CN1377790A - Flapping-wing flying water automobile - Google Patents

Abstract

The flapping-wing fling water automobile includes engine, double-blade air screw propeller, right and left hydraulic screw propellers, right and left wings, control system, safety lifesaving equipment, and four-wheel undercarriage, hanging damper and fuselage, with the wings being connected to the fuselage via mechanical and hydraulic mechanism. The present automobile is one traffic facility for land, water and air use simultaneously, and has high efficiency and maneuverability. Its wings may be folded for land running.

Description

Flapping-wing flying water automobile

1, technical field:

The present invention is a kind of vehicle that can both use in land, sea and air, belongs to the innovative technology of flapping-wing flying water automobile.

2, background technology:

Existing traditional fixed-wing and rotor craft is because reasons in structure is difficult to aircraft, automobile and water surface ship are combined together.All there are many shortcomings in for example following aircraft:

One, ordinary fixed rotor aircraft: taking off land to need special-purpose airfield runway, needs higher speed and could produce enough lift, causes the generation when taking off landing of about 50% left and right sides aircraft accident, and park occupied ground on ground very big.

Two, helicopter: its efficient is very low, and air resistance and induced drag cause flying speed lower more greatly, and during the aerial et out of order of most of type, the rotor of high speed revolution is fatal threats to the personnel of disembarking.

Three, the rotor craft that inclines: it combines the characteristics of ordinary fixed rotor aircraft and helicopter, but two king bolt oars when making flat flying flight resistance big, the rectangular wing induced drag of low aspect ratio is big, gliding ability is poor.

Four, fixed-wing hovercar: many people designed hovercar, but did not have a volume production.Its structure has fixed wing formula and two kinds of base models of separable wing formula.The fixed wing formula adopts the rectangular wing of low aspect ratio, and induced drag is big, road-holding property and gliding ability are poor.Separate the preceding very important person's frock top wing of wing formula flight, the wing of must dismantling after the landing just can become automobile at ground run, brings many inconvenience to use.These two kinds of base models all need the long landing runway that takes off.

Five, aqua communis is boarded a plane and ground effect aircraft: the most of employing used aerodynamic arrangement always, and vertical fin and horizontal tail are arranged, and wing is fixed on the fuselage, thereby the size of length each several part is all bigger.Be not easy to landing pier and at crowded or tortuous channel navigation, and be difficult to disembarkation and travel.

Six, forefathers' flapping wing aircraft: former flapping wing aircraft subject matter is under power, and gear mechanism transmission or connecting rod mechanism transmission are mostly used in the transmission of power, and the angle that wing is agitated fails to change.Sensor and automatic control technology are immature at that time, and aerodynamics and ornithological research are not enough.

3, summary of the invention:

The objective of the invention is to overcome above-mentioned shortcoming and provide a kind of simple in structure, size is little, and is in light weight, the flight efficiency height, and gliding ability is good, and is easy to use, all can be used as the flapping-wing flying water automobile of the vehicle in land, sea and air.

Structural representation of the present invention as shown in Figure 1, include driving engine (1), air double leaf nonuniform pitch propeller (2), a left side, right hydrodynamic force screw propeller (3,4), a left side, starboard wing (5,5 '), control system (6), safety and life (7), four-wheel landing gear and suspension damper (8), fuselage (9), driving engine (1) wherein, control system (6), safety and life (7) all place in the fuselage (9), air double leaf nonuniform pitch propeller (2) is installed in the afterbody of fuselage (9), left side hydrodynamic force screw propeller (3) and right hydrodynamic force screw propeller (4) are installed in the both sides of fuselage (9) respectively, wing (5) is installed in the top of fuselage (9), four-wheel landing gear and suspension damper (8) are installed in the two bottom sides of fuselage (9), and wherein wing (5) is connected with fuselage (9) by machine liquid combination mechanism.

The present invention is owing to adopt the structure of accessory pinna compound type folding wing or inflatable folding wing, and wing can change the angle that wing is agitated as required by control system, to obtain the control of thrust, lift and flight attitude, to carry out birds (bat) the various motions in when flight on request, so can be in travels down, on high in flight, on the water surface, navigate by water, can resemble in case of necessity and pull the plug the seabird, use double-vane to make the navigation attitude of propelling unit and control submerge, be a kind of perfect general purpose vehicle, the present invention has following characteristics:

1, can/short take-off and landing (STOL) vertical anywhere as bird, hover, inverted flight, noise in flight is very low, in theory can be silent as owl, disguised very good;

2, adopt the aerofoil control technology, manoevreability is very strong, can do the aerobatics that various birds and insect can be done and can not do, and control system (6) may command aircraft is flight and driverless operation automatically, and control program can be by software upgrading;

3, on ground and can be as bird with wingfold during the water surface, the double leaf nonuniform pitch propeller be the feathering position and be horizontal to reduce height, reduces volume and floor area;

4, adopt no empennage technology and use composite material, lightweight construction, air resistance is little, radar area is little;

5, flight efficiency height can utilize up current soaring and glide, and fuel saving, easy maintenance, and because it can use conventional fuel, so economical and practical;

6, be a kind of vehicle that can both use in land, sea and air.The present invention and fixed wing aircraft ratio can produce huge lift at short notice, promote the needed power of constant weight and are much smaller than ordinary fixed wing aircraft; Compare with autogyro, induced drag is little, flying speed is high, noise is very low, oil consumption is low, manoevreability is very strong; Compare the scene or fly to give first aid to interview etc. of when meeting accident such as traffic jam, flood, earthquake, volcanic explosion, can hightailing to the scene with ground traffic tools.The present invention also can be used as a kind of efficiently marine communication means easily, and it can be convenient to wingfold landing pier or travel and go up land, is advanced by two hydrodynamic force screw propellers when crowded or tortuous channel navigation, can pivot stud and reversing.On open water channel, lake surface and sea, wing can be launched to utilize ground effect to carry out low-latitude flying the higher or the place ahead of wave flying height that can raise easily when big obstacle is arranged;

