CN109436296A - The folding wings unmanned plane and its launching technique of cartridge type transmitting - Google Patents
The folding wings unmanned plane and its launching technique of cartridge type transmitting Download PDFInfo
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- CN109436296A CN109436296A CN201811601135.8A CN201811601135A CN109436296A CN 109436296 A CN109436296 A CN 109436296A CN 201811601135 A CN201811601135 A CN 201811601135A CN 109436296 A CN109436296 A CN 109436296A
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- 238000000034 method Methods 0.000 title claims abstract description 31
- 230000008569 process Effects 0.000 claims abstract description 17
- 230000007246 mechanism Effects 0.000 claims description 134
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 19
- 230000008602 contraction Effects 0.000 claims description 13
- 238000004891 communication Methods 0.000 claims description 6
- 238000009434 installation Methods 0.000 claims description 6
- 230000009471 action Effects 0.000 claims description 5
- 230000008901 benefit Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 19
- 239000007789 gas Substances 0.000 description 15
- 230000015572 biosynthetic process Effects 0.000 description 2
- 239000000567 combustion gas Substances 0.000 description 2
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- 230000004048 modification Effects 0.000 description 2
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
- B64C11/28—Collapsible or foldable blades
-
- 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
-
- 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
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- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
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Abstract
The present invention provides the folding wings unmanned plane and its launching technique of a kind of cartridge type transmitting, and the folding wings unmanned plane of cartridge type transmitting includes: folding wings unmanned plane (7) and launching tube (6)；In wound packages state, the folding wings unmanned plane (7) is in completely folded state and is set to the inside of the launching tube (6)；When the launching tube (6) emits folding wings unmanned plane (7), the folding wings unmanned plane (7) is by the pop-up from the launching tube (6), after the variant process gradually spread out, climbs and patrol winged task status into what is be fully deployed.Advantage are as follows: have structure simple, light-weight, the stronger feature of engineering realizability.Meanwhile by the present invention in that space utilization rate of the invention is effectively improved and in the aeroperformance for patrolling winged task status with the Z-shaped folding wing for having the characteristics that occupy little space in a folded configuration and wing area is big in the deployed state, aspect ratio is big.
Description
Technical field
The invention belongs to folding wings air vehicle technique fields, and in particular to a kind of folding wings unmanned plane of cartridge type transmitting and its
Launching technique.
Background technique
Folding wings unmanned plane can be folded each component by fold mechanism, its bulk is effectively reduced, and be realized a variety of
Weapon platform transmitting is launched.It is executable to scout and injure assessment, communication relay, mesh by the combination with ammunition technology
The single or the multi-tasks such as instruction, precision strike are marked, there is the features such as at low cost, efficiency-cost ratio is high, and size is small, and stealth capabilities are strong.
Compared to traditional unmanned plane, folding wings unmanned plane can be emitted or be launched by a variety of weapon platforms, can be fitted into the arms and services, can be quickly
Into the theater of war, penetration ability is strong, and tactical application is flexible；Compared to conventional ammunition, airborne period is long, and sphere of action is big, can
It was found that and attacking hidden Time sensitive target.
Traditional folding wings unmanned plane mostly uses the X-type wing or the tandem wing to be laid out pattern.X-type wing layout aircraft efficient loading
Space is relatively small；And the front and back wing aerodynamic interference phenomenon of tandem wing layout aircraft is than more serious.
Summary of the invention
In view of the defects existing in the prior art, the present invention provides folding wings unmanned plane and its launch party of a kind of transmitting of cartridge type
Method can effectively solve the above problems.
The technical solution adopted by the invention is as follows:
The present invention provides a kind of folding wings unmanned plane of cartridge type transmitting, comprising: folding wings unmanned plane (7) and launching tube (6)；
In wound packages state, the folding wings unmanned plane (7) is in completely folded state and is set to the inside of the launching tube (6)；
When the launching tube (6) emits folding wings unmanned plane (7), the folding wings unmanned plane (7) is by from the launching tube (6)
Pop-up climbs after the variant process gradually spread out and patrols winged task status into what is be fully deployed；
Wherein, the folding wings unmanned plane (7) include fuselage (1), Z-shaped folding wing (2), left flying tail (3A),
Right flying tail (3B), all moving fin (4) and foldable propeller component (5)；
The fuselage (1) is cylindrical-shaped structure, the bottom of the fuselage (1) cut flat with to be formed it is folded described for placing
The setting plane of Z-shaped folding wing (2)；The left and right sides of fuselage (1) tail portion are shunk, and the contraction of class truncated cone-shaped is formed
Section (15)；The left and right sides of the end of the contraction section (15) are for placing the folded foldable propeller component
(5) setting face；The right side of the front end of the contraction section is cut flat with, and is formed for placing the folded all moving fin (4)
Vertical plane (16)；The upper surface of the contraction section (15) forms symmetrical left cut flat incline plane (17) and right cut flat incline plane
(18), the left cut flat incline plane (17) is for placing the folded left flying tail (3A)；The right cut flat incline plane (18)
For placing the folded right flying tail (3B)；
The Z-shaped folding wing (2) includes middle wing panel (23), left outside main wing (24A), the right outer master of left outside aileron (24B)
The wing (25A) and right external aileron (25B)；The center of the middle wing panel (23) is mounted on institute by the way that wing centre section fold mechanism (21) are foldable
State the center of fuselage (1) bottom；The left side of the middle wing panel (23) passes through the foldable peace of left outside main wing fold mechanism (22A)
Fill the left outside main wing (24A)；The right side of the middle wing panel (23) passes through the right outer foldable installation institute of main wing fold mechanism (22B)
State main wing outside the right side (25A)；The left outside main wing (24A) and the outer main wing in the right side (25A) are relative to middle wing panel (23) left and right
Face is symmetrical；When the Z-shaped folding wing (2) is in folded state, the Z-shaped folding wing (2) be folded into length with
Fuselage (1) length is equivalent, is parallel to the small "-" type wing of the fuselage (1) axis；When the Z-shaped folding wing
(2) in when patrolling under winged task status, the Z-shaped folding wing (2) is launched into the length that length is 2 times of fuselages (1), vertical
In the spread-eagel type wing of fuselage (1)；
The outer main wing in the right side (25A) is installing the right external aileron (25B) along tangential 0.7~1 region；The right external aileron
The one end of (25B) is rotatably connected by right outer main wing control surface shaft (28) with the outer main wing in the right side (25A)；It is described right outer main
Right external aileron deflection steering engine (26B) is installed, right external aileron deflection steering engine (26B) is deflected by right external aileron on the wing (25A)
Servo driving connecting rod (27) is connect with the right external aileron (25B), and then the right external aileron (25B) main wing outside the right side is driven to grasp
Vertical face shaft (28) deflection；The left outside main wing (24A) is arranged the deflectable left outside aileron (24B) and for driving
The left outside aileron movement steering engine (26A) of left outside aileron (24B) deflection；The left outside aileron (24B) and the right external aileron
(25B), center relative to the Z-shaped folding wing (2) or so face are symmetrical；
The left flying tail (3A) passes through the foldable tail portion left side for being mounted on the fuselage (1) of left horizontal tail fold mechanism
Top；The right flying tail (3B) is right by the foldable tail portion for being mounted on the fuselage (1) of right horizontal tail fold mechanism (31)
Upper side, there are certain inverted diherdrals for the left flying tail (3A) and the right flying tail (3B), and then are conducive to improve
The space utilization rate of cylinder interior folding state；
The all moving fin (4) passes through vertical fin fold mechanism (41) foldable rear for being mounted on the fuselage (1), and
And all moving fin (4) is located at the front of the right flying tail (3B)；Wherein, the setting quantity of all moving fin (4)
For one or two；When all moving fin (4) are arranged one, all moving fin (4) is located at the fuselage (1) rear
Left or right side；When all moving fin (4) are arranged two, all moving fin (4) is located at the fuselage (1) rear
Left and right side；
The foldable propeller component (5) is installed in the middle part of the rear end face of the fuselage (1), including paddle folder (53) and
The left blade (51A) and right blade (51B) being symmetrically arranged at left and right sides of the paddle folder (53)；The left blade (51A) and institute
Stating right blade (51B) is antisymmetry structure；Wherein, the paddle folder (53) passes through drive shaft (54) and the fuselage (1) inside
Driving motor connection, the driving motor drive the paddle folder (53) to rotate by the drive shaft (54)；The left blade
(51A) passes through the foldable left end for being mounted on the paddle folder (53) of left blade fold mechanism (52A)；The right blade (51B) is logical
Cross the foldable right end for being mounted on the paddle folder (53) of right blade fold mechanism (52B).
