excellent aerodynamic performance.By more rounds, " total arrangement-pneumatic design-structure is set
The iterative optimization design of the meter-system integration ", it is determined that optimal captain, length, leading edge of a wing angle of sweep, flat vertical fin area
And the parameters such as angle of sweep.By a large amount of flight test, its aeroperformance and control and stability are demonstrated.On the one hand, the machine is in height
There is high lift-drag ratio, and lift efficiency and stalling characteristics are excellent under the conditions of design lift coefficient, has higher maximum fly weight
Amount and index in cruise duration；On the other hand, the configuration of shoulder-wing configuration makes the equipment for excellent horizontal shipping-direction stability, multiple
It can not be by high wind interference in air flow when flight in miscellaneous climatic environment；Finally, the proper fit of full machine aerodynamic center and center of gravity makes this
Equipment excellent longitudinal stability and mobility, can either resist the external disturbances such as prominent wind, and can be in catapult-assisted take-off and lanyard
Recovery stage adjusts itself flight attitude and flight course control in time.
5, unmanned plane head lower surface camber gondola of the present invention is concave structure, in this way when carry such as photoelectric nacelle etc. executes
When task device, it is ensured that recycling when, recycling rope will not touch carry equipment, can effective protection equipment safety, in addition
It executes equipment to be arranged in female structure, has taken into account pneumatic drag reduction characteristic and gondola visual field scope.
Detailed description of the invention
Fig. 1 is unmanned plane general structure schematic diagram of the present invention；
Fig. 2 is unmanned plane Structure explosion diagram of the present invention；
Fig. 3 is unmanned aerial vehicle body structural schematic diagram of the present invention；
Fig. 4 is unmanned plane wing structure schematic diagram of the present invention；
Fig. 5 is unmanned plane wing structure sectional view of the present invention；
Fig. 6 is the flat vertical fin structural schematic diagram of unmanned plane of the present invention；
Fig. 7 is unmanned aerial vehicle ejecting hook of the present invention and body connection structure schematic diagram；
Fig. 8 is unmanned plane recovering hook of the present invention and wing attachment structure schematic diagram；
Fig. 9 is unmanned plane wing of the present invention and fuselage plug connection structural schematic diagram；
Figure 10 is unmanned plane wing of the present invention and fuselage plug connection cross-sectional view；
Figure 11 is unmanned plane storage Carton step schematic diagram of the present invention；
Figure 12 is effect picture after unmanned plane storage vanning of the present invention；
Figure 13 is change curve of the unmanned plane during flying effect-flight airspeed of the present invention with the flight time；
Figure 14 is change curve of the unmanned plane during flying effect-flying height of the present invention with the flight time；
Figure 15 is change curve of the unmanned plane during flying effect-unmanned plane pitch angle of the present invention with the flight time；
Figure 16 is catapult-assisted take-off and lanyard recovery structure schematic diagram under unmanned plane terrestrial environment of the present invention；
Figure 17 is that schematic diagram is recycled in the catapult-assisted take-off and lanyard under unmanned plane marine vessel environment of the present invention.
In figure: 1, head；2, fuselage；3, wing；4, engine；5, propeller；6, flat vertical fin；7, containing box；11, head
Hatchcover；12, gondola；21, fuselage main body；22, strake wing；23, fuselage girder；24, fuselage shoe pipe；25, fuselage skin；26,
Launch hook；27, built-in fitting；28, front end face；29, rear end face；31, port wing；32, starboard wing；33, filler；34, fast bolt；
35, recovering hook；41, hood；62, the vertical fin wing；63, the horizontal tail wing；211, umbrella hatchcover；212, middle hatchcover；213, rear hatchcover；
301, wing girder；302, wing auxiliary girder；303, wing cover；304, the leading edge of a wing；305, trailing edge；306, wing ending
End face；307, winglet；308, aileron；309, wing flap；601, vertical fin shoe pipe；602, rudder；603, vertical fin steering engine；
604, vertical fin covering；631, elevator；632, horizontal tail steering engine；633, horizontal tail rib；634, horizontal tail covering.
Specific embodiment
Reach the technical means and efficacy that predetermined purpose is taken for the present invention is further explained, below in conjunction with attached drawing and reality
Example is applied to a specific embodiment of the invention, structure feature and its effect, detailed description are as follows.
Unmanned plane of the present invention refering to fig. 1~10 shown in, it is a kind of suitable for catapult-assisted take-off lanyard recycling it is small-sized it is carrier-borne nobody
Machine, including the peaceful vertical fin wing 6 of head 1, fuselage 2, wing 3, engine 4, propeller 5.
