CN109987217A - Folding wings unmanned plane and its launching technique - Google Patents
Folding wings unmanned plane and its launching technique Download PDFInfo
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- CN109987217A CN109987217A CN201910355380.3A CN201910355380A CN109987217A CN 109987217 A CN109987217 A CN 109987217A CN 201910355380 A CN201910355380 A CN 201910355380A CN 109987217 A CN109987217 A CN 109987217A
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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
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
- B64F1/06—Ground or aircraft-carrier-deck installations for launching aircraft using catapults
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Abstract
The present invention relates to a kind of folding wings unmanned planes, including fuselage, the preceding straight wing, the rear straight wing, the folding vertical fin for being installed on afterbody and the foldable propeller component for being installed on back body, one in the preceding straight wing and the rear straight wing is installed on the top surface of the fuselage, another is installed on the bottom surface of the fuselage, and can be folded centered on the fuselage.Folding wings unmanned plane provided by the invention, during expansion, the preceding straight wing and the rear straight wing can be unfolded centered on fuselage in symmetrical in the left and right sides, so that the preceding straight wing and the rear straight wing during expansion in two sides to the equilibrant force indifference of unmanned aerial vehicle body, fuselage rotation is not easily led to, to improve unmanned plane stability, and then improve the launching success rate of unmanned plane.
Description
Technical field
The invention belongs to air vehicle technique fields, and in particular to a kind of folding wings unmanned plane and its launching technique.
Background technique
With the development of science and technology, folding wings unmanned plane because its can fast folding so that can effectively reduce its transport,
The advantages such as large space are occupied when transmitting, dispensing, are rapidly developed.
Traditional folding wings unmanned plane generally uses X-type aerofoil blading, and the efficient loading space of X-type wing unmanned plane is smaller,
Therefore, people develop a kind of Z-shaped folding unmanned plane, special referring to the invention disclosed application No. is 201811601135.8
Benefit application, although this application overcomes the lesser disadvantage in efficient loading space of traditional folding wings unmanned plane, but still deposit
In technological deficiency:
During expansion, it is unfolded centered on fuselage in asymmetric at left and right sides of zigzag folding wing, to make
Zigzag folding wing is variant in equilibrant force of the two sides to unmanned aerial vehicle body during expansion, easily lead to fuselage rotation, from
And the stability of unmanned plane is had an impact, and then influence the launching success rate of unmanned plane.
Summary of the invention
For above-mentioned problems of the prior art, the present invention provides a kind of folding wings for solving above-mentioned technical problem
Unmanned plane.
In order to achieve the above-mentioned object of the invention, technical solution provided by the invention is as follows:
A kind of folding wings unmanned plane including fuselage, the preceding straight wing, the rear straight wing, is installed on the folding of afterbody
Vertical fin and the foldable propeller component for being installed on back body, the preceding straight wing and it is described after a peace in the straight wing
Top surface loaded on the fuselage, another is installed on the bottom surface of the fuselage, and can be folded centered on the fuselage.
Further, the preceding straight wing is installed on the top surface of the fuselage, left front straight on the left of fuselage including being located at
The wing and the straight wing before the right side on the right side of the fuselage, it is described it is right before the straight wing and the left front straight wing can be with the fuselage
Centered on fold back；The straight wing is installed on the bottom surface of the fuselage after described, including being located at the left back straight wing on the left of fuselage
With the straight wing behind the right side that is located on the right side of the fuselage, it is described it is right after the straight wing with the left back straight wing can be with the fuselage
Center collapsed forward；The fuselage is cylindrical-shaped structure, and top cuts flat with to be formed for placing the folded left front straight wing and the right side
The preceding straight wing, bottom cut flat with to be formed for placing the folded left back straight wing and the straight wing behind the right side.
Further, the top surface of the fuselage is longitudinally provided with front wing shaft；Front left is fixed on the left front straight wing
Torsional spring slot, it is described it is right before be fixed with front right torsional spring slot on the straight wing, the front left torsional spring slot and the front right torsional spring slot make-up are set
The space to be formed and accommodate preceding torsional spring is set, the preceding torsional spring is installed in the front left torsional spring slot and front right torsional spring slot of make-up, and is installed
In front wing shaft, it is horizontally arranged in the front wing shaft respectively and before the front left torsional spring slot and the cooperation of front right torsional spring slot
Wing bolt, the side in the front wing shaft close to the front fuselage are respectively fixed with guide part, on two guide parts
It is horizontally arranged with pressure spring, the pressure spring is not connected with one end of guide part connection with the corresponding front wing bolt；
The bottom surface of the fuselage is longitudinally provided with rear wing shaft；Rear left torsional spring slot, institute are fixed on the left back straight wing
State and be fixed with rear right torsional spring slot behind the right side on the straight wing, the rear left torsional spring slot and it is described after right torsional spring slot make-up be arranged to form receiving
The space of torsional spring afterwards, the rear torsional spring is installed in the rear left torsional spring slot and rear right torsional spring slot of make-up, and is mounted on rear wing shaft
On.
Further, the preceding resilient cushion of the kinetic energy after opening for the straight span before absorbing, institute are also equipped on the fuselage
State the preceding shaft-cup for being equipped at the top of front wing shaft and falling off during folding and unfolding for the straight wing before preventing；The rear wing
The bottom of shaft is equipped with the rear shaft-cup for preventing the rear straight wing from falling off during folding and unfolding.
