CN101314409B - Swallow type inclined rotation rotorcraft - Google Patents
Swallow type inclined rotation rotorcraft Download PDFInfo
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- CN101314409B CN101314409B CN2008100699538A CN200810069953A CN101314409B CN 101314409 B CN101314409 B CN 101314409B CN 2008100699538 A CN2008100699538 A CN 2008100699538A CN 200810069953 A CN200810069953 A CN 200810069953A CN 101314409 B CN101314409 B CN 101314409B
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Abstract
The invention relates to a swallow-type tilt-rotor aircraft, which integrates a helicopter with a fixed-wing aircraft. With external shapes changed, three aircraft types, namely the helicopter, the fixed-wing aircraft and the tilt-rotor aircraft, can be used for flying independently. The aircraft adopts a swallow-type aerodynamic configuration and has a geometrical shape similar to a swallow among flyers. The aircraft is provided with a hydraulic staypole folding wing; an outer segment wing and a middle segment wing are in hinged connection and can be folded downwards and stretched upwards; a coaxial tilt-rotor system is arranged on a wing beam structure of the middle segment wing, forming a horizontal-type double-rotor configuration; two pairs of rotors can rotate to and fro between a vertical position and a horizontal position; when the rotors are positioned in the vertical position and the outer segment wing is folded downwards, the aircraft is a helicopter; when the rotors are positioned in the horizontal position and the outer segment wing is stretched upwards, the aircraft becomes a fixed-wing aircraft. The aircraft is provided with a combined-type engine system consisting of a plurality of engines and a common axis, thereby having reliable safety performance. The aircraft is simple in structure, good in performance and wide in practical range.
Description
Affiliated technical field
The present invention relates to a kind of swallow type inclined rotation rotorcraft.
Background technology
In existing tiltrotor, the V-22 of the U.S. " osprey " tiltrotor is a comparatively ripe example of technology.Accompanying drawing 26 is V-22 " osprey " tiltrotor three-view drawing and power, drive system structure sketch (being published on 10 phases of " aviation knowledge " calendar year 2001).With reference to the accompanying drawings, this existing tiltrotor is commented.
The total arrangement of V-22 " osprey " tiltrotor is: at the wing wing tip place that is similar to fixed wing aircraft, respectively adorn the engine nacelle of a subband rotor.Rotor and engine nacelle can come back rotation between level attitude and upright position.When rotor was in vertical position, tiltrotor just was equivalent to laterally disposed dual rotor type helicopter; When rotor turns forward when forwarding level attitude to, tiltrotor has become fixed wing aircraft again.This tiltrotor both can be carried out VTOL, can after lift-off, forward rotor to level attitude forward again, as fixed wing aircraft, carried out the high speed long-distance flight.But still there is following weak point technically in above-mentioned this existing tiltrotor: the one, and the engine nacelle rotor structure is heavy and complicated, and operating difficulty is very big; Two is that two driving engines work alone separately, and it is equal fully that its rotating speed and horsepower output are difficult to reach, and particularly in the VTOL process, wherein driving engine has fault just can make the body lack of equilibrium slightly and causes serious consequence; The 3rd, aerodynamic arrangement is not ideal enough, as adopting the straight wing at no sweepback angle, is unfavorable for improving horizontal stability, and aspect ratio and taper ratio are little, is unfavorable for improving 1ift-drag ratio and improves maneuvering performance.Though this existing tiltrotor can be flown as fixed wing aircraft; But low, the poor stability of lift efficient; Technical indexs such as its flying speed and maneuvering performance all can't be compared with modern fixed wing aircraft; Therefore usage range is very limited, generally can only be as the vehicle of transport plane and so on.
Summary of the invention
The present invention mainly is the problems referred to above that exist in the prior art in order to solve; Provide a kind of performance simple in structure good swallow type inclined rotation rotorcraft; This tiltrotor combines helicopter and fixed wing aircraft together, can independently fly with helicopter, fixed wing aircraft and three kinds of types of tiltrotor through changing external shape.The technical scheme that is adopted is: adopt swallow formula aerodynamic arrangement, its geometric configuration is similar with the swallow in the flying bird.Fluid pressure type strut folded wing is set, and outer section wing is connected with stage casing wing hinge, the folding downwards and upwards stretching, extension of section wing outside the fluid pressure type strut is handled.Coaxial type tilting rotor system is installed on the spar structure of stage casing wing; Constitute cross-arranging type bispin wing layout; Two secondary rotors can come back rotation between upright position and level attitude, when rotor be in vertical position, outside section wing when folding downwards, be exactly a helicopter; When rotor be horizontal, outside a section wing when upwards stretching, become a fixed wing aircraft again.The composite engine system that configuration is made up of many driving engines and common axis is for this swallow type inclined rotation rotorcraft provides safe and reliable engine installation.
Beneficial effect
Compared with prior art, the present invention adopts technique scheme to have following beneficial effect:
1, the swallow formula aerodynamic arrangement of the present invention's employing, each item geometric parameter of wing, horizontal tail and vertical tail can both satisfy the performance requriements of fixed wing aircraft, can give full play to the advantage of fixed wing aircraft.
2, the present invention adopts collapsible outer section wing, with helicopter flight the time, is in downward folding position, has avoided that gas washing flows the piping and druming to top airfoil under the rotor, helps improving lift efficient, the space that has also dwindled landing and parked.
3, the coaxial type tilting rotor system that adopts of the present invention, simple in structure, weight is light, mechanical efficiency improves relatively, the positive and negative oar configuration of two secondary rotors, rotating speed equates that in the opposite direction, equilibrium of torques makes body remain state of equilibrium awing.
4, the composite engine system that adopts of the present invention except that satisfying the required maximum power of flight, also leaves enough power more than needed, even wherein one or two driving engines break down, even dead stop, this tiltrotor still can normal flight.Secondly, this engine system does not receive the restriction of single engine stand number under the condition that installing space allows, can realize that puffer assembles the target of big aircraft.
5, deformation performance of the present invention is good; Available helicopter, fixed wing aircraft and three kinds of types of tiltrotor independently fly; Therefore usage range is wide, both can bear various civilian aerial missions, can in military domain, with machine, carrier-borne aircraft, transport plane and unmanned plane etc. flying platform be provided for alert again.
Description of drawings
Fig. 1 is a three-view drawing of the present invention.Among the figure
Front elevation is the shape that becomes fixed wing aircraft.Lateral plan is the shape that becomes helicopter.
Birds-eye view is the shape that becomes fixed wing aircraft.