Preferably, the fuselage (1) uses modularized design, and load cabin (11) has been sequentially arranged from head to tail portion, has been moved
Power powerhouse dome (12), inertial navigation cabin (13) and piggyback pod (14)；Wherein, the load cabin (11) is for carrying target seeker and fight
Portion completes precision strike task, carrying scouting also may be selected, communication equipment is completed to scout and injures assessment, air alert, communication
Relay task；The electrical source of power cabin (12) is for carrying energy supply equipment, and then to the foldable propeller component
(5), the energy needed for load cabin (11) inner electronic equipment provides；The inertial navigation cabin (13) is inertial navigation unit cabin, cloth
It is equipped with gyroscope and accelerometer equipment；The piggyback pod (14) is disposed with to drive the foldable propeller component (5)
Power-equipment.
Preferably, the middle wing panel (23) is a length and the isometric rectangle wing panel of the fuselage (1) length；In described
Wingfold mechanism (21) is rectangular rotating mechanism, including wing centre section driving spring (20A) and wing centre section mandrel (20B), is torsional spring or whirlpool
Wind spring.
Preferably, the left outside main wing (24A) and the outer main wing in the right side (25A) are to be installed on middle wing panel (23) bottom
The rectangle wing panel in outside, length are the half of middle wing panel (23) length, and chord length is less than the chord length of the middle wing panel (23).
Preferably, the outer main wing fold mechanism (22B) of the left outside main wing fold mechanism (22A) and the right side is circular rotating
Mechanism.
Preferably, the left flying tail (3A) and the right flying tail (3B) are left and right face symmetrical structure, for institute
It states right flying tail (3B), including right horizontal tail fold mechanism (31), horizontal tail rotary shaft (32), horizontal tail deflect steering engine (33), horizontal tail
The peaceful tail rotation Ii miter (36) of control surface shaft (34), horizontal tail control surface (35)；The right horizontal tail fold mechanism (31) passes through
The horizontal tail rotary shaft (32) connect with the fuselage (1), for controlling the folding and expansion of the right flying tail (3B)；Institute
Horizontal tail rotation Ii miter (36) are stated for controlling the rotation angle of the right flying tail (3B)；The horizontal tail control surface (35) is logical
It crosses the horizontal tail control surface shaft (34) to connect with horizontal tail deflection steering engine (33), horizontal tail deflection steering engine (33) is installed on
On the right horizontal tail fold mechanism (31), the inclined of the horizontal tail control surface (35) is controlled by the horizontal tail control surface shaft (34)
Turn.
Preferably, all moving fin (4) includes vertical fin fold mechanism (41), vertical fin rotary shaft (42), vertical fin deflection rudder
Machine (43), vertical fin control surface shaft (44), vertical fin control surface (45) and vertical fin rotation Ii miter (46)；The vertical fin fold mechanism
(41) it is connect by the vertical fin rotary shaft (42) with the fuselage (1), for controlling the folding and exhibition of all moving fin (4)
It opens；Vertical fin deflection steering engine (43) is mounted on the vertical fin fold mechanism (41), passes through the vertical fin control surface shaft
(44) deflection of the vertical fin control surface (45) is controlled；The vertical fin rotation Ii miter (46) is for controlling all moving fin
(4) rotation angle.
Preferably, the launching tube (6) includes dustproof cover (61), transmitting tube stent (62), cylinder (63), piston boosting dress
Set (64), gas generator (65) and launching tube pedestal (66)；
The head of the cylinder (63) is installed by the dustproof cover (61)；The external of the cylinder (63) installs the launching tube
Bracket (62)；The tail portion of the cylinder (63) is installed by the launching tube pedestal (66)；The launching tube pedestal (66) is installed above
The gas generator (65)；The outlet port of the gas generator (65) installs the piston assist device (64)；It is described
The folding wings unmanned plane (7) is set before piston assist device (64).