Further, it is provided with aileron on the rear straight wing, the aileron includes port aileron and starboard aileron；The right pair
The wing is connected with the straight wing behind the right side by hinge paper, and starboard aileron can turn down up and down, and the first aileron company is fixed on the starboard aileron
Fitting, it is described it is right after be fixed with right standard rudder machine on the straight wing, the steering engine arm of the right standard rudder machine and the first aileron connector are hinged；
The port aileron is connected with the left back straight wing by hinge paper, and port aileron can turn down up and down, and is fixed on the port aileron
Two aileron connectors, left rudder machine is fixed on the left back straight wing, and the steering engine arm of the left rudder machine and second aileron connect
Fitting is hinged.
Further, the vertical fin includes left vertical fin and right vertical fin；The left vertical fin passes through left vertical fin axis and the fuselage
Connection, link position are located at the left side of the fuselage, and left vertical fin cover, installation in the left vertical fin cover are cased on the left vertical fin axis
There is the left vertical fin torsional spring being unfolded upwards for left vertical fin；The right vertical fin is connect by right vertical fin axis with the fuselage, connection position
Setting in the right side of the fuselage, it is cased with right vertical fin cover on the right vertical fin axis, is equipped in the right vertical fin cover and hangs down for right
The right vertical fin torsional spring that tail is unfolded upwards；Vertical fin positioning card, the folding wings are provided between the left vertical fin and the right vertical fin
Unmanned plane in a fully folded condition, the vertical fin positioning card be located at the top of vertical fin and be located at the preceding straight wing lower section and
It is contacted with the preceding straight wing.
Further, the tail end of the fuselage is equipped with tailgate, and motor is fixed on the tailgate, is fixed on the motor
Have a foldable propeller component, the blade of the foldable module can collapsed forward be bonded with the afterbody；The tail
Microswitch and back damping pad are fixed on plate, the microswitch is pierced by the back damping pad and exposes outside the back damping pad,
Microswitch can be triggered when predetermined position is reached in the straight span after described controls the motor operating.
It further, further include feeder line foldable assembly, the fuselage bottom place of cutting flat with is provided with rectangle hole, for hiding
Feeder line foldable assembly；The feeder line foldable assembly includes feeder line folding stand, feeder line fixing seat and antenna, and the fixing seat is fixed on
The bottom surface of the fuselage, the feeder line folding stand is hinged by pin shaft and the feeder line folding stand, and is equipped on the pin shaft
Feeder line torsional spring for folding stand drops down；Feeder line angle coupling is installed, the antenna is fixed on the feeder line folding stand
In on the feeder line angle coupling；In a fully folded condition, the antenna is located at described rear straight the folding wings unmanned plane
The top of the wing and with it is described after the straight wing contact.
Folding wings unmanned plane provided by the invention, during expansion, the preceding straight wing and the rear straight wing can be in left and right
Two sides centered on fuselage in symmetrical expansion so that the preceding straight wing and the rear straight wing during expansion in two sides to nothing
The equilibrant force indifference of man-machine fuselage does not easily lead to fuselage rotation, to improve unmanned plane stability, and then improves nobody
The launching success rate of machine.
The present invention also provides a kind of launching techniques of above-mentioned folding wings unmanned plane, comprising the following steps:
Step 1, folding wings unmanned plane is in completely folded state, is placed in corresponding launching tube；
Wherein, folding wings unmanned plane refers in completely folded state:
For the preceding straight wing, it is folded to after straight flapwise before the left front straight wing and the right side and is overlapped with fuselage, be located at fuselage roof
Cut flat with position；
For the rear straight wing, it is folded to before straight flapwise after the left back straight wing and the right side and is overlapped with fuselage, be located at fuselage bottom
Cut flat with position；
For vertical fin, left vertical fin and right vertical fin are folded down, and are overlapped with the fuselage, and left vertical fin is located at the left side of fuselage,
Right vertical fin is located at the right side of fuselage, and vertical fin is pushed down by the preceding straight wing；
For feeder line foldable assembly, feeder line folding stand drives antenna to be folded up to fuselage rectangle hole, by rear straight
The wing is pushed down；
After folding wings unmanned plane is in completely folded state, radial full-size is no more than the internal diameter of launching tube, length
No more than the length of launching tube, can be accommodated in launching tube completely；
Step 2, launching tube installation is fixed；
Step 3, starting launching tube, folding wings unmanned plane is popped up from launching tube, and expansion is deformed up to being fully deployed rapidly,
Complete emission process:
Specific expansion deformation process are as follows: (1) the preceding straight wing and the rear straight wing are first unfolded simultaneously:
The left front straight wing and it is right before be expanded to before straight flapwise vertical with fuselage, be located at fuselage two sides；The left back straight wing and
Be expanded to after straight flapwise behind the right side it is vertical with fuselage, be located at fuselage two sides；
(2) vertical fin and the expansion of feeder line foldable assembly:
Left vertical fin and right vertical fin when the preceding straight span, which is reached, to apply pressure to vertical fin positioning card upwards expansion until
Perpendicular to fuselage, during vertical fin is unfolded, vertical fin positioning card, which is got rid of, falls off；
Feeder line foldable assembly drops down when the rear straight span, which is reached, to stop it, until perpendicular to fuselage.