Fig. 2 is wing of the present invention and horizontal tail geometric configuration figure.Among the figure:
S: wing area L: wing is always opened up long L
0: wing exhibition in stage casing is long
b
0: wing root chord length b
1: wing tip chord length X: outer section leading edge of a wing sweepback angle
S
H: horizontal tail area L
H: horizontal tail arm of force b
A: the wing mean aerodynamic chord
L
1: the long b of horizontal tail exhibition
2: horizontal tail wing root chord length b
3: horizontal tail wing tip chord length
X
1: horizontal tail leading edge sweep X
2: horizontal tail trailing edge fork angle
Fig. 3 is the Airfoil figure that the present invention selects for use, among the figure:
B: aerofoil profile chord length f: maximum camber C: maximum ga(u)ge
X
f: the X value Xc of maximum camber: the X value of maximum ga(u)ge
Fig. 4 is vertical tail geometric configuration figure of the present invention.Among the figure:
S
V: tail surface amasss L
V: tail force arm b
0: vertical tail wing root chord length
b
1: vertical tail wing tip chord length L
2: the long X of tail exhibition
0: the vertical tail leading edge sweep
S
E: rudder area
Fig. 5 is a coaxial type tilting rotor system construction drawing of the present invention.Among the figure
1, rotor head fairing 2, rotor hub 3, tapered roller bearing
4, bearing installation lid 5, rotor pillar 6, rotor shaft
7, rotor blade 8, bearing dead ring 9, plain bearing housing
10, deep groove ball bearing 11, No. two bearing installation lids 12, driving chain wheel
13, coupler 14, driving chain 15, rocking arm verts
16, spar structure 17, transmission shaft 18, sleeve verts
19, conical gear group 20, right angle pipe fitting joint 23, hinge
92, bearing installation plate
Fig. 6 is a fluid pressure type strut folded wing sketch of the present invention.Among the figure,
22, outer section wing 23, hinge 24, fuselage strut joint
26 outer section wing strut joints 56, fluid pressure type strut 85, stage casing wing
Fig. 7 is a general arrangement of the present invention.Among the figure,
27, driving compartment 28, power cabin 29, engine inlets
30, vert groove 32, the left-handed wing of navigation light 31, rotor
33, tilting rotor system 34, flap actuator 35, wing flap
36, the dextrorotation wing 37, pipeline box 23, interlinkage
39, vert pressurized strut 40, the exhaust pipe of engine 41, yaw rudder pressurized strut
42, yaw rudder Rocker arm 43, yaw rudder rotating shaft 44, collision avoidance light
45, yaw rudder 46, flying tail 47, horizontal tail rocking arm
48, horizontal tail pressurized strut 49, engine exhaust port 50, fuselage main framing
51, deck store 22, outer section wing 53, aileron pressurized strut
54, main landing gear 55, aileron 56, fluid pressure type strut
57, navigation light 58, main cabin 59, hatch door
60, nose-gear 61, battery pack 62, landing lights
63, avionics equipment 64, pitot
Fig. 8 is fuselage of the present invention and vertical tail constructional drawing.Among the figure,
65, nose-ring interface 66, driving compartment interface 67, fuselage bulkhead
68, engine ceiling board 69, wing interface 70, fuselage are put the beams in place
71, stringer 72, deck store interface 73, tail interface
74, floor 75, stringer 76, spar
77, yaw rudder covering 78, covering 79, fuselage central sill
80, fuselage underbeam 81, main cabin base plate 82, pipeline passway
83, equipment ceiling board 84, driving compartment base plate
Fig. 9 is wing structure figure of the present invention.Among the figure
5, rotor pillar 35, wing flap 86, top airfoil stringer
9, plain bearing 16, spar 87, rib
18, vert sleeve 37, pipeline box 88, cable
89, hydraulic hose 55, aileron 22, outer section wing
23, hinge 85, stage casing wing 90, lower aerofoil stringer
91, wing joint 92, bearing installation plate 93, gear case cover
94, covering
Figure 10 is a folded wing hinge arrangement enlarged drawing of the present invention.Among the figure
95, spar flange 96, spar web 951, spar flange
961, spar web 97, hinge tongue-and-groove 98, bearing pin
99, hinge tenon
Figure 11 is a flying tail constructional drawing of the present invention.Among the figure
100, horizontal tail rocking arm 101, rotating shaft 102, horizontal tail rib
103, spar framework 104 lower aerofoil stringers 105, top airfoil stringer
106, covering 107, horizontal tail carriage
Figure 12 is the framework type landing gear structure figure that the present invention adopts.Among the figure
(A) nose-gear (B) main landing gear 108, damper leg
109, strut 110, wheel
Figure 13 is a composite engine system schematic of the present invention.Among the figure
111, driving chain wheel 112, gross horsepower output chain gear 113, driving chain
114, driving engine 115, No. two driving engines 116, common axis
117, pedestal 118, No. three driving engines 119, No. four driving engines
Figure 14 is the hydraulic efficiency pressure system diagram of block that the present invention adopts.Among the figure,
120, valve 122, fuel tank safety valve are connected in fuel tank 121, ground
123, valve 125, hydraulic filter are connected in reducing valve 124, ground
126, compression indicator 127, pressure accumulator 128, inflation are chewed
136, check valve 137, safety valve 138, check valve
139, hydraulic filter 140, Hydraulic Pump 141, hydraulic filter
129, distortion manipulation 130, flap control 131, aileron control
132, rudder control 133, flying tail manipulation 134, hatch door are handled
135, subsequent use joint
Figure 15 is a distortion maneuvering system schematic diagram of the present invention., among the figure
5, rotor pillar 15, the rocking arm 39 that verts, the pressurized strut of verting
22, outer section wing 56, fluid pressure type strut 142, drive link
143, selector valve rocking arm 144, selector valve 145, pressure oil pipe
146, oil return pipe 257, tilting rotor lockout mechanism
258, folded wing lockout mechanism
Figure 16 is a flap control systematic schematic diagram of the present invention.Among the figure
147, stage casing trailing edge 148, rotating shaft 149, wing flap
150, wing flap rocking arm 151, pressurized strut 152, control handle
153, selector valve 154, pressure oil pipe 155, oil return pipe
Figure 17 is an aileron control systematic schematic diagram of the present invention, among the figure
156, port aileron 157, rotating shaft 158, left rocking arm
159, left pressurized strut 160, right pressurized strut 161, right rocking arm
162, rotating shaft 163, starboard aileron 164, oil return pipe
165, pressure oil pipe 166, selector valve 167, selector valve rocking arm
168, drive link
Figure 18 is a flying tail maneuvering system schematic diagram of the present invention.Among the figure
169, pressurized strut 170, horizontal tail rocking arm 171, rotating shaft
172, horizontal tail carriage 173, flying tail 174, oil return pipe
175, pressure oil pipe 176, selector valve 177, selector valve rocking arm
178, drive link
Figure 19 is a rudder control systematic schematic diagram of the present invention.Among the figure
179, pressurized strut 180, rocking arm 181, rotating shaft
182, yaw rudder 183, oil return pipe 184, pressure oil pipe