The present invention also provides a kind of launching techniques of the folding wings unmanned plane of cartridge type transmitting, comprising the following steps:
Step 1, folding wings unmanned plane (7) is in completely folded state, and is placed in launching tube (6)；
Wherein, folding wings unmanned plane (7) is in completely folded state, refers to:
For Z-shaped folding wing (2), left outside main wing (24A) folds into middle wing panel around left outside main wing fold mechanism (22A)
(23) underface, right outer main wing (25A) main wing fold mechanism (22B) outside the right side fold into the underface of middle wing panel (23), in
Wing panel (23) rotates to the underface of fuselage (1) around wing centre section fold mechanism (21), at this point, Z-shaped folding wing (2) is folded into exhibition
The long small "-" type wing for being equal to, being parallel to the fuselage (1) axis with fuselage (1) length；
For left flying tail (3A) and right flying tail (3B), the left flying tail (3A) passes through left horizontal tail folding machine
Structure is folded to the left cut flat incline plane (17) of the fuselage (1)；The right flying tail (3B) passes through right horizontal tail fold mechanism (31)
It is folded to the right cut flat incline plane (18) of the fuselage (1)；
For all moving fin (4), all moving fin (4) is folded to the fuselage (1) by vertical fin fold mechanism (41)
The vertical plane (16) of right side；
For foldable propeller component (5), left blade (51A) is folded to institute by left blade fold mechanism (52A)
State the tail portion left side of fuselage (1)；Its right blade (51B) is folded to the fuselage (1) by right blade fold mechanism (52B)
Tail portion right side；
By to the fuselage (1) carry out bottom cut flat with, tail portion shrink, tail portion upper surface be cut into left cut flat incline plane (17) and
The design of right cut flat incline plane (18), after the folding wings unmanned plane (7) is in completely folded state, radial full-size is not
More than the diameter of the launching tube (6), the length of of length no more than launching tube (6) therefore can be accommodated in the hair completely
In the cylinder of shooting cylinder (6)；
Step 2, after individual soldier bears launching tube (6) the arrival launch site for being placed with the folding wings unmanned plane (7), by institute
The launch angle needed installs the launching tube (6)；
Step 3, start the gas generator (65) of launching tube (6), gas generator (65) generates high pressure gas, passes through work
Fill in assist device (64) pop-up from launching tube (6) by the folding wings unmanned plane (7)；
Step 4, the folding wings unmanned plane (7) is after the pop-up from the launching tube (6), by the variant gradually spread out
After process, climbs into the winged task status of patrolling being fully deployed, complete emission process；
Specifically, Z axis is in the plane of symmetry of Z-shaped folding wing (2), perpendicular to X using the axial direction of fuselage (1) as X-axis
Axis, using the direction vertical with X-Z plane as Y-axis；
After folding wings unmanned plane (7) is by the pop-up from the launching tube (6), under the action of each fold mechanism, from
Folded state is gradually spread out, until forming fully unfolded position, variant process are as follows:
For Z-shaped folding wing (2), wherein wing panel (23) is carried out suitable in the xy plane by wing centre section fold mechanism (21)
Hour hands rotation, meanwhile, left outside main wing (24A) is rotated counterclockwise in the xy plane by left outside main wing fold mechanism (22A),
Right outer main wing (25A) is rotated counterclockwise in the xy plane by right outer main wing fold mechanism (22B), by left outside main wing
After (24A), middle wing panel (23) and right outer main wing (25A) form the intermediate state of Z-shaped, middle wing panel (23), left outside main wing (24A)
Continue to rotate with main wing outside the right side (25A), until middle wing panel (23) rotates to the position vertical with fuselage (1), left outside main wing (24A)
Rotate to the position conllinear with middle wing panel (23), until right outer main wing (25A) rotates to the position conllinear with middle wing panel (23), this
When Z-shaped folding wing (2) to be launched into length be the length of 2 times of fuselages (1), the spread-eagel type wing perpendicular to fuselage (1)；
For left flying tail (3A) and right flying tail (3B), left flying tail (3A) is existed by left horizontal tail fold mechanism
It is rotated counterclockwise in X/Y plane, until the axis of left flying tail (3A) is vertical with the axis of the fuselage (1)；Together
When, right flying tail (3B) is rotated clockwise in the xy plane by right horizontal tail fold mechanism (31), until right complete dynamic flat
Until the axis of tail (3B) is vertical with the axis of the fuselage (1)；
For all moving fin (4), all moving fin (4) is revolved in XZ plane clockwise by vertical fin fold mechanism (41)
Turn, until the axis of all moving fin (4) is vertical with the axis of the fuselage (1)；
For foldable propeller component (5), left blade (51A) passes through left blade fold mechanism (52A) in the xy plane
It is rotated counterclockwise, meanwhile, right blade (51B) is revolved clockwise in the xy plane by right blade fold mechanism (52B)
Turn, until left blade (51A), paddle folder (53) and right blade (51B) form "-" type.
The folding wings unmanned plane and its launching technique of cartridge type transmitting provided by the invention have the advantage that
The present invention provides the folding wings unmanned plane and its launching technique of a kind of cartridge type transmitting, has cruising condition aerodynamic characteristic
The features such as good, wound packages state occupies little space, is light-weight, and carrying can be born by individual soldier, is convenient for operation.
Detailed description of the invention
Fig. 1 is structural schematic diagram of the folding wings unmanned plane provided by the invention when patrolling winged task status；
Fig. 2 is the structural schematic diagram of folding wings unmanned plane side in folded state provided by the invention；
Fig. 3 is the structural schematic diagram of folding wings unmanned plane other side in folded state provided by the invention；
Fig. 4 is arrangement schematic diagram of the folding wings unmanned plane provided by the invention in launching tube；
Fig. 5 is after the present invention emits out of cylinder, from folded state to the variant process schematic for patrolling winged task status；
Fig. 6 is each component relative mounting positions schematic diagram in body tail portion of the invention；
Fig. 7 is arrangement schematic diagram of the 1 inside loading space of fuselage of the present invention under an orientation；
Fig. 8 is arrangement schematic diagram of the 1 inside loading space of fuselage of the present invention under another orientation；
Fig. 9 is 2 distribution form schematic diagram of Z-shaped folding wing of the invention；
Figure 10 is 23 axonometric drawing of middle wing panel of Z-shaped folding wing 2 of the present invention；
Figure 11 is 23 top view of middle wing panel of Z-shaped folding wing 2 of the present invention；
Figure 12 is the bottom view of the outer main wing 25A in the right side of Z-shaped folding wing 2 of the present invention；
Figure 13 is Figure 12 along A-A cross-sectional view；
Figure 14 is the bottom view of the outer main wing 25A in the right side of Z-shaped folding wing 2 of the present invention；
Figure 15 is the axonometric drawing of flying tail 3 of the present invention；
Figure 16 is the top view of flying tail 3 of the present invention；
Figure 17 is the bottom view of flying tail 3 of the present invention；
Figure 18 is the axonometric drawing of all moving fin 4 of the present invention；
Figure 19 is the left view of all moving fin 4 of the present invention；
Figure 20 is the schematic diagram of the foldable propeller component 5 of the present invention in a folded configuration；
Figure 21 is the schematic diagram of the foldable propeller component 5 of the present invention in an intermediate state；
Figure 22 is schematic diagram of the foldable propeller component 5 of the present invention in the case where being fully deployed；
Figure 23 is change procedure figure of the foldable propeller component 5 of the present invention by folded state to fully unfolded position；
Figure 24 is that cartridge type of the present invention emits application scenarios schematic diagram；
Figure 25 is airdrop-launched application scenarios schematic diagram of the present invention；
Wherein:
1 fuselage；11 load cabins；12 electrical source of power cabins；13 inertial navigation cabins；14 piggyback pods；15 contraction sections；16 vertical planes；17 is left
Cut flat with inclined-plane；18 right cut flat incline planes；
2Z font folding wing；20A wing centre section drives spring；20B wing centre section mandrel；21 wing centre section fold mechanisms；The left outside main wing folding of 22A
Folded mechanism；The right outer main wing fold mechanism of 22B；Wing panel in 23；The left outside main wing of 24A；The left outside aileron of 24B；The right outer main wing of 25A；25B is right
External aileron；The left outside aileron movement steering engine of 26A；The right external aileron of 26B deflects steering engine；27 right external ailerons deflect servo driving connecting rod；28
Right outer main wing control surface shaft；
The left flying tail of 3A；The right flying tail of 3B；31 right horizontal tail fold mechanisms；32 horizontal tail rotary shafts；33 horizontal tails deflect rudder
Machine；34 horizontal tail control surface shafts；35 horizontal tail control surfaces；36 rotation Ii miters；
4 all moving fins；41 vertical fin fold mechanisms；42 vertical fin rotary shafts；43 vertical fins deflect steering engine；44 vertical fin control surfaces turn
Axis；45 vertical fin control surfaces；46 vertical fin rotation Ii miters；
5 foldable propeller components；The left blade of 51A；The right blade of 51B；The left blade fold mechanism of 52A；The right blade of 52B folds
Mechanism；53 paddles folder；54 drive shafts；
6 launching tubes；Dustproof cover 61；Emit tube stent 62；Cylinder 63；Piston assist device 64；Gas generator 65；Transmitting
Cylinder pedestal 66；
7 folding wings unmanned planes.