7, comformability is strong; But the landing place hour flapping wing vertical takeoff and landing of taking off.But there be suitable flapping wing or the two bladed propeller of taking off during the landing place to advance the sliding landing of running, to reduce oil consumption.Wing is not fluttered during cruising flight, and only the fine setting wing advances by two bladed propeller when handling, and can prolong the aircraft life-span and reduce occupant's the sense of jolting;

8, safe and reliable, break down as aerial contingency, can penetrate parachute by drogue chute gun, with aircraft and occupant safety send ground back to, add that air bag system and being used of bikini surface lifesaving gas-bag system will be safer in the machine;

9, be the vehicle that save time most and increase work efficiency, and take advantage of a commercial air flights to compare not to be subjected to the flight time limitation, do not have the time of waiting, transferring to the vehicle.The passenger can be picked out from the entrance, take off in ground run to the suitable place of taking off, near the destination, land after course line through stipulating and the flying height, the passenger is delivered to the place that they think, will produce a new aerial taxi trade thus through ground run;

10, various serial flapping wing aircrafts will become the most attractive a kind of sports item, a kind of convenience that everybody likes and cheap aircraft;

11, flight time image bird is the same, to passenger and a kind of impression of returning the Nature of onlooker, as the children's stories world, is a kind of outstanding leisure vehicle;

12, civilian widely purposes is not only arranged, the advantage that has other vehicle to hardly match equally militarily, can be used for scouting, transport, to the strike of all types of target, attack armed helicopter and low-to-medium altitude cruise missile etc.The present invention is a kind of rational in infrastructure, design ingenious, function admirable, convenient and practical flapping-wing flying water automobile.

4, description of drawings:

Fig. 1 is a structural representation of the present invention;

Fig. 2 is the birds-eye view of Fig. 1;

Fig. 3 is the left view of Fig. 1;

Fig. 4 is accessory pinna and fuselage (9) bonded assembly structural representation among the present invention;

Fig. 5-1 is the accessory pinna and plain cotton fabric (26,27) the bonded assembly structural representation of accessory pinna compound type folding wing in the embodiment of the invention 1;

Fig. 5-2 is subjected to aerodynamic force for accessory pinna compound type folding wing in the embodiment of the invention 1 at flight course

The time become the structural representation of S aerofoil profile by concave-convex wings;

Fig. 5-3 is the birds-eye view of accessory pinna in the accessory pinna compound type folding wing in the embodiment of the invention 1;

Fig. 5-4 is the A-A section-drawing among Fig. 5-3;

Fig. 6 is the autonomous cruise speed system schematic diagram of compound type folding wing;

Fig. 7 is the control system schematic diagram of two hydrodynamic force screw propellers (3,4);

Fig. 8 is the pneumatic control system schematic diagram of safety and life (7);

The block diagram that Fig. 9 uses as land vehicle for the present invention;

The block diagram of Figure 10 during for the safe in utilization and life (7) of the present invention;

Figure 11 is the block diagram of the present invention as backpack individual flapping wing aircraft;

Figure 12 is the block diagram of the present invention as the flapping flight motor bike;

Figure 13 is the block diagram of the present invention as the flapping flight automobile;

Figure 14-1 is air chamber shim and plain cotton fabric (26, a 27) bonded assembly structural representation in the inflatable folding wing in the embodiment of the invention 2;

Figure 14-2 is subjected to aerodynamic force for inflatable folding wing in the embodiment of the invention 2 in flight course

The time become the structural representation of S aerofoil profile by concave-convex wings;

Figure 15 is the air-charging and air-discharging system schematic diagram of inflatable folding wing in the embodiment of the invention 2;

Figure 16 is the structural representation of inflatable folding wing in the embodiment of the invention 2.

5, the specific embodiment:

Embodiment 1:

Structural representation of the present invention such as Fig. 1, Fig. 2, shown in Figure 3, include driving engine (1), air double leaf nonuniform pitch propeller (2), a left side, right hydrodynamic force screw propeller (3,4), a left side, starboard wing (5,5 '), control system (6), safety and life (7), four-wheel landing gear and suspension damper (8), fuselage (9), driving engine (1) wherein, control system (6), safety and life (7) all place in the fuselage (9), air double leaf nonuniform pitch propeller (2) is installed in the afterbody of fuselage (9), left side hydrodynamic force screw propeller (3) and right hydrodynamic force screw propeller (4) are installed in the both sides of fuselage (9) respectively, wing (5) is installed in the top of fuselage (9), four-wheel landing gear and suspension damper (8) are installed in the two bottom sides of fuselage (9), and wherein wing (5) is connected with fuselage (9) by machine liquid combination mechanism.

For reducing design, production and use cost, the first-selected aluminium alloy car piston type of driving engine (1) is so that the gasoline that the user uses general-utility car to use easily.In addition, also can select the diesel motor, turbofan engine, turboaxle motor and a kind of driving engine (can export enough power drive Hydraulic Pumps, can produce the thrust of scalable size again) between turbofan engine and turboaxle motor that meet emission request for use.The horsepower output of driving engine is the required horsepower of complete machine take-off weight KG/10.