Unmanned plane of the present invention uses modularized design, and head 1 is detachably connected on the front end face of fuselage 2,3 grafting of wing
On the left and right sides end face of fuselage 2, engine 4 is mounted on the rear end face of fuselage 2, is nothing for driving the rotation of propeller 5
Man-machine offer power, the flat vertical fin wing 6 are connect by vertical fin shoe pipe 601 with fuselage 2.
Specifically, being provided with head hatchcover 11 in the middle part of 1 top-surface camber of head, head hatchcover 11 is used for operation element area,
It is preferably enclosed in 1cm~5cm width range on lid periphery one, hatch frame benefit is carried out using carbon fiber and hard foam
By force, the lower surface camber gondola 12 of head 1 is set as concave structure, executes task device for carry, such as can be used for carry light
The task devices such as electric gondola are designed as concave structure, and there are two advantages: first is that having taken into account pneumatic drag reduction characteristic and gondola visual field
Angular region；Second is that when lanyard recycles, it can be ensured that under any situation, posture, recycling rope will not all touch carry equipment, can be effective
Protect equipment safety.
The fuselage 2 is the hard shell body structure with strake wing, including fuselage main body 21, strake wing 22, fuselage girder 23, machine
Body shoe pipe 24 and fuselage skin 25, strake wing 22 are symmetricly set on 21 two sides of fuselage main body, and fuselage girder 23 is arranged in two sides
In strake wing 22 and through 21 middle part of fuselage main body, fuselage shoe pipe 24 be symmetricly set on the lower surface of two sides strake wing 22 and
Molding is integrated with fuselage skin 25 by way of bonding, fuselage skin 25 coats fuselage shoe pipe by setting skirt
24, cladding fuselage shoe pipe 24 can reduce aerodynamic drag, and the bonding strength of fuselage shoe pipe 24 also can be improved, in addition it can
Realize that the precise positioning of fuselage shoe pipe 24, fuselage shoe pipe 24 are connect with vertical fin shoe pipe 601 while molding, fuselage 2
Lower surface two sides are symmetrically arranged with ejection hook 26 at fuselage shoe pipe 24, and ejection hook 26 passes through fastener and fuselage skin 25
Interior built-in fitting 27 connects, and built-in fitting 27 is connected as one with fuselage girder 23；It, can also be in order to enhance the intensity of junction
The periphery of built-in fitting 27 is laid with carbon fibre material and carries out structural strengthening, and preferred built-in fitting 27 is aluminum material to mitigate whole weight
Amount and do not lose intensity, it is preferred launch hook 26 be arranged in the inside of fuselage shoe pipe 24, be apart from fuselage shoe pipe 24 5cm~
20cm, to guarantee in catapult-assisted take-off, catapult-launching gear avoids fuselage shoe pipe 24.
Symmetrical wing 3 is installed, it is contemplated that the diversification of land application environment and sea climate on two sides strake wing 22
Complicated and changeable, the wing use " shoulder-wing configuration ", to enhance the flight stability of entire unmanned plane comprising port wing of environment
31 and starboard wing 32, for wing 3 using the high lift-drag ratio laminar flow airfoil of autonomous Design, the maximum gauge of aerofoil profile is 10%C, maximum
The corresponding chordwise location of thickness is 34%C, and maximum camber 3.76%C, the corresponding chordwise location of maximum camber is 41%C, after
Edge is with a thickness of 0.3%C, and wherein C is aerofoil profile chord length；
Wherein, the geometric coordinate expression formula of the aerofoil profile upper and lower surfaces is respectively as follows:
Wherein, x indicates the surface abscissa of aerofoil profile, yupIndicate the upper surface ordinate of aerofoil profile；ylowIndicate the following table of aerofoil profile
Face ordinate；AupRepresent the expression formula coefficient of aerofoil profile upper surface geometric coordinate；AlowRepresent the expression of aerofoil profile lower surface geometric coordinate
Formula coefficient；
AupAnd AlowValue be shown in Table 1:
The expression formula coefficient of 1 airfoil geometry coordinate of table
Wing 3 using " major-minor girder structure " design, including wing girder 301, wing auxiliary girder 302, wing cover 303,
The setting of the leading edge of a wing 304, trailing edge 305, wing ending end face 306 and winglet 307, winglet 307 reduces machine
The induced drag of the wing 3 improves the lifting resistance characteristic of unmanned plane, increases cruise duration, and wing girder 301 and wing auxiliary girder 302 are arranged
In wing wing cover 303, wing girder 301 and wing auxiliary girder 302 are closely connected by way of bonding with wing cover 303
It is connected in one, to enhance the bearing strength of wing 3, filler 33, filling are filled at the leading edge of a wing 304 and trailing edge 305
Object 33 is preferably light weight and the rigid foam with excellent physical impact performance, and winglet 307 is inserted into wing 3 simultaneously
Fixed with wing ending end face 306, wing ending end face 306 is preferably carbon fiber board, when wing 3 is connect with fuselage 2, wing
Girder 301 be inserted into fuselage girder 23 in, until wing 3 be bonded completely with the end face of strake wing 22, then pass through fast 34 locking of bolt,
On the one hand the inserting mode realizes the quick connection of wing 3 and fuselage 2, on the other hand can be efficiently and reliably by wing girder
The load transmissions such as 301 moment of flexure, the pulling force carried are carried by fuselage girder 23 to fuselage girder 23 and pass to fuselage skin
The components such as 25 and fuselage main body frame meet bonding strength requirement while control structure weight.