Specific embodiment
In order to which the technical problems, technical solutions and beneficial effects solved by the present invention is more clearly understood, below in conjunction with
Accompanying drawings and embodiments, the present invention will be described in further detail.It should be appreciated that specific embodiment described herein only to
It explains the present invention, is not intended to limit the present invention.
In order to overcome the disadvantages of traditional folding wings unmanned plane space utilization rate is low, aerodynamic interference phenomenon is serious.The present invention mentions
For the folding wings unmanned plane and its launching technique of a kind of transmitting of cartridge type, have cruising condition aerodynamic characteristic good, wound packages state occupies
The features such as space is small, light-weight, and carrying can be born by individual soldier, is convenient for operation.
The folding wings unmanned plane of cartridge type transmitting, comprising: folding wings unmanned plane 7 and launching tube 6；In wound packages state, fold
Wing unmanned plane 7 is in completely folded state and is set to the inside of launching tube 6, and such as Fig. 4, as folding wings unmanned plane 7 are set to
The state diagram when inside of launching tube 6；When launching tube 6 emits folding wings unmanned plane 7, folding wings unmanned plane 7 is by from launching tube 6
Pop-up climbs after the variant process gradually spread out and patrols winged task status into what is be fully deployed.It is the present invention with reference to Fig. 1
Structural schematic diagram of the folding wings unmanned plane of offer when patrolling winged task status；Fig. 2 is folding wings unmanned plane provided by the invention
The structural schematic diagram of side in folded state；Fig. 3 is folding wings unmanned plane provided by the invention other side in folded state
Structural schematic diagram.Fig. 5 is to illustrate after the present invention emits out of cylinder from folded state to the variant process for patrolling winged task status
Figure.
The structure of folding wings unmanned plane 7 and launching tube 6 is discussed in detail separately below:
(1) folding wings unmanned plane 7
Folding wings unmanned plane 7 includes fuselage 1, Z-shaped folding wing 2, left flying tail 3A, right flying tail 3B, moves entirely
Vertical fin 4 and foldable propeller component 5.The folding and exhibition of each mechanism are realized by the fold mechanism of connection fuselage 1 and each component
It opens, completes folding wings unmanned plane from wound packages standby mode to the variant process for patrolling winged task status.
(1) fuselage
With reference to Fig. 6 and Fig. 1, fuselage 1 is cylindrical-shaped structure, and the bottom of fuselage 1 cuts flat with to be formed for placing folded Z-shaped
The setting plane of type folding wing 2, to guarantee that the radial full-size of full machine after folding is no more than the diameter of launching tube；Fuselage
The left and right sides of 1 tail portion are shunk, and the contraction section 15 of class truncated cone-shaped is formed；The left and right sides of the end of contraction section 15 be for
Place the setting face of folded foldable propeller component 5；The right side of the front end of contraction section is cut flat with, and is formed for placing folding
The vertical plane 16 of all moving fin 4 of poststack；The upper surface of contraction section 15 forms symmetrical left cut flat incline plane 17 and right cut is flat
The intersecting lens of inclined-plane 18, left cut flat incline plane 17 and right cut flat incline plane 18 is the axis of fuselage 1, to the left from the axis of fuselage, left cut
The height of flat incline plane 17 is gradually lower；To the right from the axis of fuselage, the height of right cut flat incline plane 18 is gradually lower；Left cut flat incline plane
17 is consistent with the bottom surface gradient of left flying tail 3A, for placing folded left flying tail 3A；Right cut flat incline plane 18 with
The bottom surface gradient of right flying tail 3B is consistent, for placing folded right flying tail 3B；That is, when left complete dynamic flat
When tail 3A is folded to left cut flat incline plane 17, the bottom surface of left flying tail 3A is just contacted with the surface of left cut flat incline plane 17；Equally
, when right flying tail 3B is folded to right cut flat incline plane 18, the bottom surface of right flying tail 3B just with right cut flat incline plane 18
Surface contact.Symmetrically cut flat with inclined-plane by setting two, rather than one with the plane for the lower position flush for cutting flat with inclined-plane, can
Increase the space utilization rate of fuselage endpiece, while to dispose folded flying tail, to meet the space ruler of wound packages state
Very little constraint.
Fuselage 1 has been sequentially arranged load cabin 11, power electric with reference to Fig. 7-Fig. 8 using modularized design from head to tail portion
14 4 source cabin 12, inertial navigation cabin 13 and piggyback pod bay sections；Wherein, load cabin 11 completes essence for carrying target seeker and warhead
Really strike task, also optional carrying is scouted, communication equipment is completed to scout and injure assessment, air alert, and it is more to communicate relaying etc.
Item task；Electrical source of power cabin 12 is for the energy supplies equipment such as battery-mounted, and then to foldable propeller component 5, load cabin
11 inner electronic equipments etc. provide required energy；Inertial navigation cabin 13 is inertial navigation unit cabin, is disposed with gyroscope and accelerometer
Etc. equipment；Piggyback pod 14 is disposed with the power-equipment to drive foldable propeller component 5, including driving motor, electronics tune
The equipment such as fast device.
(2) Z-shaped folding wing
Z-shaped folding wing 2 is located at the lower section of fuselage 1 middle part, with reference to Fig. 9, including it is middle wing panel 23, left outside main wing 24A, left outside
Aileron 24B, right outer main wing 25A and right external aileron 25B；Middle wing panel 23, left outside main wing 24A and left outside aileron 24B are three Duan Shengli
Face；Left outside aileron 24B and right external aileron 25B is two control surfaces.
With reference to Figure 10 and Figure 11, middle wing panel 23 is a length and the isometric rectangle wing panel of 1 length of fuselage；Middle wing panel 23
Center passes through the foldable center for being mounted on 1 bottom of fuselage of wing centre section fold mechanism 21；Wherein, wing centre section fold mechanism 21 is side
Shape rotating mechanism, including wing centre section driving spring 20A and wing centre section mandrel 20B, can be used the structures such as torsional spring structure or plane scroll spring
It realizes, passes through the folding and expansion of wing panel 23 in the rotation control of wing centre section fold mechanism 21.
The left side of middle wing panel 23 passes through the left outside main wing 24A of the foldable installation of left outside main wing fold mechanism 22A；Middle wing panel 23
Right side passes through the right outer right outer main wing 25A of the foldable installation of main wing fold mechanism 22B；Left outside main wing 24A is opposite with right outer main wing 25A
It is symmetrical in middle 23 or so face of wing panel；Wherein, left outside main wing 24A and right outer main wing 25A is to be installed on middle 23 bottom outside of wing panel
Rectangle wing panel, length are the half of middle 23 length of wing panel, and chord length is slightly less than the chord length of middle wing panel 23.Left outside main wing fold mechanism
22A and right outer main wing fold mechanism 22B is circular rotating mechanism.Awing, left outside main wing 24A and right outer main wing 25A passes through
Outer main wing fold mechanism is rotated to winged task status is patrolled, and realizes high aspect ratio, high lift-drag ratio cruise；It is left outside under wound packages state
Main wing 24A and right outer main wing 25A are rotated by outer main wing fold mechanism to folded state, realize wound packages transmitting.
When Z-shaped folding wing 2 is in folded state, Z-shaped folding wing 2 is folded into length and 1 length of fuselage etc.