185, selector valve 186, selector valve rocking arm 187, drive link
Figure 20 is the hydraulically powered control system diagram of block.Among the figure,
188, chaufeur (hand, pin) 189, steering unit 190, transmission device
191, hydraulic booster 192, transmission device 193, rudder face
Figure 21 is flying tail hydraulically powered control system figure.Among the figure
194, jociey stick 195, drive link 196, rocking arm
197 arm regulators 198, control feel simulator
199, tab effect mechanism 200, hydraulic booster 201, flying tail
Figure 22 is a central control mechanism of the present invention---distortion joystick sketch.Among the figure
202, distortion joystick 203, base 204, retracing spring
205, drive link 206, two rocking arm 142, drive link
Figure 23 is a central control mechanism of the present invention---the jociey stick sketch drawing.Among the figure
(a) hand reset (b) automatically reset 207, rocking arm
208, Torque tube 209, jociey stick 210, rocking arm
211, drive link 212, drive link 213, drive link
214, retracing spring
Figure 24 is a central control mechanism of the present invention---the pedal sketch.Among the figure
215, cross bar 216, vertical shaft 217, retracing spring
218, pedal rod 219, pedal 220, cable wire
221, disk 222, rocking arm 223, drive link
Figure 25 is a proof machine driving compartment arrangement plan of the present invention.Among the figure
224, instrument carrier panel 225, operator platform 226, telltale
227, volt meter 228, amperemeter/ammtr 229, magnetic compass
230, fuel level indicator 231, low amount of fuel warning indication
232, engine condition avometer 233, horizon instrument 234, airspeed indicator
235, height above sea level kilsyth basalt 236, elevation rate table 237, clock
238, turning slip speedometer drive 239, charging water gauge 240, cylinder head ther mometer
241, engine charge compression indicator 242, avionics device control plate 243, airscrewpiston indication
244, propeller speed table 245, wing flap control stalk
246, blwr control stalk, blwr work indication 247, jociey stick
248, combustion gas mixing is than adjust bar 249, propeller speed control stalk
250, left foot pedal 251, right pedal 252, seat
253, form 254, bottom right form under the left side
255, tilting rotor position indication 256, the indication of folded wing position
257, tilting rotor lockout mechanism 258, folded wing lockout mechanism
259, distortion joystick 260, flap configuration indication
261, driving engine magneto switch 262, source switch 263, throttle lever
264, fuel charger switch 265, lighting circuit switch 266, following cover switch
267, hatch door master cock 268, hydraulic efficiency pressure system switch
Figure 26 is U.S. V-22 " osprey " tiltrotor three-view drawing and power, drive system structure sketch.(this figure be selected from " aviation knowledge 10 phases of calendar year 2001)
The specific embodiment
Through embodiment and combine accompanying drawing, technical scheme of the present invention is elaborated below.
In Fig. 1, be the fixed wing aircraft shape shown in front elevation and the birds-eye view, rotor is horizontal, and an outer section wing upwards stretches to the utmost point extreme position (on the leading edge anti-10 °); Be the helicopter shape shown in the lateral plan, rotor is in vertical position, and outer section wing is folded to end position (leading edge is perpendicular to ground level) downwards.
In Fig. 2, Fig. 3, embodiment shown in Figure 4, the geometric parameter of swallow formula aerodynamic arrangement is:
1, wing geometric parameter
The stage casing wing is opened up long L relatively
0=L
0/ L=48%
Wing aspect ratio λ=L
2/ S=7.4
Taper η=b
0/ b
1=2.4
Sweepback angle X=30 ° of the outer section leading edge of a wing
Outer section leading edge of a wing dihedral angle φ=10 °
The relative camber f=f/b=2% of aerofoil profile
Aerofoil profile maximum camber position X
f=X
f/ b=40%
Relative thickness of airfoil C=c/b=18%
Aerofoil profile maximum ga(u)ge position Xc=Xc/b=30%
2, flying tail geometric parameter
The relative wing area S of horizontal tail
H=S
H/ S=20%
Horizontal tail aspect ratio λ=L
2 1/ S
H=2.3
Horizontal tail taper ratio η=b
2/ b
3=3.8
Horizontal tail tail capacity A
H=L
HS
H/ (b
AS)=0.68
Horizontal tail leading edge sweep x
1=60 °
Horizontal tail trailing edge fork angle X
2=130 °
3. vertical tail geometric parameter
The relative wing area of vertical tail
Vertical tail aspect ratio λ=L
2 2/ S
V=1.4
Vertical tail taper ratio η=b
0/ b
1=2.8
Vertical tail tail capacity A
V=L
VS
V/ LS=0.12
Vertical tail leading edge sweep X
0=42 °
The opposed tail surface of yaw rudder amasss
In the embodiment shown in fig. 5, vert sleeve (18) and rotor pillar (5) for steel cylindrical tube.Transmission shaft (17) and the sleeve that verts (18) are arranged on the same axis, make rotor rotatablely move and vert the motion do not disturb mutually.Vert sleeve (18) and rotor pillar (5) is threaded with right angle pipe fitting joint (20) that to add screw fastening.Transmission shaft (17) configuration deep groove ball bearing (10) is installed in the inner chamber two ends of the sleeve that verts (18); Use bearing dead ring (8) and No. two bearing installation lids (11) fixing respectively; Bearing dead ring (8) is threaded with the sleeve that verts (18), and to add screw fastening, and No. two bearing installation lids (11) are threaded with the sleeve that verts (18), and to add screw fastening.Rotor shaft (6) layout circle taper roller bearing (3) is installed in the inner chamber two ends of rotor pillar (5); Use a bearing dead ring (8) and a bearing installation lid (4) fixing respectively; Bearing dead ring (8) is threaded with rotor pillar (5), and to add screw fastening, and a bearing installation lid (4) is threaded with rotor pillar (5), and to add screw fastening.Transmission shaft (17) is connected with rotor shaft (6) layout circle bevel gear set (19), transmission axis and rotor axis right angle intersection.Rotor shaft (6) top configuration rotor hub (2) and rotor head fairing (1), rotor blade (7) is installed on the blade shank of rotor with hub (2).Sleeve (18) the two ends configuration plain bearings (9) that vert are installed on the bearing installation plate (92) of stage casing wing spar structure (16) with bolt.The rocking arm (15) that verts is fastened on the sleeve that verts (18) with key and screw and leans on fuselage inwall one end, and this rocking arm (15) is provided with prong and is used for being connected with pressurized strut piston rod bearing pin.Transmission shaft (17) configuration driving chain wheel (12) is connected with the gross horsepower output chain gear of engine system with driving chain (14).On the spar structure of fuselage another side; Identical tilting rotor mechanism is installed symmetrically, and the transmission shaft on left and right both sides (17) connects with coupler (13), forms complete coaxial type tilting rotor system; This system left and right two secondary rotors dispose with positive and negative oar; Its rotating speed is equal, and is in the opposite direction, equilibrium of torques.