Unmanned plane is emitted by using this method, during expansion, the preceding straight wing and the rear straight wing can be in left and right
Two sides using fuselage as center journey symmetrical expression be unfolded so that the preceding straight wing and the rear straight wing during expansion in two sides to nothing
The equilibrant force indifference of man-machine fuselage does not easily lead to fuselage rotation, to improve unmanned plane stability, and then improves nobody
The launching success rate of machine.In addition, the preceding straight wing, the rear straight wing, vertical fin and feeder line foldable assembly can be opened in order, Neng Goubao
Demonstrate,prove smooth opening between various components.
Detailed description of the invention
Fig. 1 shows a kind of unfolded state structural schematic diagram of folding wings unmanned plane；
Fig. 2 shows the mounting structure schematic diagrams of the preceding straight wing；
Fig. 3 shows the mounting structure schematic diagram of the rear straight wing and foldable propeller component；
Fig. 4 shows the mounting structure schematic diagram of aileron；
Fig. 5 shows the mounting structure schematic diagram of vertical fin；
Fig. 6 shows the position limiting structure schematic diagram of vertical fin；
Fig. 7 shows the mounting structure schematic diagram of feeder assembly；
Fig. 8 shows the structural schematic diagram of feeder assembly；
Fig. 9 shows a kind of folded state structural schematic diagram of folding wings unmanned plane；
Figure 10 shows a kind of emission process schematic diagram of folding wings unmanned plane；
In figure, fuselage 01, it is right before the straight wing 02, the left front straight wing 03, it is right after the straight wing 04, starboard aileron 05 is left back straight
The wing 06, port aileron 07, right vertical fin 08, left vertical fin 09, the output end of 9-1- push-pull electromagnet, blade 10, front wing shaft 11, pressure
Spring 12, front wing bolt 13, screw 14, front right torsional spring slot 15, preceding torsional spring 16, front left torsional spring slot 17, preceding resilient cushion 18, shaft-cup 19,
Rear wing shaft 20, rear left torsional spring slot 21, rear right torsional spring slot 22, rear torsional spring 23, rear shaft cover board 24, microswitch 25, rear damping
Pad 26, tailgate 27, fuselage tail frame 28, the first aileron connector 29, cross head screw 30, the steering engine arm 31 of right standard rudder machine, right standard rudder
Machine 32, left rudder rack 33, right standard rudder rack 34, motor 35, paddle shaft 36, lock ring 37, paddle folder 38, spinner 39, screw rod 40, locknut 41,
Left vertical fin axis 42, left vertical fin torsional spring 43, left vertical fin cover 44, right vertical fin cover 45, right vertical fin torsional spring 46, crossed countersunk head screw 47 are interior
Hexagonal cylindrical head screw 48, feeder line fixing seat 49, feeder line folding stand 50, pin shaft 51, feeder line torsional spring 52, antenna 53, feeder line right angle
Connector 54, vertical fin positioning card 55.
Specific embodiment
In order to make the objectives, technical solutions, and advantages of the present invention clearer, with reference to the accompanying drawing and specific implementation
The present invention will be further described for example.It should be appreciated that described herein, specific examples are only used to explain the present invention, and does not have to
It is of the invention in limiting.Based on the embodiments of the present invention, those of ordinary skill in the art are not making creative work premise
Under every other embodiment obtained, shall fall within the protection scope of the present invention.
Embodiment 1, referring to Fig. 1, this application provides a kind of folding wings unmanned plane, including it is fuselage 01, the preceding straight wing, rear flat
The straight wing is installed on the folding vertical fin of afterbody and is installed on the foldable propeller component of back body, before described
One in the straight wing and the rear straight wing is installed on the top surface of the fuselage, another is installed on the bottom surface of the fuselage,
And can be folded centered on the fuselage, specifically, the preceding straight wing is installed on the top surface of the fuselage, including it is located at
The left front straight wing 03 on the left of fuselage and the straight wing 02 before the right side on the right side of the fuselage, it is described it is right before the straight wing and the left side
The preceding straight wing can be folded back centered on the fuselage；The straight wing is installed on the bottom surface of the fuselage, including position after described
The left back straight wing 06 on the left of fuselage and the straight wing 04 behind the right side on the right side of the fuselage, it is described it is right after the straight wing with it is described
The left back straight wing can be using the fuselage as center collapsed forward；The fuselage is cylindrical-shaped structure, and top cuts flat with to be formed and be used for
The folded left front straight wing and the straight wing before the right side are placed, bottom cuts flat with to be formed for placing the folded left back straight wing and the right side
The straight wing afterwards.
As a kind of specific preceding straight wingfold structure, referring to fig. 2, the top surface of the fuselage is longitudinally provided with front wing and turns
Axis 11；It is fixed with front left torsional spring slot 17 on the left front straight wing, is fixed with front right torsional spring slot 15, institute on the straight wing before the right side
State front left torsional spring slot and the front right torsional spring slot make-up be arranged to be formed accommodate before torsional spring space, the preceding torsional spring 16 is installed on pair
It in the front left torsional spring slot and front right torsional spring slot of button, and is mounted in front wing shaft 11, generally covers in front wing shaft, the front wing
The front wing bolt cooperated respectively with the front left torsional spring slot and front right torsional spring slot, the front wing bolt are horizontally arranged in shaft
The inherent side close to the front fuselage is respectively fixed with guide part, and it is preferable to use screws 14 for guide part, before being generally fixed to
In wing shaft, pressure spring 12 is horizontally arranged on two guide parts, one end that the pressure spring is not connect with the guide part with
The corresponding front wing bolt connection.Further, it is also equipped on the fuselage dynamic after being opened for the straight span before absorbing
Can preceding resilient cushion 18, be equipped at the top of the front wing shaft and fall off during folding and unfolding for the straight wing before preventing
Preceding shaft-cup 19.