Propelling form of the present invention has three kinds of push types, comprises that the air flapping wing advances, air double leaf nonuniform pitch propeller advances, two hydrodynamic force screw propeller advances.Left and right wing (5,5 ') is that the air flapping wing advances, and is used for vertical/short take-off and landing (STOL), hovers, high maneuverability flight.Air double leaf nonuniform pitch propeller (2) is loaded on afterbody, can reduce influence and flight resistance to wing, ground park and when travelling double leaf nonuniform pitch propeller (2) for feathering and be horizontal, to reduce height.Two hydrodynamic force screw propellers (3,4) advance and are used for crowded or tortuous channel navigation, and the hydrodynamic force propeller propulsive efficiency is higher during the low speed surface navigation.Fuselage (9) adopts the totally-enclosed nacelle of hull formula, and its face area is little, friction drag is little, can reduce air resistance obtains good aeroperformance.Birds-eye view is a drops, mean line head section deflection below, and tail partly is partial to the top, with the convenient two bladed propeller of installing.Passenger cabin can be with reference to utilizing helicopter and car design and production technology.

An above-mentioned left side, starboard wing (5,5 ') be that structure is identical, and symmetry is connected the accessory pinna compound type folding wing of fuselage (9), include A group accessory pinna, B group accessory pinna and the machine liquid combination mechanism that is attached thereto, wherein A group accessory pinna and B group accessory pinna include some accessory pinnas again respectively, machine liquid combination mechanism includes connecting rod (212), connecting rod (214), connecting rod (219), connecting rod (221), piston rod (205), piston rod (209), piston rod (215), piston rod (220), piston cylinder (204), piston cylinder (211), piston cylinder (213), piston cylinder (218), connecting rod (212) connects to form spherical pair (207) by frame (202) and fuselage (9), connect to form spherical pair (208) with an end of piston rod (209), connect to form spherical pair (206) with an end of piston rod (205), connect to form revolute pair (222) with piston cylinder (213), connect to form revolute pair (226) with connecting rod (214); The other end of piston rod (205) places in the piston cylinder (204), forms wing luffing mechanism (53), and forms spherical pair (203) with frame (202); The other end of piston rod (209) places in the piston cylinder (211), forms the wing mechanism (47) that seesaws, and forms spherical pair (210) with frame (202); Piston rod (215) places composition wing first articulation mechanism (41) in the piston cylinder (213), forms revolute pair (223) with connecting rod (214); Connecting rod (214) connects to form revolute pair (217) with connecting rod (219), and as wing twist swing oil motor (35); Connecting rod (219) connects to form revolute pair (224) with piston cylinder (218), and form revolute pair (216) with member (221), piston rod (220) places forms wing second joint kinematic mechanism (29) in the piston cylinder (218), and forms revolute pair (216) with connecting rod (221), as shown in Figure 4.

Above-mentioned accessory pinna is done camber, wherein contain plumage beam (20), middle part, its cross sectional shape vertical with plumage beam (20) at accessory pinna are S shape, shown in Fig. 5-4, and plumage beam (20) is thin cone, and its diameter is in accessory pinna root maximum, tail end minimum, two-layer up and down resilient plain cotton fabric (26,27) is connected with the root of all plumage beams (20) of A group accessory pinna and B group accessory pinna, and plain cotton fabric (26,27) is connected with fuselage (9).Shown in Fig. 5-1.The Airfoil of being made by composite material is concave-convex wings when static, owing to be subjected to aerodynamic effect tail end K/UP, becomes the S aerofoil profile automatically when flight, shown in Fig. 5-2, can improve the stability of anury formula aircraft.

Above-mentioned fuselage (9) is the totally-enclosed nacelle of hull formula, band hydroplane face, is drops, mean line head section deflection below, and tail partly is partial to the top.

Adjustable wing high mounted wing of the present invention awing, chaufeur has good visual field downwards; When taking off landing, even run-off the straight, wing also is difficult for contacting to earth.The wing of high wing airplane has improved flight stability on full machine center of gravity.Wing can be folding as birds at surface navigation, ground run and when parking, to reduce the space.

Aircraft form of the present invention adopts the anury formula, and major advantage is that resistance is little, in light weight.The major defect of common all-wing aircraft is that manoevreability is relatively poor, stability is also relatively poor, and the take-off and landing ground run distance is longer.Flapping wing aircraft of the present invention adopts the aerofoil control technology, can overcome the shortcoming of common all-wing aircraft.

An above-mentioned left side, starboard wing (5,5 ') control system (6) include flight control bar (58), computing machine (59), attitude sensors (60), flying speed sensor (61), environment temperature sensor (62), ambient atmosphere pressure force gauge (63), flight lifting degree sensor (64), flight sideslip sensor (65), pitch sensor (66), throttle and sensor (67), horizontal side senser (68), hydraulic oil fuel tank (69), thick oil filter (70), smart oil filter (71), isolated pneumatic accumulator (72), unidirectional variable capacity oil pump (73), hydraulic pressure sensor (74), the left and right sides wing luffing electromagnetic valve (52 that shutoff valve (75) and structure are identical, 55), left and right sides wing luffing mechanism (53,56), left and right sides wing luffing sensor (54,57), the left and right sides wing electromagnetic valve (46 that seesaws, 49), the left and right sides wing mechanism (47 that seesaws, 50), the left and right sides wing sensor (48 that seesaws, 51), the left and right sides wing first joint electromagnetic valve (40,43), left and right sides wing first articulation mechanism (41,44), left and right sides wing first joint sensors (42,45), left and right sides wing twist electromagnetic valve (34,37), left and right sides wing twist swing oil motor (35,38), left and right sides wing twist sensor (36,39), left and right sides wing second joint electromagnetic valve (28,31), left and right sides wing second joint mechanism (29,32), left and right sides wing second joint sensor (30,33), as shown in Figure 6.