In the embodiment shown in fig. 6; Outer section wing (22) is connected with stage casing wing (85) with hinge (23); Fluid pressure type strut (56) lower end and fuselage strut joint (24) are hinged; Piston rod is hinged with the strut joint (26) of outer section wing, fluid pressure type strut (56) handle the folding downwards end position of outer section wing (22) be leading edge perpendicular to ground level, the end position that upwards stretches is on the leading edge anti-10 °
Embodiment shown in Figure 7 is the general layout of major part of the present invention.Central control mechanism in the driving compartment (27) and meter system have detailed description in addition in Figure 25.In the power cabin (28), except that engine system and front and back fuel tank were installed, both sides leaned on fuselage wall that two capsules also are housed, and are used to hold the vert pressurized strut (39) and the rocking arm that verts.Engine inlets (29) are installed in the outer wall of power cabin (28).Wing two ends, stage casing top airfoil is provided with the rotor groove (31) that verts, and is used to hold the rotor pillar that verts forward.On the wing structure of stage casing, be furnished with the left-handed wing (32) and the dextrorotation wing (36), wing flap (35) and the flap actuator (34) of navigation light (30), tilting rotor system (33).Connect with hinge (23) between stage casing wing and the outer section wing (22), and configuration pipeline box (37).Be furnished with vertical tail pressurized strut (41), rocking arm (42), rotating shaft (43), collision avoidance light (44) and yaw rudder (45) above the tail structure in the vertical tail.Be furnished with flying tail pressurized strut (48), rocking arm (47) in the tail structure.The rotating shaft of flying tail is connected tail structure both sides, and horizontal tail (46) is stretched out from the tail rear window.Engine exhaust port (49) is arranged on the base plate of tail.Deck store (51) is as bus attendant work stall, water closet and luggage locker.Main landing gear (54) damper leg is installed on the construction profile of fuselage main framing (50), and strut is installed on the fuselage bottom girder.Outer section wing (22) is provided with aileron (55), aileron pressurized strut (53) and navigation light (57).Fluid pressure type strut (56) upper end is hinged with the strut joint of outer section wing, and lower end and the structural joint of fuselage main framing (50) are hinged.Arrange equipment such as seat in the main cabin (58), hatch door (59) is arranged in forward position, right side, main cabin.Nose-gear (60) is installed on driving compartment (27) the lower floor bottom girder.Driving compartment lower floor is an equipment compartment, and battery pack (61), landing lights (62), avionics equipment (63) wherein are set.Head is provided with pitot (64).
In the embodiment shown in fig. 8, the present invention adopts high mounted wing wing box to pass the topology layout that fuselage adds outer strut, and airframe structure is confirmed four main technique separating interfaces, i.e. four main interfaces; Stage casing wing interface (69), driving compartment interface (66), deck store interface (72) and tail interface (73).Leave fairing interface (65) at head in addition.Airframe structure is made up of bulkhead (67), put the beams in place (70), central sill (79), underbeam (80), stringer (71) and covering (78), and except that covering (78) was used riveted joint, other each parts all connected with track bolt.The stage casing wing is connected on the wing interface (69) with track bolt, and other interfaces adopt peripheral bolted connection.Equipment ceiling board (83), driving compartment base plate (84), main cabin base plate (81), engine ceiling board (68) and deck store base plate; All use joint and bolted connection on the beam and bulkhead of periphery; Said base plate increases the function of airframe structure intensity in addition except that parts and equipment erecting stage are provided.Below equipment ceiling board (83), main cabin base plate (81) and deck store base plate, leave pipeline passway (82), be used to arrange conduit under fluid pressure and the cable line that leads to each functional component from driving compartment.The vertical tail structure is made up of floor (74), spar (76), stringer (75), covering (77) and yaw rudder.Except that covering (77) adopted the riveted joint mode, other members were with joint and bolted connection.The joint of the interface in the airframe structure, beam, bulkhead, each floor beam and key position all adopts steel, and other members and vertical tail structure adopt high-strength aluminum alloy material.
Embodiment shown in Figure 9 is a wing structure transparent view of the present invention.Among the figure, the inner structure and the stage casing wing (85) of outer section wing (22) are basic identical, so do not draw in detail.Spar (16), rib (87), bearing installation plate (92), top airfoil stringer (86) and lower aerofoil stringer (90) are become the whole wing spar framework with joint with bolted connection, with the spar framework with wing joint (91) and bolted connection on the wing interface of fuselage.The midway location of rib (87) leaves circular hole, is used to install the sleeve that verts (18) of rotor system, and the sleeve that verts (18) configuration plain bearing (9) bolt together is on bearing installation plate (92).Covering (94) is riveted on the spar framework.The rotor at wing two ends, the stage casing groove that verts is used to hold the rotor pillar (5) that verts forward.Gear case cover (93) is connected on the casing with hinge and snap close, is convenient to open the mechanism in the service kit.The rotating shaft of wing flap (35) is connected on stage casing wing (85) the trailing edge structure.Spar (16) bolt together of hinge (23) one ends and stage casing wing, the spar bolt together of the other end and outer section wing (22).Pipeline box (37) is installed on the endwall structure of stage casing wing (85); Cable (88) and hydraulic hose (89) enclose around axis 1-2 in pipeline box (37); One end leads to the maneuvering system in the fuselage, and the other end gets in the outer section wing (22) and leads to functional components such as aileron pressurized strut, navigation light.
The effect of pipeline box (37) be outside section wing (22) folding with stretching process in, protection cable line (88) and hydraulic hose (89) can not fractureed.The rotating shaft of aileron (55) is connected on the trailing edge structure of outer section wing (22).Spar (16), bearing installation plate (92) and wing joint (91) adopt the high strength steel material; Rib (87), stringer (86), (90), covering (94) and gear case cover (93) are used high-strength aluminum alloy material, and wing flap (35) and aileron (55) can adopt composite material and honeycomb structure.
Embodiment shown in Figure 10 is the enlarged drawing of outer section wing-folding hinge arrangement of the present invention.Among the figure, on the web (96) of two hinge master slice bolt ups below wing spar termination, stage casing edge strip (95), constitute hinge tongue-and-groove (97).The same bolt up of intermediate plate of hinge tenon (99) is outside on the web (961) below section wing spar termination edge strip (951).The casterangle of hinge tenon (99) intermediate plate equates with outer section leading edge of a wing sweepback angle.Hinge tenon (99) inserts in the hinge tongue-and-groove (97), connects with bearing pin (98).
Embodiment shown in Figure 11 is a flying tail constructional drawing of the present invention.Among the figure, horizontal tail rocking arm (100) bolt together is on the clamping plate of horizontal tail carriage (107), and rotating shaft (101) configuration plain bearing is connected with the tail structure.Spar framework (103) bolt together of being made up of vertical spar and crossbeam is on horizontal tail carriage (107).Rib (102) with joint and bolted connection on spar framework (103).Top airfoil stringer (105) and lower aerofoil stringer (104) are riveted on the rib (102).Covering (106) is riveted on top airfoil stringer (105) and the lower aerofoil stringer (104) again.All members of flying tail all can adopt high-strength aluminum alloy material, also can adopt composite material and honeycomb structure.