The unmanned plane further includes recovering hook 35, and recycling purchase 35 is arranged in the costal field of wing ending end face 306 and passes through
Fastener is connect with wing ending end face 306 and wing girder 301, and lower surface camber and 3 wing of wing are slightly bent on preferred recovering hook 35
The shape in face is consistent, to guarantee that recycling rope will not be stuck in localized positions.
By above-mentioned setting, when unmanned plane is in catapult-assisted take-off: the forward thrust on ejection hook 26 will all pass to " pre-
Embedded part 27 and fuselage girder 23 " this global facility, and further carry and pass to fuselage skin 25, excellent partial structurtes
Intensity and Path of Force Transfer will be so that unmanned plane of the present invention while realizing light weight, fully meet maximum produced by catapult-assisted take-off
Overload the Structural strength calls for unmanned plane；When the recycling of unmanned plane lanyard: recycling rope slides to recovering hook along the leading edge of a wing 304
35 and after realizing locking, greatly export-oriented pulling force can be generated in recycling 35 along spanwise, be restored in unmanned plane to static mistake
Cheng Zhong, will also generate great moment of flexure and torque, and respective loads will pass to wing girder 301, wing master by recovering hook 35
Beam 301 is used as direct load-carrying construction part, fractional load is on the one hand transferred to wing cover 303 and by itself and wing auxiliary girder 302
Deng common carrying, moment of flexure and pulling force are on the other hand passed into fuselage girder 23, be carried by it and further pass to fuselage illiteracy
The components such as skin 25 and fuselage main body frame, to disperse stress, to meet maximum overload produced by lanyard recycles for unmanned plane
Structural strength calls.
Preferably, each wing 3 further includes aileron 308 and wing flap 309, and aileron 308 and wing flap 309 are all disposed within wing 3
Posterior marginal zone and aileron 308 close to 306 side of wing ending end face, wing 3 also installs additional while configuring conventional aileron 308
Wing flap 309 can be dropped when the big down to her mark flight operation of unmanned plane to improve the lift of catapult-assisted take-off and lanyard recovery stage
Low velocity requirement reduces maximum overload when catapult-assisted take-off and lanyard recycling, is conducive to extend the service life of unmanned plane.
Preferably, the head 1, fuselage girder 23, fuselage shoe pipe 24, fuselage skin 25, wing cover 303 and wing
Girder 301 is all made of the production of high-strength carbon fiber composite material.
In order to avoid propeller 5 and lanyard from winding when guaranteeing that unmanned plane during flying is stablized, and recycling, unmanned plane of the present invention is used
The design of H-type twin vertical fin, the flat vertical fin wing 6 include the left and right vertical fin wing 62 and high horizontalization empennage 63,62 peace of the left and right vertical fin wing
Empennage 63 is all made of " major-minor girder structure " design similar with wing 3, is removable between the horizontal tail wing 63 and the left and right vertical fin wing 62
Connection is unloaded, the vertical fin wing 62 includes the vertical fin shoe pipe 601 that lower part is arranged in, and the rudder 602 of 62 rear of the vertical fin wing is arranged,
63 rear of the horizontal tail wing is provided with elevator 631, and 63 upper surface two sides of the horizontal tail wing also set up horizontal tail rib 633, the left and right vertical fin wing 62
On the peaceful empennage 63 of vertical fin covering 604 on horizontal tail covering 604 also made of high-strength carbon fiber composite material, in left and right
The peaceful tail actuator 632 of vertical fin steering engine 603 is additionally provided on the peaceful empennage 63 of the vertical fin wing 62, the steering engine is all made of ultra-thin steering engine,
The confined space of empennage can be made full use of to realize complete immersion installation, reduce empennage while abundant operating torque is provided
Partial resistance.