In addition, the present invention also can be used as amphibious formula except as flight usefulness, the double water device of doing of the fuselage of its aeroboat, and plug-in thing is few, helps the raising of airworthiness.Center of gravity and line of pull are relatively low, and the sliding stability of running is increased, and road-holding property is better, and seakeeping is good.Adopt the four-wheel landing gear of car when use on land and select suitable suspension damper for use, alighting gear can be taken in fuselage and dress landing gear trousers in case of necessity with the water surface aloft.

For the performance that the present invention is used on land and water better, its fuselage (9) head is equipped with preceding hydraulic pressure telescoping spoiler (85), fuselage (9) afterbody is equipped with back hydraulic pressure telescoping spoiler (86), a corresponding left side, starboard wing (5,5 ') control system (6) also include and preceding hydraulic pressure telescoping spoiler (85) bonded assembly before telescoping spoiler electromagnetic valve (79), preceding telescoping spoiler kinematic mechanism (80), before telescoping spoiler sensor (81) and with back hydraulic pressure telescoping spoiler (86) bonded assembly after telescoping spoiler electromagnetic valve (82), back telescoping spoiler kinematic mechanism (83), back telescoping spoiler sensor (84), as shown in Figure 6.

The control system of above-mentioned left and right hydrodynamic force screw propeller (3,4) includes left governor valve (88), left three position four-way electromagnetic valve (89), left two-way fixed displacement oil motor (90), left hydrodynamic force screw propeller (3), left-hand rotation speed sensors (92), right governor valve (93), right three position four-way electromagnetic valve (94), right two-way fixed displacement oil motor (95), right hydrodynamic force screw propeller (4), right-hand rotation speed sensors (91), bearing circle (87), throttle collapse plate (67) and other hydraulic services, as shown in Figure 7.

Above-mentioned safety and life (7) include preceding life saving air bag (10), left back life saving air bag (11), right back life saving air bag (12), main chute (13), drogue chute gun (16), preceding life saving air bag cold high pressure gas cylinder (87), the preceding manual raft door of life saving air bag (194), the preceding manual raft gate control of life saving air bag handle (195), left back life saving air bag cold high pressure gas cylinder (196), the manual raft door of left back life saving air bag (197), the manual raft gate control of left back life saving air bag handle (198), right back life saving air bag cold high pressure gas cylinder (199), the manual raft door of right back life saving air bag (200), the manual raft gate control of right back life saving air bag handle (201), preceding life saving air bag (10), left back life saving air bag (11), right back life saving air bag (12) is packed in fuselage (9) front end and two rear sides respectively, and the manual raft gate control of preceding life saving air bag handle (195) and the manual raft gate control of left back life saving air bag handle (198) and the manual raft gate control of right back life saving air bag handle (201) interlock mutually, as shown in Figure 8.

When the present invention uses, connecting rod (212) is subjected to the seesaw control of mechanism (47) motion of wing luffing mechanism (53) and wing, and all accessory pinna of drivening rod (214), wing first articulation mechanism 41, wing twist swing oil motor 35, connecting rod (219), wing second joint kinematic mechanism 29, connecting rod (221) and wing is done luffing and seesawed around spherical pair 207; A group accessory pinna that the flexible drivening rod (214) of wing first articulation mechanism (41), left wing's torsionoscillation oil motor (35), connecting rod (219), wing second joint kinematic mechanism (29), connecting rod (221) and wing are all and B group accessory pinna rotate around revolute pair (226), in the present embodiment, A group accessory pinna includes accessory pinna (227,228,229,230,231,232,233,234,234,236), and B group accessory pinna includes accessory pinna (237,238,239,240,241,242,243,244,245,246); Half accessory pinna near the A group in the A group accessory pinna of wing twist swing oil motor (35) drivening rod (219), wing second joint kinematic mechanism (29), connecting rod (221), wing and the B group accessory pinna reverses around revolute pair (217), and the A group accessory pinna of second joint kinematic mechanism (29) drivening rod (221) and wing rotates around revolute pair (216).

Under the control of mechanisms such as flight control bar (58), computing machine (59) and each cell sensor, each unit electromagnetic valve, in conjunction with said mechanism, wing can around do luffing around spherical pair (207), seesaw, twisting motion, fore and aft motion.Therefore can change the angle that wing agitates and obtain thrust, carry out aerofoil control, with wingfold etc.

The present invention is when surface navigation and flight, and two hydrodynamic force screw propellers (3,4) propulsion system is used in crowded or tortuous channel navigation, pivot stud and reversing.The throttle plate (67) that collapses is controlled the speed that the flow of left and right sides governor valve (88,93) advances or moves backward with control simultaneously, and the flow that bearing circle (87) is controlled left and right sides governor valve (88,93) respectively turns to control.The hand of spiral of left side hydrodynamic force screw propeller (3) and right hydrodynamic force screw propeller (4) is opposite, and hand of rotation is opposite during propelling.The hand of rotation that each following screw propeller is rotated in the forward direction when pushing ahead for it.

When straight ahead, left side three position four-way electromagnetic valve (89), right three position four-way electromagnetic valve (94) are positioned at the position, a left side of advancing, a left side two-way fixed displacement oil motor (90), left hydrodynamic force screw propeller (3), right two-way fixed displacement oil motor (95), right hydrodynamic force screw propeller (4) are rotated in the forward, and speed of advance is controlled the flow of left governor valve (88), right governor valve (93) simultaneously and controlled by the throttle plate (67) that collapses.