Embodiment shown in Figure 12 is the framework type landing gear structure sketch that the present invention adopts.Among the figure, (A) being nose-gear, (B) is main landing gear.Load framework and airframe structure by damper leg (108), strut (109) and wheel (110) are formed are hinged, also all are hinged between damper leg in the framework (108) and the strut (109).When alighting gear receives ground reaction force; Damper leg (108) and two struts (109) only bear the axial force that stretches or compress, and do not bear moment of flexure, and are therefore simple in structure; Weight is lighter, and its bigger contour dimension also is applicable to outer section wing folding needed space and height downwards.
Embodiment shown in Figure 13 is a composite engine systematic schematic diagram of the present invention.This system is by a driving engine (114), No. two driving engines (115), No. three driving engines (118), No. four driving engines (119) ... wait many driving engines and common axis (116) to form.Common axis (116) configuration antifriction-bearing box is installed on the pedestal (117), and several driving chain wheels (111) and a gross horsepower output chain gear (112) also are set.Driving chain wheel (111) is connected with chain with the output chain gear of every driving engine, and gross horsepower output chain gear (112) is connected with the driving chain wheel of tilting rotor system with chain (113).The effect of common axis (116) is to accumulate gross horsepower to the power of every driving engine output, flows to the tilting rotor system works through gross horsepower output chain gear (112) again.There is following advantage in this composite engine system: the one, and under the condition that installing space allows, the engine stand number that makes up is unrestricted, can realize that puffer assembles the target of big aircraft; The 2nd, the gross horsepower of this system leaves enough power more than needed except that satisfying the maximum power drain of aircraft, even wherein one or two driving engines break down even stop suddenly, tiltrotor still can normal flight, and safety is fully ensured.
Among the embodiment shown in Figure 14, the voltage supply system connects valve (121), fuel tank safety valve (122), reducing valve (123), ground fuel tank (120), ground and connects that valve (124), hydraulic filter (125), compression indicator (126), pressure accumulator (127), inflation are chewed (128), check valve (136), safety valve (137), check valve (138), hydraulic filter (139), Hydraulic Pump (140), hydraulic filter elements such as (141) is formed by connecting with pressure oil pipe and oil return pipe.Functional subsystem is made up of distortion manipulation (129), flap control (130), aileron control (131), rudder control (132), flying tail manipulation (133) and hatch door manipulation (134), and other is provided with subsequent use joint (135).
Embodiment shown in Figure 15; It is the principle of work of distortion maneuvering system; Among the figure; Pressure oil pipe (145) in the oil inlet of selector valve (144) is connected with the voltage supply system with oil return pipe (146), and the oil outlet oil pipe is connected with the oil pipe of folded wing system with the tilting rotor system respectively, and tilting rotor lockout mechanism (257) and folded wing lockout mechanism (258) are set.In the tilting rotor system, the hydraulic tubing parallel connection that two pairs are verted and transferred to tube (39), the pressurized strut piston rod is hinged with the rocking arm (15) that verts, and the cylinder barrel bottom is hinged with airframe structure, and the motion of stretching, contract of piston rod drives rotor pillar (5) and produces the motion of verting.In the folded wing system, the piston rod of fluid pressure type strut (56) is hinged with the strut joint of outer section wing (22) lower aerofoil special use, and strut (56) cylinder barrel bottom is hinged with body joint.The motion of stretching, contract of fluid pressure type strut (56) piston rod drives outer section wing (22) and produces folding and stretching routine.
Rule is handled in distortion: the preceding distortion joystick that pushes away, and body becomes fixed wing aircraft, post-tensioning distortion joystick, body becomes helicopter.Concrete operating pattern has two kinds:
(1) static deformation is handled.Promptly, become helicopter to body, perhaps become fixed wing aircraft on the ground by predefined flying method, indeformable in landing and flight course.That is to say, become helicopter after, just use helicopter flight, become fixed wing aircraft after, just fly with fixed wing aircraft.Its steering program is: open tilting rotor lockout mechanism (257) and folded wing lockout mechanism (258) simultaneously; Before push away the distortion joystick; Signal (displacement and stick force) flows to selector valve rocking arm (143) through drive link (142) and makes it to forward to A point position; The A position of selector valve (144) is communicated with the two ends oil pipe, and the pressure oil that flows out from pressure oil pipe (145) gets into the pressurized strut of verting (39) ante-chamber and fluid pressure type strut (56) back cavity respectively, and the piston rod withdrawal of the pressurized strut of verting (39) spurs the rocking arm (15) that verts verts rotor pillar (5) forward; Simultaneously, the piston rod of fluid pressure type strut (56) stretches out and promotes upwards stretching, extension of outer section wing (22).When rotor pillar (5) turn forward go to level attitude, outside a section wing (22) when upwards stretching supreme anti-10 ° of positions; Unclamping the distortion joystick automatically resets; Selector valve (144) resets to neutral position C point, and oil circuit is closed, and this moment, body just became a fixed wing aircraft.If tilting rotor lockout mechanism (257) and folded wing lockout mechanism (258) are closed simultaneously, just can carry out independent flight with fixed wing aircraft.If carry out independent flight with helicopter; Should on the ground body be become helicopter equally; Its steering program is: open earlier tilting rotor lockout mechanism (257) and folded wing lockout mechanism (258) simultaneously, post-tensioning distortion joystick makes the B position of selector valve (144) be communicated with the two ends oil pipe.Pressure oil gets into the back cavity of the pressurized strut of verting (39) and the ante-chamber of fluid pressure type strut (56) respectively.The piston rod of pressurized strut (39) of verting stretches out and promotes rotor pillar (5) and upwards vert to the upright position, and the piston rod withdrawal pulling outer section wing (22) of fluid pressure type strut (56) is folded to leading edge downwards perpendicular to the ground level position, and body has just become a helicopter.If independently fly with helicopter; Can close folded wing lockout mechanism (258); Make the tilting rotor lockout mechanism still be in open mode, distortion joystick manipulation rotor pillar (5) is limited to vert and cooperates jociey stick, pedal and helicopter landing of Throttle Opening Control lever operation and flight.
(2) dynamic deformation is handled.Promptly fly with tiltrotor; Earlier become helicopter to body on the ground, all open tilting rotor lockout mechanism (257) and folded wing lockout mechanism (258), after the lift-off of taking off vertically; Before push away the distortion joystick; Become fixed wing aircraft to helicopter while flying, unclamp the distortion joystick, just can use jociey stick, throttle lever and the long-distance flight of pedal operating aircraft high speed.When aircraft arrives the sky, destination, post-tensioning distortion joystick, fixed wing aircraft has become helicopter, then vertical landing.