Unmanned aerial vehicle body 2 of the present invention uses the hard shell body structure with strake wing, has the advantage that one, improves nobody
The aerodynamic characteristic of machine, excellent blended wing-body shape can effectively realize lift-rising drag reduction, and then increase cruise duration；Two, it hangs
It restricts recovery stage, as long as unmanned plane touches recycling rope within the scope of the span, subsequent time recycling rope will be along before smooth
Edge slides to the recovering hook 35 of the wing slightly, so that locking completes recycling, using the fuselage appearance with strake wing, can make recycling rope more
It is easy, more rapidly slides at recovering hook 35；Three, length and thickness of the strake wing formula shape at wing root are larger, can
The structural strength for improving wing root, when catapult-assisted take-off and lanyard recycle, it can be ensured that unmanned plane bear the impact compared with big overload without
There is structural damage problem；Four, hard shell body structure productivity easy to process and intensity are high, in addition the arrangement of internal unit, make
With, it is easy to maintain.
Unmanned plane of the present invention offers umbrella hatchcover 211, middle hatchcover 212 and rear hatchcover 213 in 2 upper surface of fuselage, can be used for
It arranges umbrella cabin, fly the Aerial Electronic Equipments such as control, fuel tank and figure biography, the front end face 28 and rear end face 29 of fuselage 2 are provided with high strength carbon
Bulkhead is reinforced in fibrous composite production, described to start to guarantee there is enough intensity when connecting with head 1 and engine 4
Machine 4 is connected on rear end face 29 by hood 41, plays the role of rectifying drag reduction, engine 4 is mainly opposed using twin-tub
Formula petrol engine, to drive the rotation of propeller 5 to provide thrust, this tail pushing-type power arrangement form is conducive to unmanned plane extension
Rope recycling can avoid recycling rope and damage to propeller 5；Thrust axis generally within fuselage axis line position at, approximation is worn
Cross full machine center of gravity；The engine 4 can also carry " stator-rotator formula " generator, and wherein stator is pacified by stator mounting bracket
On engine crankcase, rotor is directly driven by engine crankshaft, to provide the long endurance of airborne whole Aerial Electronic Equipments
Power supply (multichannel different voltages) supply.
Unmanned plane of the present invention uses modularized design, when carrying out storage storage after completing flight operation, removes machine respectively
Head, wing, flat vertical fin can be put into the containing box 7 of default formulation by Figure 10 step, and it is as shown in figure 11 to be put into rear effect, made
Used time takes out installation in reverse order, convenient for being stored and being transported in the small spaces such as naval vessel, car body, realizes space
The optimum use of resource.
By a large amount of design simulation and flight test, the present invention designs best unmanned plane, and parameter is as follows: maximum
Take-off weight is 30kg, and the leading edge sweep of cruising speed 100km/h, captain 2.1m, wingspan length 3.6m, wing are
7 °, the length of horizontal tail is 0.78m, and the leading edge sweep of horizontal tail is 0 °, and the leading edge sweep of vertical fin is 25 °.
Specific example
Real-time mode of the invention is specifically described below by three examples:
Example one: prototype flight test
Inventor has carried out a large amount of flight test for the small drone, and landing mode is respectively pneumatic catapult-assisted take-off
It stops and recycling with vertical rope.Figure 13~15 be the small drone practical flight effect, respectively flight airspeed, flying height and
For unmanned plane pitch angle with the variation relation of flight time, flight test time is 3 hours.It can be seen from the figure that unmanned plane exists
Catapult-assisted take-off and lanyard recovery stage performance are stablized, and during entire flight test, which can maintain cruising altitude (height above sea level
750m) and cruising speed (28m/s) stabilized flight, and pitch angle is also always in 0 ° of neighbouring fuctuation within a narrow range, has excellent flight
Stability.By flight test, this example shows that unmanned plane of the present invention has excellent pneumatic lifting resistance characteristic and pneumatic trim special
Property, and engineering exploitativeness is preferable, is a small drone for being highly suitable for catapult-assisted take-off and lanyard recycling.