When advancing turning, with the turnon left is example, flow by left governor valve (88) when turning left as bearing circle (87) progressively reduces left two-way fixed displacement oil motor (90) and the reduction of left hydrodynamic force screw propeller (3) rotating speed, flapping-wing flying water automobile is turned left, when bearing circle (87) turns left to reach 45 °, left side governor valve (88) cuts out fully, left side three position four-way electromagnetic valve (89) enters the reversing position when surpassing 45 °, a left side two-way fixed displacement oil motor (90) and left hydrodynamic force screw propeller (3) low speed and reverse, when bearing circle (87) turns left to reach 90 °, a left side two-way fixed displacement oil motor (90) and left hydrodynamic force screw propeller (3) be counter-rotating at full speed, and flapping-wing flying water automobile is with the minor radius sharply turning.Right during this period governor valve (93) is not subjected to the control of bearing circle (87), only is subjected to the collapse control of plate (67) of throttle.

When pivot stud, with flicker to being example, when the water surface stops, when turning left to reach 90 ° as bearing circle (87), left side three position four-way electromagnetic valve (89) enters the reversing position, a left side two-way fixed displacement oil motor (90) and left hydrodynamic force screw propeller (3) are opposite with the hand of rotation of right two-way fixed displacement oil motor (94) and right hydrodynamic force screw propeller (4), and rotating speed equates, realizes pivot stud.

When straight line car-backing, left side three position four-way electromagnetic valve (89), right three position four-way electromagnetic valve (94) enter the right position of reversing, a left side two-way fixed displacement oil motor (90), left hydrodynamic force screw propeller (3), right two-way fixed displacement oil motor (95), right hydrodynamic force screw propeller (4) contrarotation, back-up speed is controlled the flow of left governor valve (88), right governor valve (93) simultaneously and is controlled by the throttle plate (67) that collapses.

When reversing is turned, turning with left side reversing is example, left side three position four-way electromagnetic valve (89), right three position four-way electromagnetic valve (94) enter the right position of reversing, left two-way fixed displacement oil motor (90), left hydrodynamic force screw propeller (3), right two-way fixed displacement oil motor (95), right hydrodynamic force screw propeller (4) contrarotation.Flow by left governor valve (88) when turning left as bearing circle (87) progressively reduces left two-way fixed displacement oil motor (90) and the reduction of left hydrodynamic force screw propeller (3) rotating speed, flapping-wing flying water automobile is turned left, when bearing circle (87) turns left to reach 45 °, left side governor valve (88) cuts out fully, left side three position four-way electromagnetic valve (89) enters advanced potential when surpassing 45 °, a left side two-way fixed displacement oil motor (90) and left hydrodynamic force screw propeller (3) low speed just change, when bearing circle (87) turns left to reach 90 °, a left side two-way fixed displacement oil motor (90) and left hydrodynamic force screw propeller (3) just change at full speed, and flapping-wing flying water automobile is with the minor radius sharply turning of moveing backward.Right during this period governor valve (93) is not subjected to the control of bearing circle (87), only is subjected to the collapse control of plate (67) of throttle.

On open water channel, lake surface and sea, wing can be launched to utilize ground effect to carry out low-latitude flying, can according to circumstances select two kinds of flying methods this moment, and the air flapping wing advances or air double leaf nonuniform pitch propeller advances.Higher or the place ahead of wave flying height that can raise easily when big obstacle is arranged.

The present invention is when ground run, for reducing the lift that ground run produces, the stroke of telescoping spoiler sensor (81), back telescoping spoiler kinematic mechanism (83) improves the ground run performance to increase tire and ground-surface adhesive ability before can regulating as requested.Air double leaf nonuniform pitch propeller is parked on ground when travelling, and the double leaf nonuniform pitch propeller is a feathering, and is horizontal (18) to reduce height and to reduce resistance to motion, as shown in Figure 9.

The fuel system that the present invention uses on ground, driving device, mobile devices, steering hardware, brake equipment, electric equipment etc. are similar to general-utility car, all will meet the requirement of GB, and design by the anti-crash requirement of autogyro.

Safety among the present invention and life (7) comprise organic interior air bag system, aerial parachute life saving system and bikini surface lifesaving gas-bag system.Wherein in the machine air bag system of air bag system and automotive use require identical, mainly on ground, use when the water surface and aerial parachuting.

Drogue chute gun (16) and main chute (13) in the aerial parachute life saving system when the aerial just in case fault that occurs getting rid of, can be penetrated main chute (13) by drogue chute gun (16), send flapping-wing flying water automobile back to ground with the occupant.Be installed on flapping-wing flying water automobile front end and two rear sides during bikini surface lifesaving gas-bag system, use bikini surface lifesaving gas-bag system to can further improve safety performance when falling umbrella in the air simultaneously.

When need use bikini surface lifesaving gas-bag system, can be by chaufeur (96), copilot (97) or occupant (98) pulling be the manual raft gate control of the preceding life saving air bag handle (195) of interlock mutually, the manual raft gate control of left back life saving air bag handle (198), the manual raft gate control of right back life saving air bag handle (201), the high pressure cold of life saving air bag cold high pressure gas cylinder (87) is through the manual raft door of preceding life saving air bag (194) life saving air bag (10) inflation forward before making, the high pressure cold of left back life saving air bag cold high pressure gas cylinder (196) is inflated to left back life saving air bag (11) through the manual raft door of left back life saving air bag (197), the high pressure cold of right back life saving air bag cold high pressure gas cylinder (199) is inflated to right back life saving air bag (12) through the manual raft door of right back life saving air bag (200), as shown in figure 10.

When water surface stormy waves is too big, use the surface lifesaving gas-bag system can increase flotation property.Also can use during parachuting in the air,, improve safety performance to reduce the impact of the ground or the water surface to flapping-wing flying water automobile and occupant.