Small "-" type wing that is same, being parallel to 1 axis of fuselage；When Z-shaped folding wing 2, which is in, to patrol under winged task status, Z-shaped folding
It is the length of 2 times of fuselages 1, the spread-eagel type wing perpendicular to fuselage 1 that folded missile wing 2, which is launched into length,；
Left outside main wing 24A is realized with right outer main wing 25A by outer main wing fold mechanism and the connection of middle wing panel 23, and about
Fuselage axisymmetrical.
With reference to Figure 12-Figure 14, right outer main wing 25A is the rectangle wing panel for being mounted on middle 23 bottom outside of wing panel, on edge
Right external aileron 25B is installed in tangential 0.7~1 region；One end of right external aileron 25B passes through outside right outer main wing control surface shaft 28 and the right side
Main wing 25A is rotatably connected；Right external aileron deflection steering engine 26B is installed, right external aileron deflection steering engine 26B is logical on right outer main wing 25A
It crosses right external aileron deflection servo driving connecting rod 27 to connect with right external aileron 25B, and then right external aileron 25B main wing outside the right side is driven to grasp
Vertical face shaft 28 deflects；Left outside main wing 24A is arranged deflectable left outside aileron 24B and for driving left outside aileron 24B to deflect
Left outside aileron movement steering engine 26A；Left outside aileron 24B and right external aileron 25B, the center relative to Z-shaped folding wing 2
Left and right face is symmetrical；
(3) left flying tail and right flying tail
Left flying tail 3A passes through top on the left of the foldable tail portion for being mounted on fuselage 1 of left horizontal tail fold mechanism；It is right complete dynamic
Horizontal tail 3B passes through top on the right side of the foldable tail portion for being mounted on fuselage 1 of right horizontal tail fold mechanism 31；Left flying tail 3A and the right side are complete
There are certain inverted diherdrals by dynamic horizontal tail 3B, and then are conducive to improve the space utilization rate of cylinder interior folding state；
Left flying tail 3A and right flying tail 3B is left and right face symmetrical structure, with reference to Figure 15-Figure 17, only with right complete dynamic flat
For tail 3B, its structure is introduced: inclined for right flying tail 3B, including right horizontal tail fold mechanism 31, horizontal tail rotary shaft 32, horizontal tail
It comes about the peaceful tail rotation Ii miter 36 of machine 33, horizontal tail control surface shaft 34, horizontal tail control surface 35；Right horizontal tail fold mechanism 31 passes through
Horizontal tail rotary shaft 32 is connect with fuselage 1, for controlling the folding and expansion of right flying tail 3B；Horizontal tail rotation Ii miter 36 is used for
Control the rotation angle of right flying tail 3B；Horizontal tail control surface 35 deflects steering engine 33 by horizontal tail control surface shaft 34 and horizontal tail and connects
It connects, horizontal tail deflection steering engine 33 is installed on right horizontal tail fold mechanism 31, controls horizontal tail control surface by horizontal tail control surface shaft 34
35 deflection.
(4) all moving fin
In the accompanying drawings, all moving fin 4 is arranged one, passes through the foldable rear for being mounted on fuselage 1 of vertical fin fold mechanism 41
Right side, also, all moving fin 4 is located at the front of right flying tail 3B；It, can also when all moving fin 4 is arranged one in practical application
With the foldable left rear side for being mounted on fuselage 1；All moving fin 4 also can be set, and be located at the left side and the right side at 1 rear of fuselage
Side；
With reference to Figure 18-Figure 19, all moving fin 4 includes vertical fin fold mechanism 41, vertical fin rotary shaft 42, vertical fin deflection steering engine
43, vertical fin control surface shaft 44, vertical fin control surface 45 and vertical fin rotation Ii miter 46；Vertical fin fold mechanism 41 is rotated by vertical fin
Axis 42 is connect with fuselage 1, for controlling the folding and expansion of all moving fin 4；Vertical fin deflection steering engine 43 is mounted on vertical fin folding machine
On structure 41, the deflection of vertical fin control surface 45 is controlled by vertical fin control surface shaft 44；Vertical fin rotation Ii miter 46 is complete for controlling
The rotation angle of dynamic vertical fin 4.
(5) foldable propeller component
With reference to Figure 20-Figure 23, foldable propeller component 5 is installed in the middle part of the rear end face of fuselage 1, including paddle folder 53 and
It is symmetrically arranged on the left blade 51A and right blade 51B of 53 left and right sides of paddle folder；Left blade 51A and right blade 51B is antisymmetry knot
Structure；Wherein, paddle folder 53 is a bar part, and paddle folder 53 is connect by drive shaft 54 with the driving motor inside fuselage 1, driving electricity
Machine drives 53 rotation of paddle folder by drive shaft 54；Left blade 51A is mounted on paddle folder 53 by the way that left blade fold mechanism 52A is foldable
Left end；Right blade 51B passes through the foldable right end for being mounted on paddle folder 53 of right blade fold mechanism 52B.Wherein, left blade folds
Mechanism 52A and right blade fold mechanism 52B is all made of the realization of blade shaft, and blade shaft is a parts of bearings, and blade can be made real
Now rotated freely around axis.Under wound packages state, left blade 51A and right blade 51B folding are placed on 1 tail portion side of fuselage to meet
Bulk constraint can unscrew automatically in the case where motor is rotated and driven around respective blade shaft after transmitting or air-drop.
It is emphasized that for this application involves the various fold mechanisms arrived, including wing centre section fold mechanism, left outside main wing
Fold mechanism, right outer main wing fold mechanism, left horizontal tail fold mechanism, right horizontal tail fold mechanism, vertical fin fold mechanism, left blade folding
Folded mechanism and right blade fold mechanism can be realized using any type of fold mechanism in the prior art, as long as can be realized
Under the action of each fold mechanism, associated components can be rotated around fuselage, thus realize the folding of associated components, this Shen
Please the concrete form of the fold mechanism of use is not intended to limit.
(2) launching tube
With reference to Fig. 4, launching tube 6 includes dustproof cover 61, transmitting tube stent 62, cylinder 63, piston assist device 64, combustion gas hair
Raw device 65 and launching tube pedestal 66；
Dustproof cover 61 is installed on the head of cylinder 63, dustproof cover 61 be a rubbery plug lid, prevent dust gravel etc. from entering bullet
Cylinder 63 influences transmitting；The external installation transmitting tube stent 62 of cylinder 63, emits the foldable folding and unfolding of tube stent 62, so that individual soldier bears
Transport；The tail portion of cylinder 63 is installed by launching tube pedestal 66；Launching tube pedestal 66 installs gas generator 65 above；Gas generator
65 outlet port installs piston assist device 64；Folding wings unmanned plane 7 is set before piston assist device 64.
About 60 ° of the transmitting inclination angle (gun barrel axis angle with horizontal plane) of launching tube 6 has structure simple, and weight is small, individual soldier
The features such as can operating.Launching tube 6 pushes piston boosting to fill by the high pressure gas that fuel combustion in gas generator 65 generates
It sets 64 to pop up folding wings unmanned plane 7 at a high speed, completes transmitting.