Example two: transmitting and recycling under the vehicle environment of land
Since land operation has the characteristics that the complicated multiplicity of environment and task mobility strong, answered particularly with border patrol etc.
Generally require long endurance flight in 10 hours or more with scene, and it is traditional it is sliding run landing fixed-wing unmanned plane to site requirements compared with
Height, is restricted that factor is more, and middle-size and small-size more rotors in the market and vertical take-off and landing drone then only have cruise duration it is 1~5 small
When, also it is unable to satisfy mission requirements.Therefore, it is necessary to use using catapult-assisted take-off and lanyard to recycle as the middle-size and small-size nothing in a manner of landing
It is man-machine, it is equipped with corresponding ejection/recyclable device and fulfils assignment task.Figure 16 is certain land of practical application unmanned plane of the present invention
Launch recycling institutional operation vehicle, the unmanned plane can complete deployment assembly within the scope of compartment, catapult-assisted take-off, lanyard recycling, receive
Receive vanning etc. subjects, it was demonstrated that unmanned plane of the present invention sufficiently meets the use demand under continental rise environment.
Example three: transmitting and recycling under marine carrier-borne environment
Unmanned plane has a huge application demand under marine environment, and the landing site that naval vessel and island are capable of providing compared with
Small, space is very limited；In addition, the job tasks such as sea fishery detection, the patrol of seashore boundary line need to be equipped with pocket
Long endurance unmanned aircraft.At this point, then needing to come real using the small drone for integrating catapult-assisted take-off and lanyard recycling function
Unmanned plane during flying operation on existing naval vessel mobile platform or island platform.Figure 17 show the offshore vessel using unmanned plane of the present invention
Oceangoing ship catapult-assisted take-off and lanyard recycle operation process, both can be efficiently since unmanned plane of the present invention uses modularized design
Cabinet storage is carried out using the confined space on ship, can also easily carry out deployment assembly；Wing and fuselage are using innovation simultaneously
Property design organization plan and Path of Force Transfer, on the one hand can bear maximum ejection acceleration guarantee body and internal unit not by
Damage, impact acceleration when on the other hand can be recycled with efficient absorption and transmitting lanyard, realizes recycle without damage.Therefore, of the invention
A kind of small drone of catapult-assisted take-off and lanyard recycling, suitable for the transmitting and recycling under marine carrier-borne environment.
The above content is a further detailed description of the present invention in conjunction with specific preferred embodiments, and it cannot be said that
Specific implementation of the invention is only limited to these instructions.For those of ordinary skill in the art to which the present invention belongs, In
Under the premise of not departing from present inventive concept, a number of simple deductions or replacements can also be made, all shall be regarded as belonging to of the invention
Protection scope.
Claims (10)
1. a kind of small-sized Shipborne UAV suitable for the recycling of catapult-assisted take-off lanyard, it is characterised in that: including head (1), fuselage
(2), the peaceful vertical fin wing (6) of wing (3), engine (4), propeller (5)；
The unmanned plane is modularized design, and the head (1) is detachably connected on the front end face of fuselage (2), the wing
(3) it is plugged on the left and right sides end face of fuselage (2), the engine (4) is mounted on the rear end face of fuselage (2), for driving
Dynamic propeller (5) rotation provides power for unmanned plane, and the flat vertical fin wing (6) is connected by vertical fin shoe pipe (601) and fuselage (2)
It connects；
It is provided with head hatchcover (11) in the middle part of head (1) top-surface camber, the lower surface camber of head (1) is provided with concave structure
Gondola (12) executes task device for carry；
The fuselage (2) is the hard shell body structure with strake wing, including fuselage main body (21), strake wing (22), fuselage girder
(23), fuselage shoe pipe (24) and fuselage skin (25), the strake wing (22) are symmetricly set on fuselage main body (21) two sides, institute
Fuselage girder (23) setting is stated in two sides strake wing (22) and in the middle part of fuselage main body (21), the fuselage shoe pipe
(24) it is symmetricly set on the lower surface of two sides strake wing (22) and is integrated by way of bonding with fuselage skin (25)