In addition, the present invention also can be changed to following three kinds of versions:

1, backpack individual flapping wing aircraft: this kind type is light single backpack, can freely circle in the air as bat behind the back.Compare with propeller-parachuting with the hillside gliding parachute, also possess except that the advantage with them following characteristics are arranged, A, the landing place is less demanding to taking off.B, can do various maneuvering flights.C, has better wind resistance characteristic.D, to compare noise very little with propeller-parachuting.To replace the mountain probably and drape over one's shoulders gliding parachute and propeller-parachuting, its military use is very extensive.Its structure as shown in figure 11, there are driving engine (1), autonomous cruise speed system (6), (pneumatic system is arranged when using the inflatable folding wing), cabinet to connect by rod member (267) in the cabinet that bear at the back of chaufeur (96) with accessory pinna compound type folding wing (5) (or inflatable folding wing), cabinet is connected by harness system (268) with chaufeur (96), there is life-saving para chute (12) shirtfront of chaufeur (96), the right hand of chaufeur (96) is possessed joystick (58), and the left hand of chaufeur (96) is possessed throttle control handle and sensor (67).The principle of work of its control system (6), folding wing (5) is identical with the relevant portion of flapping-wing flying water automobile, as shown in figure 11.

2, flapping flight motor bike: characteristics such as motor bike is simple in structure because of having, price is cheap, cross country power and carrying capacity are strong are used widely, but just powerless when running into mountain, river, river, lake, sea.Rotorcycle is plugged dipteron with motor bike and is overcome these difficulties, becomes a kind of really vehicle easily.As shown in figure 12, driving engine (1), control system (6) are equipped with in motor bike (269) inside, accessory pinna compound type folding wing (5) (or inflatable folding wing) is equipped with by rod member (267) in its top, there is life-saving para chute (13) at chaufeur (96) back, chaufeur (96) is connected by safety strap (270) with motor bike (269), the right hand of chaufeur (96) is possessed joystick (58), and the left hand of chaufeur (96) is possessed throttle control handle and sensor (67).The principle of work of its hydraulic efficiency pressure system 6, autonomous cruise speed system (7), folding wing (5) is identical with the relevant portion of flapping-wing flying water automobile, as shown in figure 12.

3, flapping flight automobile, this type organically combines car and flapping-wing aircraft, is fit to the hinterland and uses.Compare fuselage with flapping-wing flying water automobile and be not with hydroplane face and two hydrodynamic force propeller propulsion system, keep other each system and part, thereby the weight saving cost reduces.It is floating to open bikini surface lifesaving gas-bag system when the water surface, advances or air screw propelling lowsteaming available flapping wing mode short take-off and landing with flapping wing.And can utilize the mature technology (light-weight design) of existing car design of part and production, can attract numerous desires to buy the client of cars, cross-country car etc. in conjunction with outstanding moulding, as shown in figure 13.

Embodiment 2:

Structure embodiment of the present invention 1 is identical, difference is an above-mentioned left side, starboard wing (5,5 ') also can be the inflatable folding wing, it is identical with accessory pinna compound type folding wing with machine liquid combination mechanism bonded assembly structure, the inflatable folding wing includes some air chambers of being made up of A group air chamber and B group air chamber, some air chambers are by two-layer resilient plain cotton fabric (26 up and down, 27) surround with each air chamber shim respectively, as shown in figure 16, the air chamber shim of wing front side has only fin (23), all the other each air chamber shims include girt strip (24) and fin (23), and girt strip (24) is thin cone, its diameter is in the root maximum, the tail end minimum, shown in Figure 14-1, connecting rod (221) is connected with the girt strip (24) of wing A group air chamber, connecting rod (214,219) be connected with the B group pairing girt strip of air chamber (24) of wing respectively, and plain cotton fabric (26,27) inboard is connected with fuselage (9), shown in Figure 14-1.A group air chamber includes air chamber (111,115,119,123,127), and B group air chamber includes air chamber (131,135,139,143,147), as shown in figure 16.Each little air chamber charges into the cold air (dry pressurized air) of low pressure reduction (poor with environment atmospheric pressure) during the flapping wing state, so that wing is fluttered.Each little air chamber charged into the cold air (dry pressurized air) of higher differential pressure when screw propeller advanced cruising flight, make wing that good aerodynamic configuration and bigger 1ift-drag ratio be arranged, wing was not to the adjustment of state of flight when do not influence little manoevreability this moment, air-charging and air-discharging system made pressure reduction keep constant the pressure of each little air chamber of automatically regulating when flying height changed.Air-charging and air-discharging system will reduce the pressure of corresponding little air chamber automatically during the high maneuverability flapping flight.After flight finished, the blow off valve of each little air chamber was opened, wing-folding.Same inflatable folding wing aerofoil profile is concave-convex wings when static, the girt strip of being made by composite material (24) is thin cone, its diameter is in girt strip root maximum, the tail end minimum, during flight owing to be subjected to aerodynamic effect tail end K/UP, automatically become the S aerofoil profile, shown in Figure 14-2, to improve the stability of anury formula aircraft.In addition, also formed air chamber (107) between inflatable folding wing and the fuselage (9).

The control system of present embodiment (6) is identical with accessory pinna compound type folding wing, but also be provided with air-charging and air-discharging system, air-charging and air-discharging system includes air intake filter (99), air compressor (100), main road filter (101), storage tank (102), shutoff valve (104), pneumatic baroceptor (103), check valve (105) and two groups of structures that are attached thereto are identical, left and right sides wing (5,5 ') several air chambers (107 of all having respectively, 111,115,119,123,127,131,135,139,143,147), several air chamber air inlet electromagnetic valves (106,110,114,118,122,126,130,134,138,142,146), several air chamber exhaust solenoid valves (108,112,116,120,124,128,132,136,140,144,148), several air chamber baroceptor (109,113,117,121,125,129,133,137,141,145,149), as shown in figure 15.