When the preceding straight wingfold structure is installed, preceding resilient cushion 18 is installed on fuselage with screw, it is preceding flat for absorbing
Kinetic energy after directly the span is opened；Before front right torsional spring slot 15 is cemented in the right side with glue on the straight wing 02, front left torsional spring slot 17 is used into gluing
Gu preceding torsional spring 16 is installed in the left and right preceding straight wing torsional spring slot of make-up on the left front straight wing 03, then pre-tightens and be installed to
In front wing shaft 11；The front wing cooperated with the front left torsional spring slot and front right torsional spring slot respectively is horizontally arranged in front wing shaft to insert
Mounting groove is sold, the front wing bolt and pressure spring are installed in front wing bolt mounting groove, and pressure spring is fixed by screw,
Guiding and limit, two independent front wing bolts 13 are installed on 11 the inside of front wing shaft；Two independent front wing bolts 13 lean on
The thrust of two independent pressure springs 12 is moved forward and backward, and guarantees the motion profile of pressure spring with the screw 14 of two M2.5；By front axle
Lid 19 is screwed on preceding resilient cushion 18 and front wing shaft 11, prevents front wing from falling off during folding and unfolding.
In the preceding straight wingfold structure structure: preceding straight wingfold process: pressure spring 12 compresses, and two front wing bolts 13 contract
Enter in front wing shaft 11, preceding 16 stress of torsional spring pre-tightens, it is right before the straight wing 02 and the left front straight wing 03 to fuselage 01 with front wing shaft
11 fold for axis, coincide with fuselage 01, this state needs to be bundled with nylon adherent buckle during transportation, and pressure spring compression can
It is stirred using external tool such as pin, pole etc., to head side in general pole insertion 13 hole of front wing bolt with 3mm
To firmly, the straight wing before then folding, the left front straight wing is usually to fold by external force when folding with straight flapwise fuselage before the right side
's.
Preceding straight span open procedure: pressure spring 12 is unfolded, it is right before the straight wing 02 and the left front straight wing 03 to fuselage 01 with rear wing
Shaft 20 is axis expansion until in alignment and perpendicular to fuselage 01, and two front wing bolts 13 are inserted into front right torsional spring slot 15 respectively
In the notch of front left torsional spring slot 17, wing is fixed, prevents wing in flight course from conjugating, leads to the failure hair of flight
It is raw.
As a kind of specific preceding straight wingfold structure, referring to Fig. 3, the bottom surface of the fuselage is longitudinally provided with rear wing and turns
Axis 20；It is fixed with rear left torsional spring slot 21 on the left back straight wing, is fixed with rear right torsional spring slot 22, institute on the straight wing behind the right side
State rear left torsional spring slot and it is described after right torsional spring slot make-up be arranged to be formed accommodate after torsional spring space, it is described after torsional spring 23 be installed on pair
It in the rear left torsional spring slot of button and rear right torsional spring slot, and is mounted in rear wing shaft 20, generally covers in rear wing shaft.Further
, the bottom of the rear wing shaft is equipped with the rear shaft-cup 24 for preventing the rear straight wing from falling off during folding and unfolding.
When the rear straight wingfold structure is installed, rear shaft 20 is fixed on the downside of 01 tail portion of fuselage, by rear left torsional spring slot
21 are cemented on the left back straight wing 06 with glue, after rear right torsional spring slot 22 is cemented in the right side with glue on the straight wing 04；Then it is turned round by after
Spring 23 is mounted in the torsional spring slot of rear left torsional spring slot 21 and rear 22 make-up of right torsional spring slot, then is installed in rear shaft 20, and screw is used
Rear shaft cover board 24 is fixed on rear 20 bottom of shaft, pushes down wing.
In the rear straight wingfold structure structure: rear straight wingfold is roughly the same with expansion process and the preceding straight wing, area
It is not to be unfolded backward due to it, not set front wing latch structure, therefore can be directly folded by external force.
Folding wings unmanned plane provided by the invention, during expansion, the preceding straight wing and the rear straight wing can be in left and right
Two sides centered on fuselage in symmetrical expansion so that the preceding straight wing and the rear straight wing during expansion in two sides to nothing
The equilibrant force indifference of man-machine fuselage does not easily lead to fuselage rotation, to improve unmanned plane stability, and then improves nobody
The launching success rate of machine.