Embodiment shown in Figure 16 is a flap control systematic schematic diagram of the present invention.Among the figure, the oil outlet pipe of selector valve (153) is directly connected to the ante-chamber and the back cavity of pressurized strut (151).The joint of pressurized strut (151) rear end and stage casing wing (147) trailing edge structure is hinged, and piston rod and wing flap rocking arm (150) are hinged, and rotating shaft (148) the configuration plain bearing of wing flap (149) is installed on stage casing trailing edge (147) structure.Chaufeur direct control control handle (152), the preceding control handle (152) that pushes away, the A position of selector valve (153) is communicated with oil inlet (154), (155) and oil outlet pipe.Pressure oil gets into the back cavity of pressurized strut (151) through pressure oil pipe (154), and piston rod stretches out and promotes wing flap rocking arm (150), make wing flap (149) around the shaft (148) deflect down.The oil return that pressurized strut (151) ante-chamber is discharged is flowed back to fuel tank from oil return pipe (155).The steering program that wing flap (149) puts down finishes.Chaufeur post-tensioning control handle (152), the B position of selector valve (153) is communicated with the two ends oil pipe, and pressure oil gets into pressurized strut (151) ante-chamber through pressure oil pipe (154), and piston rod withdrawal pulling wing flap rocking arm (150) is upwards packed up wing flap.Place the C position to control handle (152), oil circuit is closed, and prohibits the wing and is locked.When sliding the race landing with fixed wing aircraft, just use wing flap in order to increase lift, with helicopter and tiltrotor flight the time, wing flap is blocked.
Embodiment shown in Figure 17 is an aileron control systematic schematic diagram of the present invention.Among the figure; (166) the left oil outlet pipe of selecting to live is divided into two-way, and one the tunnel connects the back cavity of left pressurized strut (159), and another road connects the ante-chamber that pressurized strut (160) are done on the right side; Right oil outlet pipe also is divided into two-way; One the tunnel connects the ante-chamber of left pressurized strut (159), and another road connects the back cavity of right pressurized strut (160), makes the in the opposite direction of port aileron (156) and starboard aileron (163) deflection.The rotating shaft (157) of port aileron (156) is installed on the outer section trailing edge structure of left side, and the rotating shaft (162) of starboard aileron (163) is installed on section trailing edge structure on the right side outside.Joint on pressurized strut (159) rear end, a left side and the left side wing structure is hinged, and piston rod and left rocking arm (158) are hinged.Joint on right pressurized strut (160) rear end and the right side wing structure is hinged, and piston rod and right rocking arm (161) are hinged.The steering program of this system is: press jociey stick left; Signal passes to selector valve rocking arm (167) through drive link (168) and makes it to forward to A point position; The A position of selector valve this moment (166) is communicated with the two ends oil pipe, and pressure oil gets into left pressurized strut (159) ante-chamber and right pressurized strut (160) back cavity respectively through pressure oil pipe (165).Left side pressurized strut (159) piston rod withdrawal pulling left rocking arm (158) upward deflects port aileron (156); Right pressurized strut (160) piston rod stretches out and promotes right rocking arm (161), and starboard aileron is deflected down.Because port aileron (156) upwards partially, starboard aileron (163) downward bias causes the left side airfoil lift to reduce, and the right side airfoil lift increases, and makes fuselage around Y left side lift-over.Press jociey stick to the right, then fuselage lift-over to the right.The oil return that left side pressurized strut (159) and right pressurized strut (160) are discharged is at work all passed through oil return pipe (164) and is flowed back to fuel tank.
Embodiment shown in Figure 180 is a flying tail maneuvering system schematic diagram of the present invention, and among the figure, horizontal tail rotating shaft (171) is installed on the structure on two sides in tail exit, and the joint on pressurized strut (169) rear end and the tail structure of bottom girder is hinged.Horizontal tail (173) is connected as a single entity with bolt with horizontal tail carriage (172).Its steering program is: the chaufeur stick-forword movement; Signal is delivered to drive link (178) promotion selector valve rocking arm (177) and forwards A point position to; The A position of selector valve (176) is communicated with the oil pipe at two ends, and pressure oil gets into pressurized strut (169) back cavity from pressure oil pipe (175), piston rod stretch out promote horizontal tail rocking arm (170) make horizontal tail (173) around the shaft (171) deflect down; Horizontal tail lift increases, and makes head around transverse axis nutation (bowing).Otherwise the post-tensioning jociey stick can be arranged on the B position with selector valve (176), and pressure oil gets into pressurized strut (169) ante-chamber, and piston rod withdrawal pulling horizontal tail rocking arm (170) upward deflects horizontal tail (173), and the horizontal tail lift divergence makes head around transverse axis face upward (new line).In steering program, the oil return that pressurized strut (169) inner chamber is discharged is flowed back to fuel tank through oil return pipe (174).
Embodiment shown in Figure 19 is a rudder control systematic schematic diagram of the present invention.Among the figure, yaw rudder rotating shaft (181) is installed on the vertical tail structure, and the rear end and the structural joint of vertical tail of pressurized strut (179) are hinged.The steering program of yaw rudder (182) is: pedal left foot before the chaufeur and pedal; The power of pedaling promotes selector valve rocking arm (186) through drive link (187) and forwards A point position to; Make the A position of selector valve (185) be communicated with the two ends oil pipe, pressure oil gets into pressurized strut (179) ante-chamber through pressure oil pipe (184), piston rod withdrawal pulling rocking arm (180) right-hand turning; Make yaw rudder (182) with rotating shaft (181) deflection left, the aerodynamic force that acts on the vertical tail makes Nose Left deflection.Pedal right pedal before the chaufeur; The B position of selector valve (185) is communicated with the two ends oil pipe; Pressure oil gets into the back cavity of pressurized strut (179) through pressure oil pipe (184); Piston rod stretches out and promotes rocking arm (180) left-handed turning, makes yaw rudder (182) with rotating shaft (181) deflection to the right, and aerodynamic force makes Airplane Nose Right deflection.In pressurized strut (179) working process, the oil return that inner chamber is discharged is flowed back to fuel tank through oil return pipe (183).
Aforementioned Figure 15, Figure 16, Figure 17, Figure 18 and embodiment shown in Figure 19; It all is a kind of simple hydraulically powered control system of forming by selector valve and pressurized strut; This system can only only be applicable to the flight control of more small-sized tiltrotor of the present invention with the rudder face start to limited several position.For more large-scale tiltrotor of the present invention, the aerodynamic loading on the rudder face is big, needs to adopt hydraulic booster to assisted control.Embodiment shown in Figure 20 is a representative type hydraulic booster maneuvering system diagram of block.Among the figure; Chaufeur is through hand, pin (188) are operated the joystick, pedal is formed central control mechanism (189); Through transmission device (190) signal conveys is arrived hydraulic booster (191); Hydraulic booster (191) is transported to rudder face (193) through transmission device (192) after signal is amplified again, thereby realizes the deflection of hydraulic booster primary control surface.The advantage of this system is to realize the one-to-one relationship of input and output signal (displacement or power).