When the present invention prepares flapping wing and takes off, pneumatic system is started working, air enters air compressor (100) by air intake filter (99) and enter storage tank (102) behind main road filter (101) filtering moisture and greasy dirt, portion gas enters pneumatic baroceptor (103) through shutoff valve (104), sensor signal is sent into computing machine (59) through sensor bus (78), and check valve (105) prevents that gas oppositely enters gas supply system in each unit.The air inlet electromagnetic valve of each air chamber is opened, the detection data of the baroceptor of each air chamber are sent into computing machine (59) through sensor bus (78), whether the air pressure that computing machine (59) is analyzed each air chamber reaches specified value, as reach then and control each air chamber closed electromagnetic valve respectively by electromagnetic valve bus (77), the beginning flapping wing takes off and flies.When needs air double leaf displacement air double leaf nonuniform pitch propeller (2) advances flight, computing machine (59) is controlled each air chamber electromagnetic valve respectively by electromagnetic valve bus (77) and is opened and closed and adjust pressure, makes the inflatable folding wing that aerodynamic configuration be arranged preferably and improves airworthiness.Ambient atmosphere pressure force gauge (63) detected the signal that pressure reduces and sends into computing machine (59) through sensor bus (78) when flying height increased, and computing machine (59) is controlled each air chamber exhaust solenoid valve respectively by electromagnetic valve bus (77) and opened and adjust pressure just the pressure reduction maintenance of each air chamber and environment atmospheric pressure is constant.

Under the control of flight control bar (58), computing machine (59), each cell sensor, each unit electromagnetic valve, mechanism, in conjunction with hydraulic gear and pneumatic system, wing can be done luffing around spherical pair (207), seesaws, twisting motion, fore and aft motion.Therefore can change the angle that wing agitates and obtain thrust, carry out aerofoil control, with wingfold etc.

Claims (10)

1, a kind of flapping-wing flying water automobile, include driving engine (1), air double leaf nonuniform pitch propeller (2), a left side, right hydrodynamic force screw propeller (3,4), a left side, starboard wing (5,5 '), control system (6), safety and life (7), four-wheel landing gear and suspension damper (8), fuselage (9), driving engine (1) wherein, control system (6), safety and life (7) all place in the fuselage (9), air double leaf nonuniform pitch propeller (2) is installed in the afterbody of fuselage (9), left side hydrodynamic force screw propeller (3) and right hydrodynamic force screw propeller (4) are installed in the both sides of fuselage (9) respectively, wing (5) is installed in the top of fuselage (9), four-wheel landing gear and suspension damper (8) are installed in the two bottom sides of fuselage (9), it is characterized in that wing (5) is connected with fuselage (9) by machine liquid combination mechanism.

2, flapping-wing flying water automobile according to claim 1, it is characterized in that an above-mentioned left side, starboard wing (5,5 ') be that structure is identical, and symmetry is connected the accessory pinna compound type folding wing of fuselage (9), include A group accessory pinna, B group accessory pinna and the machine liquid combination mechanism that is attached thereto, wherein A group accessory pinna and B group accessory pinna include some accessory pinnas again respectively, machine liquid combination mechanism includes connecting rod (212), connecting rod (214), connecting rod (219), connecting rod (221), piston rod (205), piston rod (209), piston rod (215), piston rod (220), piston cylinder (204), piston cylinder (211), piston cylinder (213), piston cylinder (218), connecting rod (212) connects to form spherical pair (207) by frame (202) and fuselage (9), connect to form spherical pair (208) with an end of piston rod (209), connect to form spherical pair (206) with an end of piston rod (205), connect to form revolute pair (222) with piston cylinder (213), connect to form revolute pair (226) with connecting rod (214); The other end of piston rod (205) places in the piston cylinder (204), forms wing luffing mechanism (53), and forms spherical pair (203) with frame (202); The other end of piston rod (209) places in the piston cylinder (211), forms the wing mechanism (47) that seesaws, and forms spherical pair (210) with frame (202); Piston rod (215) places composition wing first articulation mechanism (41) in the piston cylinder (213), forms revolute pair (223) with connecting rod (214); Connecting rod (214) connects to form revolute pair (217) with connecting rod (219), and as wing twist swing oil motor (35); Connecting rod (219) connects to form revolute pair (224) with piston cylinder (218), and form revolute pair (216) with member (221), piston rod (220) places forms wing second joint kinematic mechanism (29) in the piston cylinder (218), and form revolute pair (216) with connecting rod (221), connecting rod (221) is connected with the A group accessory pinna of wing, and connecting rod (214,219) is connected with the B group accessory pinna of wing respectively.

3, flapping-wing flying water automobile according to claim 2, it is characterized in that above-mentioned accessory pinna does camber, wherein contain plumage beam (20), middle part, its cross sectional shape vertical with plumage beam (20) at accessory pinna are S shape, and plumage beam (20) is thin cone, and its diameter is in accessory pinna root maximum, tail end minimum, two-layer up and down resilient plain cotton fabric (26,27) is connected with the root of all plumage beams (20) of A group accessory pinna and B group accessory pinna, and plain cotton fabric (26,27) is connected with fuselage (9).

4, flapping-wing flying water automobile according to claim 1 is characterized in that the totally-enclosed nacelle of above-mentioned fuselage (9) for hull formula, band hydroplane face, is drops, mean line head section deflection below, and tail partly is partial to the top.