Aileron in background technique is arranged on the two sides winglet of zigzag folding wing, and steering engine is installed and is controlled, exhibition
The arrangement of cable has very big hidden danger when opening, and in the application, can be used before aileron is set to by which on the straight wing, for
Steering engine installation and control, the arrangement security performance of cable improves when expansion.Preferred scheme is straight after described referring to Fig. 1 and Fig. 4
Aileron is provided on the wing, the aileron includes port aileron 07 and starboard aileron 05；The starboard aileron 05 passes through with the straight wing 04 behind the right side
Hinge paper is connected, and starboard aileron 05 can turn down up and down, and the first aileron connector 29 is fixed on the starboard aileron, is put down behind the right side
It is fixed with right standard rudder machine 32 on the straight wing 04, in general, fixing right standard rudder rack 34 behind the right side on the straight wing, right standard rudder machine is fixed on right standard rudder rack
On, the steering engine arm 31 of the right standard rudder machine and the first aileron connector are hinged；The port aileron 07 and the left back straight wing 06 are logical
It crosses hinge paper to be connected, port aileron 07 can turn down up and down, and the second aileron connector is fixed on the port aileron, described left back flat
It is fixed with left rudder machine on the straight wing 06, in general, fixing left rudder rack 33 on the left back straight wing, left rudder machine is fixed on left rudder rack
On, the steering engine arm of the left rudder machine and the second aileron connector are hinged, this structure, can design steering engine and aileron more
It is compact, when aileron is installed, the first aileron connector 29 is screwed on starboard aileron 05；Cross head screw 30 is fixed
On the steering engine arm 31 of right standard rudder machine, the steering engine arm 31 of right standard rudder machine is fixed on right standard rudder machine 32, right standard rudder machine 32 is fixed on right standard rudder
In rack 34, right standard rudder rack 34 is screwed behind the right side on the straight wing 04, and 30 screw rod head of cross head screw is passed through
In the long hole of first aileron connector 29, for controlling the angle of starboard aileron 05；Port aileron 07 and the left back straight wing 06 pass through conjunction
Page paper is connected, and port aileron 07 can turn down up and down；Second aileron connector 29 is screwed on port aileron 07；By ten
Line pan head screw 30 is fixed on the steering engine arm of left rudder machine, and the steering engine arm of left rudder machine is fixed on left rudder machine, left rudder machine is consolidated
It is scheduled in left rudder rack 33, left rudder rack 33 is screwed on the left back straight wing 06, and by cross head screw screw rod
Head passes through in the long hole of the second aileron connector, for controlling the angle of port aileron 07.
Existing structure can be used in vertical fin deployed configuration, as a preferred solution, described to hang down referring to Fig. 1 and Fig. 5
Tail includes left vertical fin 09 and right vertical fin 08；The left vertical fin is connect by left vertical fin axis 42 with the fuselage, and link position is located at
The left side of the fuselage is cased with left vertical fin cover 44 on the left vertical fin axis, be equipped in the left vertical fin cover for left vertical fin to
The left vertical fin torsional spring 43 of upper expansion；The right vertical fin is connect by right vertical fin axis with the fuselage, and link position is located at the machine
The right side of body is cased with right vertical fin cover 45 on the right vertical fin axis, is equipped in the right vertical fin cover and is unfolded upwards for right vertical fin
Right vertical fin torsional spring 46；Vertical fin positioning card 55, the folding wings unmanned plane are provided between the left vertical fin and the right vertical fin
In a fully folded condition, the vertical fin positioning card be located at vertical fin top and be located at the preceding straight wing lower section and with it is described
Preceding straight wing contact.
When the vertical fin is installed, by 44 sets of left vertical fin cover on vertical fin axis 42, left vertical fin torsional spring 43 is installed, then from fuselage
01 tail inner side is pierced by be fixed with the left crossed countersunk head screw 47 of vertical fin 08, is then pre-tightened to left vertical fin 08, is pre-tightened
It is fixed afterwards with hexagon socket cap head screw 48, it is general that 110 ° of annular grooves, interior hexagonal cylindrical head spiral shell can be opened on left vertical fin
Nail in this way limits expanded position, that is, realizes Automatic-expanding, in turn ensure expanded position across annular groove；The right side is hung down
45 sets of hood on vertical fin axis 42, are installed upper right vertical fin torsional spring 46, are then pierced by from 01 tail inner side of fuselage and are used with right vertical fin 09
Crossed countersunk head screw 47 is fixed, and then pre-tightens to right vertical fin 09, pre- next to be consolidated with hexagon socket cap head screw
Fixed, general that 110 ° of annular grooves can be opened on right vertical fin, hexagon socket cap head screw passes through annular groove, in this way to expanded position into
Row limit, that is, realize Automatic-expanding, in turn ensures expanded position, and it is also small to occupy body space.
The structure, left vertical fin and right vertical fin are being turned round when the preceding straight span, which is reached, to apply pressure to vertical fin positioning card 55
Expansion falls off up to perpendicular to fuselage, during vertical fin is unfolded, vertical fin positioning card 55 is got rid of upwards under the active force of spring；By
It is unfolded upwards in vertical fin, in recycling, vertical fin will not be with ground face contact, it is not easy to damage.