Embodiment shown in Figure 21 is the normal hydraulic booster that adopts in the prior art to be handled principle be used for flying tail of the present invention and handle.Among the figure; Pilot control jociey stick (194) produces a mechanical signal (displacement and power), and signal flows to hydraulic booster (200) through drive link (195), rocking arm (196), arm regulator (197), control feel simulator (198), tab effect mechanism transmission devices such as (199).Flow to the rocking arm of flying tail after hydraulic booster (200) amplifies the signal that receives again through transmission devices such as rocking arm, drive links, promote (or pulling) flying tail deflection.Arm regulator (197) scalable jociey stick arrives the gearing factor of horizontal tail and arrives the transmission position of control feel simulator.Control feel simulator (198) claims aircraft control load simulator again, and its effect is to make chaufeur strong sensation when operating the joystick, and it and arm regulator (197) are used, and can also feel the variation of rudder face load indirectly.Tab effect mechanism (199) connects with control feel simulator (198), but the removal control force makes the controls-free flight of chaufeur ability.
The embodiment of above-mentioned each maneuvering system is not unique embodiment, comparative maturity and practical all can using for reference in every prior art.
Embodiment shown in Figure 22 is a central operation of the present invention mechanism---distortion joystick sketch.Among the figure, base (203) is installed on the right operator platform structure of driving compartment, and chaufeur is handled with the right hand.Distortion joystick (202) lower end is provided with retracing spring (204), and its effect is in the manipulation process, can automatically reset behind the loose bar, also can experience displacement and stick force.Steering program is: the preceding distortion joystick (202) that pushes away; Stick force is transported to distortion maneuvering system selector valve rocking arm through drive link (205), rocking arm (206), drive link (142); Handle that the rotor pillar verts forward and outer section wing upwards stretches, when the rotor pillar arrives the desired location with outer section wing, unclamp and be out of shape joystick (202) it is automatically reset; The distortion steering program finishes, and body becomes fixed wing aircraft; Post-tensioning distortion joystick (202) can handle then that the rotor pillar upwards verts and an outer section wing is folded to the desired location downwards, makes body become helicopter.Above-mentioned steering program is called interlock to be handled, and another kind of steering program is called independent manipulation, exactly in two lockout mechanisms one of them is opened, and another is closed.When handling, can only handle the subsystem of the lockout mechanism that is opened.For example, folding downwards and close the folded wing lockout mechanism outer section wing in advance when making helicopter flight, just can handle helicopter flight.During helicopter flight was handled, distortion joystick (202) reached the purpose of control flying speed through the angle that the control rotor verts, and the directional control and the pitch control of helicopter are still realized by pedal and jociey stick.
Embodiment shown in Figure 23 is a central control mechanism of the present invention---the jociey stick sketch.Among the figure, (a) be hand reset, (b) for automatically reseting.Torque tube (208) two ends configuration plain bearing is installed on the operator platform structure.Jociey stick (209) can be handled flying tail and aileron simultaneously, and promptly push rod is used for the deflection of fore-and-aft control flying tail with taking back forward; Left and right depression bar is used for the lateral control aileron movement.Fore-and-aft control and lateral control do not disturb mutually, and aileron is motionless when promptly handling horizontal tail, and horizontal tail is motionless when handling aileron.Concrete steering program is: stick-forword movement (209); Stick force and displacement signal are transported to the selector valve (or hydraulic booster) of flying tail maneuvering system through drive link (212), rocking arm (210) and drive link (213); The manipulation flying tail deflects down; Make nose dip (bowing), post-tensioning jociey stick (209) then can be handled nose-up (new line), but steering program finishes hand reset or automatically resets through retracing spring (214).Press jociey stick (209) left; Stick force drives Torque tube (208) rotation moves right the drive link (211) of rocking arm (207) lower end, the signal of displacement and power is passed to the selector valve of aileron control system, thereby handle aileron movement; Make fuselage lift-over left; Equally, press jociey stick to the right, can handle fuselage lift-over to the right.After steering program finishes, hand reset, or loose bar automatically resets through retracing spring (214).
Embodiment shown in Figure 24 is a central control mechanism of the present invention---the pedal structure sketch.Among the figure, two cross bars (215) and two pedal rods (218) hinge joint are each other formed the parallelogram framework.The midway location of two cross bars (215) and vertical shaft (216) are hinged, and the vertical shaft lower end is fixed on the operator platform base arrangement, galianconism that is used to install retracing spring (217) of upper end configuration.The vertical shaft hypomere is provided with the disk (221) of trough of belt, and the rocking arm (222) on the disk (221) rotates with disk (221).Configuration cable wire (220) one ends are connected sheer pole (215) left side section, and the rich disk 1-2 circle of cable wire (220) the back other end is fixed on the right section of sheer pole (215).Rocking arm (222) is connected with the selector valve rocking arm of rudder control system through drive link (223).Concrete steering program is: the preceding left foot of pedaling is pedaled (219); rocking arm (222) turning clockwise; through drive link (223) with the selector valve rocking arm (if the displacement signal carried with the rotation direction of yaw rudder selector valve rocking arm do not match; two rocking arms can in addition be set with change sense of displacement) of signal conveys, just but the deflection left of steering rudder makes the Nose Left commentaries on classics to the rudder control system.Equally, the preceding right pedal of pedaling gets final product the deflection to the right of steering rudder, and Airplane Nose Right is changeed.After steering program is accomplished, unclamp pedal, pedal can automatically reset, and the selector valve of rudder control system also resets to the C position, the SELF CL oil circuit.
Above-mentioned Figure 22, Figure 23, central control mechanism shown in Figure 24 are not the unique embodiment of the present invention, and comparative maturity all can be used for reference with practical example in every prior art.