5, flapping-wing flying water automobile according to claim 1 is characterized in that an above-mentioned left side, starboard wing (5,5 ') control system (6) include flight control bar (58), computing machine (59), attitude sensors (60), flying speed sensor (61), environment temperature sensor (62), ambient atmosphere pressure force gauge (63), flight lifting degree sensor (64), flight sideslip sensor (65), pitch sensor (66), throttle and sensor (67), horizontal side senser (68), hydraulic oil fuel tank (69), thick oil filter (70), smart oil filter (71), isolated pneumatic accumulator (72), unidirectional variable capacity oil pump (73), hydraulic pressure sensor (74), the left and right sides wing luffing electromagnetic valve (52) that shutoff valve (75) and structure are identical, wing luffing mechanism (53), wing luffing sensor (54), the wing electromagnetic valve (46) that seesaws, the wing mechanism (47) that seesaws, the wing sensor (48) that seesaws, the wing first joint electromagnetic valve (40), wing first articulation mechanism (41), wing first joint sensors (42), wing twist electromagnetic valve (34), wing twist swing oil motor (35), wing twist sensor (36), wing second joint electromagnetic valve (28), wing second joint mechanism (29), wing second joint sensor (30).

6, flapping-wing flying water automobile according to claim 1, it is characterized in that an above-mentioned left side, starboard wing (5,5 ') also can be the inflatable folding wing, it is identical with accessory pinna compound type folding wing with machine liquid combination mechanism bonded assembly structure, the inflatable folding wing includes some air chambers of being made up of A group air chamber and B group air chamber, some air chambers are by two-layer resilient plain cotton fabric (26 up and down, 27) surround with each air chamber shim respectively, the air chamber shim of wing front side has only fin (23), all the other each air chamber shims include girt strip (24) and fin (23), and girt strip (24) is thin cone, its diameter is in the root maximum, the tail end minimum, connecting rod (221) is connected with the girt strip (24) of wing A group air chamber, connecting rod (214,219) be connected with the B group pairing girt strip of air chamber (24) of wing respectively, and plain cotton fabric (26,27) inboard is connected with fuselage (9).

7, flapping-wing flying water automobile according to claim 6, it is characterized in that above-mentioned inflatable folding wing also includes air-charging and air-discharging system, its control system (6) is identical with accessory pinna compound type folding wing, and air-charging and air-discharging system includes air intake filter (99), air compressor (100), main road filter (101), storage tank (102), shutoff valve (104), pneumatic baroceptor (103), check valve (105) and two groups of structures that are attached thereto are identical, left and right sides wing (5,5 ') several air chambers (107 of all having respectively, 111,115,119,123,127,131,135,139,143,147), several air chamber air inlet electromagnetic valves (106,110,114,118,122,126,130,134,138,142,146), several air chamber exhaust solenoid valves (108,112,116,120,124,128,132,136,140,144,148), several air chamber baroceptor (109,113,117,121,125,129,133,137,141,145,149).

8, according to claim 1 or 2 or 3 or 4 or 5 or 6 or 7 described flapping-wing flying water automobiles, it is characterized in that above-mentioned fuselage (9) head also is equipped with preceding hydraulic pressure telescoping spoiler (85), fuselage (9) afterbody is equipped with back hydraulic pressure telescoping spoiler (86), correspondingly a left side, starboard wing (5,5 ') control system (6) also include and preceding hydraulic pressure telescoping spoiler (85) bonded assembly before telescoping spoiler electromagnetic valve (79), preceding telescoping spoiler kinematic mechanism (80), before telescoping spoiler sensor (81) and with back hydraulic pressure telescoping spoiler (86) bonded assembly after telescoping spoiler electromagnetic valve (82), back telescoping spoiler kinematic mechanism (83), back telescoping spoiler sensor (84).

9, flapping-wing flying water automobile according to claim 8, the control system that it is characterized in that above-mentioned left and right hydrodynamic force screw propeller (3,4) include left governor valve (88), left three position four-way electromagnetic valve (89), left two-way fixed displacement oil motor (90), left hydrodynamic force screw propeller (3), left-hand rotation speed sensors (92), right governor valve (93), right three position four-way electromagnetic valve (94), right two-way fixed displacement oil motor (95), right hydrodynamic force screw propeller (4), right-hand rotation speed sensors (91), bearing circle (87), throttle collapse plate (67) and other hydraulic services.

10, flapping-wing flying water automobile according to claim 9, it is characterized in that above-mentioned safety and life (7) comprise organic in air bag system, aerial parachute life saving system and bikini surface lifesaving gas-bag system, wherein in the machine air bag system of air bag system and automotive use require identical; Aerial parachute life saving system includes main chute (13), drogue chute gun (16); Bikini surface lifesaving gas-bag system includes preceding life saving air bag (10), left back life saving air bag (11), right back life saving air bag (12), preceding life saving air bag cold high pressure gas cylinder (87), the preceding manual raft door of life saving air bag (194), the preceding manual raft gate control of life saving air bag handle (195), left back life saving air bag cold high pressure gas cylinder (196), the manual raft door of left back life saving air bag (197), the manual raft gate control of left back life saving air bag handle (198), right back life saving air bag cold high pressure gas cylinder (199), the manual raft door of right back life saving air bag (200), preceding life saving air bag (10), left back life saving air bag (11), right back life saving air bag (12) is packed in the inside of fuselage (9) front end and two rear sides respectively, and the manual raft gate control of preceding life saving air bag handle (195) and the manual raft gate control of left back life saving air bag handle (198) and the manual raft gate control of right back life saving air bag handle (201) interlock mutually.

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