Existing structure can be used in foldable propeller component, as a preferred solution, referring to Fig. 3 and Fig. 4, institute
The tail end for stating fuselage is equipped with tailgate 27, and motor 35 is fixed on the tailgate, foldable propeller is fixed on the motor
Component, the blade 10 of the foldable module can collapsed forward be bonded with the afterbody, can generally be done in afterbody
It closes up, for placing folded blade, specifically, fixing paddle shaft 36 on the motor shaft of motor, lock ring 37 is provided in paddle shaft
With paddle folder 38, blade and paddle folder are hinged.When installation, blade 10 is fixed on paddle folder 38 with customization screw rod 40 and locknut 41, so
Paddle lock ring 37, paddle are pressed from both sides 38 sets in paddle shaft 36 afterwards, the first step is carried out with spinner 39 and fixes.Then tail-rotor component is inserted in motor
On axis 35, carries out second step and fix and lock.By way of fixing blade screw rod and locknut, so that blade and paddle press from both sides shape
At articulated structure, blade 10 can be rolled in the past to be bonded with 01 tail portion of fuselage, and paddle can be realized by way of torsional spring is arranged on screw rod
The Automatic-expanding of leaf.Be fixed with microswitch 25 and back damping pad 26 on the tailgate, the microswitch be pierced by it is described after subtract
Shake pad exposes outside the back damping pad, and the rear straight span can trigger microswitch when reaching predetermined position and control the electricity
Machine operates, and can be realized at a distance from the rear straight wing by default microswitch, such as when rear straight wingfold, microswitch position
In the side of the rear straight wing, when the rear straight wing fully opens after correct can be to being against on microswitch, certainly can be with
Using other way, it is not specifically limited herein.In general, microswitch 25 is cemented on tailgate 27 with glue, by rear damping
Pad 25 is cemented on tailgate 27 with glue, and microswitch exposes from the hole of back damping pad 25, by hexagonal in the socket cap of motor 35
Screw is fixed on tailgate 27；This component is installed on fuselage tail frame 28.
The feeder line foldable assembly of above-mentioned folding wings unmanned plane can be used existing structure, and it is preferable to use following in the application
Structure: referring to figs. 7 and 8, the fuselage bottom place of cutting flat with is provided with rectangle hole, for hiding feeder line foldable assembly；It is described
Feeder line foldable assembly includes feeder line folding stand 50, feeder line fixing seat 49 and antenna 53, and the fixing seat is fixed on the fuselage
Bottom surface, the feeder line folding stand is hinged by pin shaft 51 and the feeder line folding stand, and is equipped on the pin shaft for folding
The feeder line torsional spring 52 of frame drops down；Feeder line angle coupling 54 is installed, the antenna is fixed on institute on the feeder line folding stand
It states on feeder line angle coupling；In a fully folded condition, the antenna is located at the rear straight wing to the folding wings unmanned plane
Top and with it is described after the straight wing contact.When installation, feeder line angle coupling 54 is mounted on feeder line folding stand 50, and by antenna 53
It is mounted on feeder line angle coupling 54, this component and feeder line torsional spring 52, feeder line fixing seat 49 is then passed through into pin shaft 51 through one
It rises, finally feeder line fixing seat 49 is fixed on the inside of 01 abdomen of fuselage.
It should be noted that front, back, left, right, up, down in the application, top, bottom, cross and the orientation such as vertical are flat with unmanned plane
Put state be reference, can also with or unmanned plane with horizontal flight when state be reference.
Embodiment 2, the present invention also provides a kind of launching techniques of above-mentioned folding wings unmanned plane, comprising the following steps:
Step 1, folding wings unmanned plane is in completely folded state, is placed in corresponding launching tube A；
Wherein, folding wings unmanned plane refers in completely folded state:
For the preceding straight wing, it is folded to after straight flapwise before the left front straight wing and the right side and is overlapped with fuselage, be located at fuselage roof
Cut flat with position；
For the rear straight wing, it is folded to before straight flapwise after the left back straight wing and the right side and is overlapped with fuselage, be located at fuselage bottom
Cut flat with position；
For vertical fin, left vertical fin and right vertical fin are folded down, and are overlapped with the fuselage, and left vertical fin is located at the left side of fuselage,
Right vertical fin is located at the right side of fuselage, and vertical fin is pushed down by the preceding straight wing；
For feeder line foldable assembly, feeder line folding stand drives antenna to be folded up to fuselage rectangle hole, by rear straight
The wing is pushed down；
After folding wings unmanned plane is in completely folded state, radial full-size is no more than the internal diameter of launching tube, length
No more than the length of launching tube, can be accommodated in launching tube completely, completely folded state can be found in Fig. 9；
Step 2, launching tube installation is fixed；
Step 3, starting launching tube, folding wings unmanned plane is popped up from launching tube, and expansion is deformed up to being fully deployed rapidly,
Complete emission process:
Specific expansion deformation process are as follows: (1) the preceding straight wing and the rear straight wing are first unfolded simultaneously:
The left front straight wing and it is right before be expanded to before straight flapwise vertical with fuselage, be located at fuselage two sides；The left back straight wing and
Be expanded to after straight flapwise behind the right side it is vertical with fuselage, be located at fuselage two sides；
(2) vertical fin and the expansion of feeder line foldable assembly:
Expansion is straight upwards when the preceding straight span, which is reached, to apply pressure to vertical fin positioning card 55 for left vertical fin and right vertical fin
It falls off to perpendicular to fuselage, during vertical fin is unfolded, vertical fin positioning card 55 is got rid of；
Feeder line foldable assembly drops down when the rear straight span, which is reached, to stop it, until perpendicular to fuselage.