Figure 25 is a proof machine driving compartment arrangement plan of the present invention.Among the figure, on the instrument carrier panel (224), telltale (226) is arranged in the optimal visual area of the middle chaufeur of first row, and both sides are respectively volt meter (227) and clock (237).Amperemeter/ammtr (228) is in volt meter (227) below.Engine instruments is arranged in the foreground of instrument carrier panel (224) left side and operator platform (225), helps chaufeur and concentrates observation.Fuel level indicator (230), low amount of fuel warning indication (231), engine condition avometer (232), cylinder head ther mometer (240), engine charge compression indicator (241), airscrewpiston indication (243), propeller speed table (244) are wherein arranged.Flying instruments is arranged in middle part and the right of instrument carrier panel (224), and the aviator is focused one's attention on when flight control.Magnetic compass (229), horizon instrument (233), airspeed indicator (234), height above sea level kilsyth basalt (235), elevation rate table (236), turning slip speedometer drive (238), charging water gauge (239) are wherein arranged.Avionics device control plate (242) is arranged in the foreground midway location of operator platform (225), is convenient to driver's operation.The joystick of arranging on the drum before the operator platform has: wing flap control stalk (245), blwr control stalk and blwr work indication (246), combustion gas mixing are than adjust bar (248) and propeller speed control stalk (249).Jociey stick (247) is arranged in seat (252) front, and left foot is pedaled (250) and right pedal (251) on floor, the preceding left and right both sides of jociey stick (252).Seat (252) both sides are provided with a left side form (253) and bottom right form (254) down, are convenient to the driver's observation surface state.Be furnished with tilting rotor position indication (255), the indication of folded wing position (256), tilting rotor lockout mechanism (257), folded wing lockout mechanism (258), distortion joystick (259) and hydraulic efficiency pressure system switch (268) on the right operator platform.On the left-hand drive platform, be furnished with flap configuration indication (260), driving engine magneto switch (261), source switch (262), throttle lever (263), fuel charger switch (264), lighting circuit switch (265), following cover switch (266) and hatch door master cock (267).
Driving compartment shown in the present embodiment is arranged, is not unalterable, example that neither be unique.In practical implementation, can adjust and increase and decrease according to the particular cases such as airworthiness of engine type, setting.
Requirement of strength of the present invention is carried out the airplane design strength specification of country's promulgation.
Claims (5)
1. swallow type inclined rotation rotorcraft; Helicopter and fixed wing aircraft are combined together; Can independently fly with helicopter, fixed wing aircraft and three kinds of types of tiltrotor through changing external shape; It is characterized in that: fluid pressure type strut folded wing is set, and outer section wing is connected with stage casing wing hinge, the folding downwards and upwards stretching, extension of section wing outside the fluid pressure type strut is handled; Coaxial type tilting rotor system is installed on the spar structure of stage casing wing; Constitute cross-arranging type bispin wing layout; Two secondary rotors can come back rotation between upright position and level attitude, when rotor be in vertical position, outside section wing when folding downwards, be exactly a helicopter; When rotor be horizontal, outside a section wing when upwards stretching, become a fixed wing aircraft again; The composite engine system that configuration is made up of many driving engines and common axis, safety performance is reliable.
2. swallow type inclined rotation rotorcraft according to claim 1 is characterized in that: the geometric parameter of swallow formula aerodynamic arrangement is set at, and the stage casing wing is opened up long by 48% relatively, wing aspect ratio 7.4; Taper 2.4,30 ° at outer section leading edge of a wing sweepback angle, 10 ° at the outer section leading edge of a wing dihedral angle, the relative camber 2% of aerofoil profile; Aerofoil profile maximum camber position 40%, relative thickness of airfoil 18%, aerofoil profile maximum ga(u)ge position 30%, the relative wing area 20% of horizontal tail; Horizontal tail aspect ratio 2.3, horizontal tail taper ratio 3.8,60 ° of horizontal tail leading edge sweeps; 130 ° at horizontal tail trailing edge fork angle, the relative wing area 22% of vertical tail, vertical tail aspect ratio 1.4; Vertical tail taper ratio 2.8,42 ° of vertical tail leading edge sweeps, the opposed tail surface of yaw rudder long-pending 25%.
3. swallow type inclined rotation rotorcraft according to claim 1; It is characterized in that: outer section wing (22) is connected with stage casing wing (85) with hinge (23); Fluid pressure type strut (56) lower end and fuselage strut joint (24) are hinged; Piston rod is hinged with the strut joint (26) of outer section wing, fluid pressure type strut (56) handle the folding downwards end position of outer section wing (22) be leading edge perpendicular to ground, the end position that upwards stretches is on the leading edge anti-10 °.
4. swallow type inclined rotation rotorcraft according to claim 1; It is characterized in that: sleeve that verts (18) and rotor pillar (5) are steel cylindrical tube; Transmission shaft (17) and the sleeve that verts (18) are arranged on the same axis; Make rotor rotatablely move and the motion of verting is not disturbed mutually, sleeve that verts (18) and rotor pillar (5) are threaded with right angle pipe fitting joint (20), and to add screw fastening; Transmission shaft (17) configuration deep groove ball bearing (10) is installed in the inner chamber two ends of the sleeve that verts (18); Use bearing dead ring (8) and No. two bearing installation lids (11) fixing respectively; Bearing dead ring (8) is threaded with the sleeve that verts (18), and to add screw fastening, and No. two bearing installation lids (11) are threaded with the sleeve that verts (18), and to add screw fastening; Rotor shaft (6) layout circle taper roller bearing (3) is installed in the inner chamber two ends of rotor pillar (5); Use a bearing dead ring (8) and a bearing installation lid (4) fixing respectively; Bearing dead ring (8) is threaded with rotor pillar (5), and to add screw fastening, and a bearing installation lid (4) is threaded with rotor pillar (5), and to add screw fastening; Transmission shaft (17) is connected with rotor shaft (6) layout circle bevel gear set (19), and transmission axis and rotor axis intersect at a right angle; Rotor shaft (6) top configuration rotor hub (2) and rotor head fairing (1), rotor blade (7) is installed on the blade shank of rotor hub (2); Sleeve (18) the two ends configuration plain bearings (9) that vert are installed on the bearing installation plate (92) of stage casing wing spar structure (16) with bolt; The rocking arm (15) that verts is fastened on the sleeve that verts (18) with key and screw and leans on fuselage inwall one end, and this rocking arm (15) is provided with prong and is used for being connected with pressurized strut piston rod bearing pin; Transmission shaft (17) configuration driving chain wheel (12) is connected with the gross horsepower output chain gear of engine system with driving chain (14); On the spar structure of fuselage another side, identical tilting rotor mechanism is installed symmetrically, the transmission shaft of the right and left (17) connects with coupler (13), forms complete coaxial type tilting rotor system.
5. swallow type inclined rotation rotorcraft according to claim 1; It is characterized in that: the composite engine system comprises a driving engine (114), No. two driving engines (115), No. three driving engines (118), No. four driving engines (119) and common axis (116) composition; Common axis (116) configuration antifriction-bearing box is installed on the pedestal (117); Also do not put several driving chain wheels (111) and a gross horsepower output chain gear (112); Driving chain wheel (111) is connected with chain with the output chain gear of every driving engine, and gross horsepower output chain gear (112) is connected with the driving chain wheel of tilting rotor system with chain (113).
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| CN2008100699538A CN101314409B (en) | 2008-07-10 | 2008-07-10 | Swallow type inclined rotation rotorcraft |
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| CN2008100699538A CN101314409B (en) | 2008-07-10 | 2008-07-10 | Swallow type inclined rotation rotorcraft |
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| CN101314409B true CN101314409B (en) | 2012-04-18 |
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