Molding, the fuselage skin (25) coat fuselage shoe pipe (24) by setting skirt, the fuselage shoe pipe (24) and vertical fin
Shoe pipe (601) connection, fuselage (2) the lower surface two sides are symmetrically arranged with ejection hook at fuselage shoe pipe (24)
(26), ejection hook (26) is connect by fastener with the built-in fitting (27) in fuselage skin (25), the built-in fitting (27)
It is connected as one with fuselage girder (23)；
It is equipped on strake wing described in two sides (22) symmetrical wing (3), the wing (3) includes wing girder (301), wing
Auxiliary girder (302), wing cover (303), the leading edge of a wing (304), trailing edge (305), wing ending end face (306) and wingtip are small
The wing (307), the wing girder (301) and wing auxiliary girder (302) setting are in wing wing cover (303), before the wing
Filler (33) are filled at edge (304) and trailing edge (305), the winglet (307) is inserted into wing (3) and and machine
Wing ending end face (306) is fixed, and wing ending end face (306) is carbon fiber board, when the wing (3) and fuselage (2) connect
When connecing, in wing girder (301) insertion fuselage girder (23), until wing (3) and the end face of strake wing (22) are pasted completely
It closes, then passes through fast bolt (34) locking；
The unmanned plane further includes recovering hook (35), it is described recycling purchase (35) setting wing ending end face (306) costal field,
And it is connect by fastener with wing ending end face (306) and wing girder (301)；
The flat vertical fin wing (6) includes the left and right vertical fin wing (62) and high horizontalization empennage (63), and the horizontal tail wing (63) and left and right are hung down
To be detachably connected between empennage (62), the vertical fin wing (62) includes the vertical fin shoe pipe (601) that lower part is arranged in, Yi Jishe
The rudder (602) of the vertical fin wing (62) rear is set, the horizontal tail wing (63) rear is provided with elevator (631).
2. a kind of small-sized Shipborne UAV suitable for the recycling of catapult-assisted take-off lanyard as described in claim 1, it is characterised in that:
Each wing (3) further includes aileron (308) and wing flap (309), and the aileron (308) and wing flap (309) are all disposed within machine
The posterior marginal zone and the aileron (308) of the wing (3) are close to wing ending end face (306) side.
3. a kind of small-sized Shipborne UAV suitable for the recycling of catapult-assisted take-off lanyard as described in claim 1, it is characterised in that:
The head (1), fuselage girder (23), fuselage shoe pipe (24), fuselage skin (25), wing cover (303) and wing girder
(301) it is all made of the production of high-strength carbon fiber composite material.
4. a kind of small-sized Shipborne UAV suitable for the recycling of catapult-assisted take-off lanyard as described in claim 1, it is characterised in that:
Filler (33) is rigid foam at the leading edge of a wing (304) and trailing edge (305).
5. a kind of small-sized Shipborne UAV suitable for the recycling of catapult-assisted take-off lanyard as described in claim 1, it is characterised in that:
Ejection hook (26) setting is 5cm~20cm in the inside of fuselage shoe pipe (24), apart from fuselage shoe pipe (24).
6. a kind of small-sized Shipborne UAV suitable for the recycling of catapult-assisted take-off lanyard as described in claim 1, it is characterised in that:
The wingspan length of the wing (3) is 3.6m.
7. a kind of small-sized Shipborne UAV suitable for the recycling of catapult-assisted take-off lanyard as described in claim 1, it is characterised in that:
The leading edge sweep of the wing (3) is 7 °.
8. a kind of small-sized Shipborne UAV suitable for the recycling of catapult-assisted take-off lanyard as described in claim 1, it is characterised in that:
The length of the horizontal tail wing (63) is 0.78m.
9. a kind of small-sized Shipborne UAV suitable for the recycling of catapult-assisted take-off lanyard as described in claim 1, it is characterised in that:
The leading edge sweep of the horizontal tail wing (63) is 0 °.
10. a kind of small-sized Shipborne UAV suitable for the recycling of catapult-assisted take-off lanyard as described in claim 1, feature exist
In: the leading edge sweep of the vertical fin wing (62) is 25 °.
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Effective date of registration: 20240618 Address after: Room 601, Building 5, China Electronics Xi'an Industrial Park, No. 1288 Caotan 10th Road, Xi'an Economic and Technological Development Zone, Shaanxi Province, 710018 Patentee after: SATPRO M&C TECH Co.,Ltd. Country or region after: China Patentee after: Xi'an Exploration Eagle Aviation Technology Co.,Ltd. Address before: 710069 Xionghua Science and Technology Industrial Park A-410, Jinye 1st Road, Yanta District, Xi'an, Shaanxi Patentee before: Xi'an Exploration Eagle Aviation Technology Co.,Ltd. Country or region before: China |