The present invention also provides a kind of launching techniques of the folding wings unmanned plane of cartridge type transmitting, comprising the following steps:
Step 1, folding wings unmanned plane 7 is in completely folded state, and is placed in launching tube 6；
Wherein, folding wings unmanned plane 7 is in completely folded state, refers to:
For Z-shaped folding wing 2, left outside main wing 24A is folding into middle wing panel 23 just around left outside main wing fold mechanism 22A
Lower section, right outer main wing 25A main wing fold mechanism 22B outside the right side fold into the underface of middle wing panel 23, and middle wing panel 23 is rolled over around wing centre section
Folded mechanism 21 rotates to the underface of fuselage 1, at this point, Z-shaped folding wing 2 is folded into length and 1 length of fuselage is equivalent, parallel
In the small "-" type wing of 1 axis of fuselage；
For left flying tail 3A and right flying tail 3B, left flying tail 3A is folded to machine by left horizontal tail fold mechanism
The left cut flat incline plane 17 of body 1；Right flying tail 3B is folded to the right cut flat incline plane 18 of fuselage 1 by right horizontal tail fold mechanism 31；
For all moving fin 4, all moving fin 4 is folded to the vertical plane 16 of 1 right side of fuselage by vertical fin fold mechanism 41；
For foldable propeller component 5, left blade 51A is folded to the tail of fuselage 1 by left blade fold mechanism 52A
Portion left side；Its right blade 51B is folded to the tail portion right side of fuselage 1 by right blade fold mechanism 52B；
By carrying out to fuselage 1, bottom is cut flat with, tail portion is shunk, left cut flat incline plane 17 is cut into tail portion upper surface and right cut is flat oblique
The design in face 18, after folding wings unmanned plane 7 is in completely folded state, radial full-size is no more than the straight of launching tube 6
Therefore diameter, the length of of length no more than launching tube 6 can be accommodated in completely in the cylinder of launching tube 6；
Step 2, after individual soldier bears the arrival of launching tube 6 launch site for being placed with folding wings unmanned plane 7, by required transmitting
Angle installs launching tube 6；
Step 3, start the gas generator 65 of launching tube 6, gas generator 65 generates high pressure gas, passes through piston boosting
Device 64 pops up folding wings unmanned plane 7 from launching tube 6；
Step 4, folding wings unmanned plane 7 after the variant process gradually spread out, climbs after popping up in launching tube 6
Into the winged task status of patrolling being fully deployed, emission process is completed；
Specifically, with the axial for X-axis of fuselage 1, Z axis is in the plane of symmetry of Z-shaped folding wing 2, perpendicular to X-axis, with
The direction vertical with X-Z plane is Y-axis；
After folding wings unmanned plane 7 is popped up from launching tube 6, under the action of each fold mechanism, from rugosity
State is gradually spread out, until forming fully unfolded position, variant process are as follows:
For Z-shaped folding wing 2, wherein wing panel 23 is revolved clockwise in the xy plane by wing centre section fold mechanism 21
Turn, meanwhile, left outside main wing 24A is rotated counterclockwise in the xy plane by left outside main wing fold mechanism 22A, right outer main wing
25A is rotated counterclockwise in the xy plane by right outer main wing fold mechanism 22B, by left outside main wing 24A, 23 and of middle wing panel
After right outer main wing 25A forms the intermediate state of Z-shaped, middle wing panel 23, left outside main wing 24A and right outer main wing 25A continue to rotate, directly
To middle wing panel 23 rotates to the position vertical with fuselage 1, left outside main wing 24A rotates to the position conllinear with middle wing panel 23, right outer
Until main wing 25A rotates to the position conllinear with middle wing panel 23, it is 2 times of fuselages 1 that Z-shaped folding wing 2, which is launched into length, at this time
Length, the spread-eagel type wing perpendicular to fuselage 1；
For left flying tail 3A and right flying tail 3B, left flying tail 3A is by left horizontal tail fold mechanism in X/Y plane
It is middle to be rotated counterclockwise, until the axis of left flying tail 3A is vertical with the axis of fuselage 1；Meanwhile right flying tail
3B is rotated clockwise in the xy plane by right horizontal tail fold mechanism 31, until the axis and fuselage 1 of right flying tail 3B
Axis it is vertical until；
For all moving fin 4, all moving fin 4 is rotated clockwise in XZ plane by vertical fin fold mechanism 41, directly
Until the axis of all moving fin 4 is vertical with the axis of fuselage 1；
For foldable propeller component 5, left blade 51A is carried out inverse in the xy plane by left blade fold mechanism 52A
Hour hands rotation, meanwhile, right blade 51B is rotated clockwise in the xy plane by right blade fold mechanism 52B, until left paddle
Until leaf 51A, paddle press from both sides 53 and right blade 51B formation "-" type.
In practical application, Figure 24 is that cartridge type of the present invention emits application scenarios schematic diagram, and folding wings unmanned plane 7 can be placed in hair
In shooting cylinder 6, via individual soldier bear it is interspersed penetrate into launch site, launching tube 6 is installed by ease of Use, starts combustion gas
Device 65 is popped up folding wings unmanned plane 7 using high pressure gas from launching tube 6.Folding wings unmanned plane 7 can lead to rapidly after pop-up
It crosses fold mechanism, completes from wound packages state to patrolling the variant process of winged task status, and climb into winged task status is patrolled, be unfolded
The tasks such as scouting, search, precision strike.
Folding wings unmanned plane 7 can also pass through aerial carrying platform other than realizing wound packages transmitting using launching tube 6
It carries and realizes airdrop-launched.Figure 25 is airdrop-launched application scenarios schematic diagram of the present invention, and folding wings unmanned plane 7 is in a folded configuration
Occupied space is minimum, can realize that larger amt carries transport by carriage by air platform, when aerial carrying platform reaches target
After launching place, it can disposably discharge a frame or multi rack folding wings unmanned plane 7 goes to execution task.Folding wings unmanned plane 7 is logical
It crosses variant and enters and patrol winged task status, composition single rack is multiple batches of or cluster formation attack pattern, to enhance folding wings unmanned plane 7
Fighting efficiency, preferably complete to tasks such as air-to-ground scouting, search, precision strikes.
The folding wings unmanned plane that one kind provided by the invention can be emitted and be dropped with cartridge type, is controlled by rotary folding mechanism
The folding and expansion of missile wing and control surface processed realize folding wings unmanned plane wound packages folded state and patrol quickly cutting for winged task status
It changes, has structure simple, light-weight, the stronger feature of engineering realizability.Meanwhile by the present invention in that with having in rugosity
It occupies little space under state and Z-shaped folding wing the features such as wing area is big in the deployed state, aspect ratio is big, is effectively promoted
Space utilization rate of the invention and in the aeroperformance for patrolling winged task status.
The above is only a preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, various improvements and modifications may be made without departing from the principle of the present invention, these improvements and modifications are also answered
Depending on protection scope of the present invention.