The expansion process of above-mentioned unmanned plane can be found in Figure 10, emit unmanned plane by using this method, in the process of expansion
In, the preceding straight wing and the rear straight wing can be unfolded centered on fuselage in symmetrical in the left and right sides, so that the preceding straight wing
With the rear straight wing during expansion in two sides to the equilibrant force indifference of unmanned aerial vehicle body, do not easily lead to fuselage rotation, thus
Unmanned plane stability is improved, and then improves the launching success rate of unmanned plane.In addition, the preceding straight wing, the rear straight wing, vertical fin and
Feeder line foldable assembly can be opened in order, can guarantee smooth opening between various components.It should be noted that it is above-mentioned nobody
The launching technique of machine is not limited only to the above method, and the platform transmitting of other devices also can be used；Blade is since this is in machine
Other components are unfolded without influence in the rear end of body two sides, therefore it is unfolded before electric motor starting, the general and preceding straight wing
It is acted together with the rear straight wing.
Embodiments of the present invention above described embodiment only expresses, the description thereof is more specific and detailed, but can not
Therefore limitations on the scope of the patent of the present invention are interpreted as.It should be pointed out that for those of ordinary skill in the art,
Without departing from the inventive concept of the premise, various modifications and improvements can be made, these belong to protection model of the invention
It encloses.Therefore, the scope of protection of the patent of the invention shall be subject to the appended claims.
Claims (9)
1. a kind of folding wings unmanned plane including fuselage (01), the preceding straight wing, the rear straight wing, is installed on the foldable of afterbody
Vertical fin and be installed on the foldable propeller component of back body, which is characterized in that
One in the preceding straight wing and the rear straight wing is installed on the top surface of the fuselage, another is installed on the machine
The bottom surface of body, and can be folded centered on the fuselage.
2. a kind of folding wings unmanned plane according to claim 1, which is characterized in that
The preceding straight wing is installed on the top surface of the fuselage, including being located at the left front straight wing (03) on the left of fuselage and being located at institute
State the straight wing (02) before the right side on the right side of fuselage, it is described it is right before the straight wing and the left front straight wing can be centered on the fuselage
It folds back；
The straight wing is installed on the bottom surface of the fuselage after described, including being located at the left back straight wing (06) on the left of fuselage and being located at institute
State the straight wing (04) behind the right side on the right side of fuselage, it is described it is right after the straight wing and the left back straight wing can be centered on the fuselage
Collapsed forward；
The fuselage is cylindrical-shaped structure, and top cuts flat with to be formed for placing the folded left front straight wing and the straight wing before the right side,
Bottom cuts flat with to be formed for placing the folded left back straight wing and the straight wing behind the right side.
3. a kind of folding wings unmanned plane according to claim 2, which is characterized in that
The top surface of the fuselage is longitudinally provided with front wing shaft (11)；
It is fixed with front left torsional spring slot (17) on the left front straight wing, is fixed with front right torsional spring slot on the straight wing before the right side
(15), the space to be formed and accommodate preceding torsional spring, the preceding torsional spring is arranged in the front left torsional spring slot and the front right torsional spring slot make-up
(16) it is installed in the front left torsional spring slot and front right torsional spring slot of make-up, and is mounted on front wing shaft (11), the front wing shaft
Inside it is horizontally arranged with the front wing bolt cooperated respectively with the front left torsional spring slot and front right torsional spring slot, it is close in the front wing shaft
The side of the front fuselage is respectively fixed with guide part, and pressure spring (12), the pressure are horizontally arranged on two guide parts
Spring is not connected with one end of guide part connection with the corresponding front wing bolt；
The bottom surface of the fuselage is longitudinally provided with rear wing shaft (20)；
It is fixed with rear left torsional spring slot (21) on the left back straight wing, is fixed with rear right torsional spring slot on the straight wing behind the right side
(22), the rear left torsional spring slot and it is described after right torsional spring slot make-up be arranged to be formed accommodate after torsional spring space, it is described after torsional spring
(23) it is installed in the rear left torsional spring slot and rear right torsional spring slot of make-up, and is mounted on rear wing shaft (20).
4. a kind of folding wings unmanned plane according to claim 3, which is characterized in that be also equipped on the fuselage for inhaling
The preceding resilient cushion (18) of the kinetic energy after the preceding straight span is opened is received, is equipped at the top of the front wing shaft for the straight wing before preventing
The preceding shaft-cup (19) to fall off during folding and unfolding；
The bottom of the rear wing shaft is equipped with the rear shaft-cup for preventing the rear straight wing from falling off during folding and unfolding
(24)。
5. a kind of folding wings unmanned plane according to claim 3 or 4, which is characterized in that be provided on the straight wing after described
Aileron, the aileron include port aileron (07) and starboard aileron (05)；
The starboard aileron (05) is connected with the straight wing (04) behind the right side by hinge paper, and starboard aileron (05) can turn down up and down, described
It is fixed with the first aileron connector (29) on starboard aileron, is fixed with right standard rudder machine (32), the right side on the straight wing (04) behind the right side
The steering engine arm (31) and the first aileron connector of steering engine are hinged；
The port aileron (07) is connected with the left back straight wing (06) by hinge paper, and port aileron (07) can turn down up and down, described
It is fixed with the second aileron connector on port aileron, is fixed with left rudder machine, the rudder of the left rudder machine on the left back straight wing (06)
Horn and the second aileron connector are hinged.