Claims (9)
1. a kind of folding wings unmanned plane of cartridge type transmitting characterized by comprising folding wings unmanned plane (7) and launching tube (6)；
In wound packages state, the folding wings unmanned plane (7) is in completely folded state and is set to the inside of the launching tube (6)；
When the launching tube (6) emits folding wings unmanned plane (7), the folding wings unmanned plane (7) is by from the launching tube (6)
Pop-up climbs after the variant process gradually spread out and patrols winged task status into what is be fully deployed；
Wherein, the folding wings unmanned plane (7) include fuselage (1), it is Z-shaped folding wing (2), left flying tail (3A), right complete
Dynamic horizontal tail (3B), all moving fin (4) and foldable propeller component (5)；
The fuselage (1) is cylindrical-shaped structure, and the bottom of the fuselage (1) cuts flat with to be formed for placing the folded Z-shaped
The setting plane of type folding wing (2)；The left and right sides of fuselage (1) tail portion are shunk, and the contraction section of class truncated cone-shaped is formed
(15)；The left and right sides of the end of the contraction section (15) are for placing the folded foldable propeller component
(5) setting face；The right side of the front end of the contraction section is cut flat with, and is formed for placing the folded all moving fin (4)
Vertical plane (16)；The upper surface of the contraction section (15) forms symmetrical left cut flat incline plane (17) and right cut flat incline plane
(18), the left cut flat incline plane (17) is for placing the folded left flying tail (3A)；The right cut flat incline plane (18)
For placing the folded right flying tail (3B)；
The Z-shaped folding wing (2) includes middle wing panel (23), left outside main wing (24A), the right outer main wing of left outside aileron (24B)
(25A) and right external aileron (25B)；Described in the center of the middle wing panel (23) is mounted on by the way that wing centre section fold mechanism (21) are foldable
The center of fuselage (1) bottom；The left side of the middle wing panel (23) passes through the foldable installation of left outside main wing fold mechanism (22A)
The left outside main wing (24A)；The right side of the middle wing panel (23) passes through described in the foldable installation of right outer main wing fold mechanism (22B)
Right outer main wing (25A)；The left outside main wing (24A) and the outer main wing in the right side (25A) are relative to middle wing panel (23) the left and right face
Symmetrically；When the Z-shaped folding wing (2) is in folded state, the Z-shaped folding wing (2) is folded into length and institute
State the small "-" type wing that fuselage (1) length is equivalent, is parallel to the fuselage (1) axis；When the Z-shaped folding wing (2)
In when patrolling under winged task status, the Z-shaped folding wing (2) be launched into the length that length is 2 times of fuselages (1), perpendicular to
The spread-eagel type wing of fuselage (1)；
The outer main wing in the right side (25A) is installing the right external aileron (25B) along tangential 0.7~1 region；The right external aileron
The one end of (25B) is rotatably connected by right outer main wing control surface shaft (28) with the outer main wing in the right side (25A)；It is described right outer main
Right external aileron deflection steering engine (26B) is installed, right external aileron deflection steering engine (26B) is deflected by right external aileron on the wing (25A)
Servo driving connecting rod (27) is connect with the right external aileron (25B), and then the right external aileron (25B) main wing outside the right side is driven to grasp
Vertical face shaft (28) deflection；The left outside main wing (24A) is arranged the deflectable left outside aileron (24B) and for driving
The left outside aileron movement steering engine (26A) of left outside aileron (24B) deflection；The left outside aileron (24B) and the right external aileron
(25B), center relative to the Z-shaped folding wing (2) or so face are symmetrical；
The left flying tail (3A) passes through on the foldable tail portion left side for being mounted on the fuselage (1) of left horizontal tail fold mechanism
Side；The right flying tail (3B) passes through the foldable tail portion right side for being mounted on the fuselage (1) of right horizontal tail fold mechanism (31)
Top, there are certain inverted diherdrals for the left flying tail (3A) and the right flying tail (3B), and then are conducive to improve cylinder
The space utilization rate of interior folding state；
The all moving fin (4) passes through vertical fin fold mechanism (41) foldable rear for being mounted on the fuselage (1), also, institute
State the front that all moving fin (4) are located at the right flying tail (3B)；Wherein, the setting quantity of all moving fin (4) is one
It is a or two；When all moving fin (4) are arranged one, all moving fin (4) is located at the left side at the fuselage (1) rear
Or right side；When all moving fin (4) are arranged two, all moving fin (4) is located at the left side at the fuselage (1) rear
Side and right side；
The foldable propeller component (5) is installed in the middle part of the rear end face of the fuselage (1), including paddle folder (53) and symmetrical
The left blade (51A) and right blade (51B) being installed at left and right sides of the paddle folder (53)；The left blade (51A) and the right side
Blade (51B) is antisymmetry structure；Wherein, the paddle folder (53) driving internal by drive shaft (54) and the fuselage (1)
Motor connection, the driving motor drive the paddle folder (53) to rotate by the drive shaft (54)；The left blade (51A) is logical
Cross the foldable left end for being mounted on the paddle folder (53) of left blade fold mechanism (52A)；The right blade (51B) passes through right blade
The foldable right end for being mounted on the paddle folder (53) of fold mechanism (52B).
2. the folding wings unmanned plane of cartridge type transmitting according to claim 1, which is characterized in that the fuselage (1) uses mould
Blockization design, has been sequentially arranged load cabin (11), electrical source of power cabin (12), inertial navigation cabin (13) and piggyback pod from head to tail portion
(14)；Wherein, the load cabin (11) completes precision strike task for carrying target seeker and warhead, also may be selected to carry
It scouts, communication equipment is completed to scout and injures assessment, air alert, communication relay task；The electrical source of power cabin (12) is used for
Energy supply equipment is carried, and then provides institute to the foldable propeller component (5), the load cabin (11) inner electronic equipment
The energy needed；The inertial navigation cabin (13) is inertial navigation unit cabin, is disposed with gyroscope and accelerometer equipment；The piggyback pod
(14) it is disposed with the power-equipment to drive the foldable propeller component (5).
3. the folding wings unmanned plane of cartridge type transmitting according to claim 1, which is characterized in that the middle wing panel (23) is one
A length and the isometric rectangle wing panel of the fuselage (1) length；The wing centre section fold mechanism (21) is rectangular rotating mechanism, including
Wing centre section drives spring (20A) and wing centre section mandrel (20B).
4. the folding wings unmanned plane of cartridge type transmitting according to claim 1, which is characterized in that the left outside main wing (24A)
It is the rectangle wing panel for being installed on middle wing panel (23) bottom outside with the outer main wing in the right side (25A), length is the wing centre section
The half of section (23) length, chord length are less than the chord length of the middle wing panel (23).
5. the folding wings unmanned plane of cartridge type transmitting according to claim 1, which is characterized in that the left outside main wing folding machine
The outer main wing fold mechanism (22B) of structure (22A) and the right side is circular rotating mechanism.
6. the folding wings unmanned plane of cartridge type transmitting according to claim 1, which is characterized in that the left flying tail (3A)
It is left and right face symmetrical structure with the right flying tail (3B), for the right flying tail (3B), including right horizontal tail folding machine
Structure (31), horizontal tail rotary shaft (32), horizontal tail deflection steering engine (33), horizontal tail control surface shaft (34), horizontal tail control surface (35) peace
Tail rotation Ii miter (36)；The right horizontal tail fold mechanism (31) is connected by the horizontal tail rotary shaft (32) and the fuselage (1)
It connects, for controlling the folding and expansion of the right flying tail (3B)；The horizontal tail rotation Ii miter (36) is described for controlling
The rotation angle of right flying tail (3B)；The horizontal tail control surface (35) is put down by the horizontal tail control surface shaft (34) with described
Tail deflects steering engine (33) connection, and horizontal tail deflection steering engine (33) is installed on the right horizontal tail fold mechanism (31), passes through institute
State the deflection that horizontal tail control surface shaft (34) control the horizontal tail control surface (35).
7. the folding wings unmanned plane of cartridge type transmitting according to claim 1, which is characterized in that all moving fin (4) packet
Include vertical fin fold mechanism (41), vertical fin rotary shaft (42), vertical fin deflection steering engine (43), vertical fin control surface shaft (44), vertical fin behaviour
Vertical face (45) and vertical fin rotation Ii miter (46)；The vertical fin fold mechanism (41) by the vertical fin rotary shaft (42) with it is described
Fuselage (1) connection, for controlling the folding and expansion of all moving fin (4)；Vertical fin deflection steering engine (43) is mounted on institute
It states on vertical fin fold mechanism (41), the deflection of the vertical fin control surface (45) is controlled by the vertical fin control surface shaft (44)；
The vertical fin rotation Ii miter (46) is used to control the rotation angle of all moving fin (4).
8. the folding wings unmanned plane of cartridge type according to claim 1 transmitting, which is characterized in that the launching tube (6) includes
Dustproof cover (61), transmitting tube stent (62), cylinder (63), piston assist device (64), gas generator (65) and launching tube
Pedestal (66)；
The head of the cylinder (63) is installed by the dustproof cover (61)；The external of the cylinder (63) installs the transmitting tube stent
(62)；The tail portion of the cylinder (63) is installed by the launching tube pedestal (66)；Described in the launching tube pedestal (66) is installed above
Gas generator (65)；The outlet port of the gas generator (65) installs the piston assist device (64)；The piston
The folding wings unmanned plane (7) is set before assist device (64).
9. a kind of launching technique of the folding wings unmanned plane of the described in any item cartridge type transmittings of claim 1-8, which is characterized in that
The following steps are included:
Step 1, folding wings unmanned plane (7) is in completely folded state, and is placed in launching tube (6)；
Wherein, folding wings unmanned plane (7) is in completely folded state, refers to:
For Z-shaped folding wing (2), left outside main wing (24A) folds into middle wing panel (23) around left outside main wing fold mechanism (22A)
Underface, right outer main wing (25A) main wing fold mechanism (22B) outside the right side folds into the underface of middle wing panel (23), middle wing panel
(23) underface of fuselage (1) is rotated to around wing centre section fold mechanism (21), at this point, Z-shaped folding wing (2) be folded into length with
Fuselage (1) length is equivalent, is parallel to the small "-" type wing of the fuselage (1) axis；
For left flying tail (3A) and right flying tail (3B), the left flying tail (3A) is rolled over by left horizontal tail fold mechanism
It is laminated on the left cut flat incline plane (17) of the fuselage (1)；The right flying tail (3B) is folded by right horizontal tail fold mechanism (31)
In the right cut flat incline plane (18) of the fuselage (1)；
For all moving fin (4), all moving fin (4) is folded on the right side of the fuselage (1) by vertical fin fold mechanism (41)
The vertical plane (16) in face；
For foldable propeller component (5), left blade (51A) is folded to the machine by left blade fold mechanism (52A)
The tail portion left side of body (1)；Its right blade (51B) is folded to the tail portion of the fuselage (1) by right blade fold mechanism (52B)
Right side；
By carrying out to the fuselage (1), bottom is cut flat with, tail portion is shunk, left cut flat incline plane (17) and right cut are cut into tail portion upper surface
The design of flat incline plane (18), after the folding wings unmanned plane (7) is in completely folded state, radial full-size is no more than
The length of the diameter of the launching tube (6), of length no more than launching tube (6) therefore can be accommodated in the launching tube completely
(6) in cylinder；
Step 2, after individual soldier bears launching tube (6) the arrival launch site for being placed with the folding wings unmanned plane (7), by required
Launch angle installs the launching tube (6)；
Step 3, start the gas generator (65) of launching tube (6), gas generator (65) generates high pressure gas, helps by piston
Pushing device (64) pop-up from launching tube (6) by the folding wings unmanned plane (7)；
Step 4, the folding wings unmanned plane (7) is after the pop-up from the launching tube (6), by the variant process gradually spread out
Afterwards, it climbs into the winged task status of patrolling being fully deployed, completes emission process；
Specifically, using the axial direction of fuselage (1) as X-axis, Z axis is in the plane of symmetry of Z-shaped folding wing (2), perpendicular to X-axis, with
The direction vertical with X-Z plane is Y-axis；
After folding wings unmanned plane (7) is by the pop-up from the launching tube (6), under the action of each fold mechanism, from folding
State is gradually spread out, until forming fully unfolded position, variant process are as follows:
For Z-shaped folding wing (2), wherein wing panel (23) is carried out clockwise in the xy plane by wing centre section fold mechanism (21)
Rotation, meanwhile, left outside main wing (24A) is rotated counterclockwise in the xy plane by left outside main wing fold mechanism (22A), right outer
Main wing (25A) is rotated counterclockwise in the xy plane by right outer main wing fold mechanism (22B), by left outside main wing (24A),
After middle wing panel (23) and right outer main wing (25A) form the intermediate state of Z-shaped, outside middle wing panel (23), left outside main wing (24A) and the right side
Main wing (25A) continues to rotate, until middle wing panel (23) rotates to the position vertical with fuselage (1), left outside main wing (24A) rotates to
Until conllinear position, right outer main wing (25A) rotate to the position conllinear with middle wing panel (23) with middle wing panel (23), Z-shaped at this time
It is the length of 2 times of fuselages (1), the spread-eagel type wing perpendicular to fuselage (1) that type folding wing (2), which is launched into length,；
For left flying tail (3A) and right flying tail (3B), left flying tail (3A) is flat in XY by left horizontal tail fold mechanism
It is rotated counterclockwise in face, until the axis of left flying tail (3A) is vertical with the axis of the fuselage (1)；Meanwhile
Right flying tail (3B) is rotated clockwise in the xy plane by right horizontal tail fold mechanism (31), until right flying tail
Until the axis of (3B) is vertical with the axis of the fuselage (1)；
For all moving fin (4), all moving fin (4) is rotated clockwise in XZ plane by vertical fin fold mechanism (41),
Until the axis of all moving fin (4) is vertical with the axis of the fuselage (1)；
For foldable propeller component (5), left blade (51A) is carried out in the xy plane by left blade fold mechanism (52A)
Rotation counterclockwise, meanwhile, right blade (51B) is rotated clockwise in the xy plane by right blade fold mechanism (52B), directly
Until left blade (51A), paddle folder (53) and right blade (51B) form "-" type.
Priority Applications (2)
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| CN201811601135.8A CN109436296B (en) | 2018-12-26 | 2018-12-26 | Barrel-type launching folding wing unmanned aerial vehicle and launching method thereof |
| PCT/CN2018/124452 WO2020133089A1 (en) | 2018-12-26 | 2018-12-27 | Barrel-launched folding-wing unmanned aerial vehicle and launch method therefor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811601135.8A CN109436296B (en) | 2018-12-26 | 2018-12-26 | Barrel-type launching folding wing unmanned aerial vehicle and launching method thereof |
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| CN109436296B CN109436296B (en) | 2024-02-13 |
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| WO (1) | WO2020133089A1 (en) |
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| CN109436296B (en) | 2024-02-13 |
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