6. a kind of folding wings unmanned plane according to claim 3 or 4, which is characterized in that the vertical fin includes left vertical fin
(09) and right vertical fin (08)；
The left vertical fin is connect by left vertical fin axis (42) with the fuselage, and link position is located at the left side of the fuselage, described
It is cased with left vertical fin cover (44) on left vertical fin axis, the left vertical fin torsional spring being unfolded upwards for left vertical fin is installed in the left vertical fin cover
(43)；
The right vertical fin is connect by right vertical fin axis with the fuselage, and link position is located at the right side of the fuselage, described right vertical
It is cased with right vertical fin cover (45) on tailing axle, the right vertical fin torsional spring being unfolded upwards for right vertical fin is installed in the right vertical fin cover
(46)；
It is provided between the left vertical fin and the right vertical fin vertical fin positioning card (55), the folding wings unmanned plane is folding completely
Under state, the vertical fin positioning card is located at the top of vertical fin and is located at the lower section of the preceding straight wing and connects with the preceding straight wing
Touching.
7. a kind of folding wings unmanned plane according to claim 3 or 4, which is characterized in that the tail end of the fuselage is equipped with
Tailgate (27) is fixed with motor (35) on the tailgate, foldable propeller component is fixed on the motor, described foldable
The blade (10) of component can collapsed forward be bonded with the afterbody；
Microswitch (25) and back damping pad (26) are fixed on the tailgate, the microswitch is pierced by the back damping pad dew
Out outside the back damping pad, the rear straight span can trigger microswitch and control the motor fortune when reaching predetermined position
Turn.
8. a kind of folding wings unmanned plane according to claim 3 or 4, which is characterized in that further include feeder line foldable assembly, institute
It states the fuselage bottom place of cutting flat with and is provided with rectangle hole, for hiding feeder line foldable assembly；
The feeder line foldable assembly includes feeder line folding stand (50), feeder line fixing seat (49) and antenna (53), and the fixing seat is solid
Due to the bottom surface of the fuselage, the feeder line folding stand is hinged by pin shaft (51) and the feeder line folding stand, and the pin shaft
On feeder line torsional spring (52) for folding stand drops down is installed；
It is equipped on the feeder line folding stand feeder line angle coupling (54), the antenna is fixed on the feeder line angle coupling；
The folding wings unmanned plane in a fully folded condition, the antenna be located at it is described after the straight wing top and with it is described after
Straight wing contact.
9. a kind of launching technique of the described in any item folding wings unmanned planes of claim 1-8, which is characterized in that including following step
It is rapid:
Step 1, folding wings unmanned plane is in completely folded state, is placed in corresponding launching tube；
Wherein, folding wings unmanned plane refers in completely folded state:
For the preceding straight wing, it is folded to after straight flapwise before the left front straight wing and the right side and is overlapped with fuselage, cut flat with positioned at fuselage roof
Position；
For the rear straight wing, it is folded to before straight flapwise after the left back straight wing and the right side and is overlapped with fuselage, cut flat with positioned at fuselage bottom
Position；
For vertical fin, left vertical fin and right vertical fin are folded down, and are overlapped with the fuselage, and left vertical fin is located at the left side of fuselage, and the right side is hung down
Tail is located at the right side of fuselage, and vertical fin is pushed down by the preceding straight wing；
For feeder line foldable assembly, feeder line folding stand drives antenna to be folded up to fuselage rectangle hole, by rear straight wing pressure
Firmly；
After folding wings unmanned plane is in completely folded state, radial full-size is no more than the internal diameter of launching tube, and length does not surpass
The length of launching tube is crossed, can be accommodated in launching tube completely；
Step 2, launching tube installation is fixed；
Step 3, start launching tube, folding wings unmanned plane is popped up from launching tube, and expansion deformation is completed up to being fully deployed rapidly
Emission process:
Specific expansion deformation process are as follows: (1) the preceding straight wing and the rear straight wing are first unfolded simultaneously:
The left front straight wing and it is right before be expanded to before straight flapwise vertical with fuselage, be located at fuselage two sides；After the left back straight wing and the right side
Be expanded to after straight flapwise it is vertical with fuselage, be located at fuselage two sides；
(2) vertical fin and the expansion of feeder line foldable assembly:
Left vertical fin and right vertical fin when the preceding straight span, which is reached, to apply pressure to vertical fin positioning card (55) upwards expansion until
Perpendicular to fuselage, during vertical fin is unfolded, vertical fin positioning card (55), which is got rid of, falls off；
Feeder line foldable assembly drops down when the rear straight span, which is reached, to stop it, until perpendicular to fuselage.
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| CN110341951A (en) * | 2019-07-22 | 2019-10-18 | 中北大学 | A kind of unmanned vehicle of folding wing and tilting rotor |
| CN111942572A (en) * | 2020-09-21 | 2020-11-17 | 中国工程物理研究院总体工程研究所 | Side single vertical tail flying patrol device with vertical tail unfolding device |
| CN112265631A (en) * | 2020-10-16 | 2021-01-26 | 中国空气动力研究与发展中心 | Box-type folding wing unmanned aerial vehicle layout capable of realizing modular assembly with variable aspect ratio |
| CN114148506A (en) * | 2021-12-06 | 2022-03-08 | 浙江大学 | Foldable variant unmanned aerial vehicle and control method thereof |
| CN115924070A (en) * | 2022-11-28 | 2023-04-07 | 西北工业大学 | Barrel type launching and spreading foldable single-control-plane aircraft and design method thereof |
| CN117775339A (en) * | 2024-02-28 | 2024-03-29 | 成都金支点科技有限公司 | Servo control mechanism and unmanned aerial vehicle of collapsible rudder |
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