CN101927825A

CN101927825A - Single aircraft

Info

Publication number: CN101927825A
Application number: CN2009101689487A
Authority: CN
Inventors: 龙川
Original assignee: Individual
Current assignee: Individual
Priority date: 2008-09-05
Filing date: 2009-09-02
Publication date: 2010-12-29
Also published as: CN101353084A

Abstract

The invention relates to a single aircraft. The single aircraft comprises a control cabin, a bypass fan propulsion system, bypass stub wings, airfoils, empennages or canards, wherein the base of the control cabin is a capsule; the front side of the capsule is provided with a capsule door, and the head of the capsule is provided with a capsule cover; the whole aircraft is vertically upward when vertically taking off and landing, and a pilot correspondingly stands in the control cabin; the whole aircraft is horizontally forward when horizontally flying, and the pilot correspondingly lies flat on the stomach in the control cabin; the bypass fan propulsion system is arranged on both sides of the control cabin through the bypass stub wings; the bypass fan propulsion system comprises an engine positioned inside an engine cabin, a clutch, a speed reducer, a supporting bypass commutator segment and a fan positioned in a bypass; the engine drives the fan to rotate so as to generate power; and the airfoils, horizontal empennages or X-shaped empennages control the transformation of vertical taking off and landing and horizontal flying. Because of the structure, the single aircraft realizes the vertical taking off and landing and high-speed flying and can stably transform between a vertical state and a horizontal state.

Description

Individual lift device

Technical field

The present invention relates to aircraft, particularly a kind of can vertical takeoff and landing (VTOL) and the individual lift device of high-speed flight.

Background technology

The individual lift device kind of prior art is a lot, the individual lift device SOLOTREK-XFV of American Michael. Mo Xier development for example, this aircraft drives two tool ducted fans by a piston engine and produces lift pulling aircraft takeoff, but this aircraft does not have wing, whole flight course all drives ducted fan by driving engine and produces lifting flight, and speed is slow, voyage is near, cruise duration is short.Her husband of Swiss. the individual lift device " the flying power wing " of Luo Xi development is made of a pair of folding wing and fixing under the wings of an airplane 4 turbojet engines, the driver is fixed on back to " the flying power wing ", jump off from aircraft just in high-altitude flight, the unfolded wing also starts the turbojet engine jet flight, landing at last releases a parachute, " the flying power wing " is though there is wing can produce lift when flight, use the jet promotion of turbojet engine simultaneously, the flying speed height, but can only take off vertical takeoff and landing (VTOL) on the ground from just jumping off at the aircraft of airflight.

In sum, the deficiency of existing individual lift device technology existence is: can not take into account vertical takeoff and landing (VTOL) and high-speed flight.

Summary of the invention

The objective of the invention is provides a kind of and can take into account vertical takeoff and landing (VTOL) and high-speed flight in order to overcome the prior art above shortcomings, and can be at the individual lift device of the two smooth conversion.

The present invention is achieved by the following technical solutions, and promptly a kind of individual lift device comprises driving compartment, ducted fan propulsion system, duct short limb, wing, empennage or canard, it is characterized in that:

1) described driving compartment is positioned at the aircraft middle part, the driving compartment basis is the cabin body, body front, cabin has hatch door, head is a hatchcover, aircraft is whole during the aircraft vertical takeoff and landing (VTOL) is attitude straight up, chaufeur is corresponding to be stood in the driving compartment, and aircraft integral body is level attitude forward during the aircraft horizontal flight, and chaufeur is corresponding prostrate in driving compartment;

2), described ducted fan propulsion system is positioned at the driving compartment both sides, the ducted fan propulsion system comprises, be positioned at the driving engine of machinery space, power-transfer clutch, retarder, the riser bar of support duct, be positioned at the fan of duct, wherein the axis of the fan shaft of fan is parallel with the longitudinal axis of aircraft, and from birds-eye view, the line between two fan shaft axle center overlaps with the lateral axis of aircraft;

3), described wing is the trapezoidal straight wing that is positioned at both sides, driving compartment middle part, this wing passes the machinery space middle part and the one section length that can produce enough lift when level cruise is flown that stretches out, the trailing edge of one section wing between driving compartment and the machinery space has wing flap, one section trailing edge outside the machinery space has aileron, between the afterbody of both sides machinery space and driving compartment afterbody, all have the tailplane of forming by horizontal stabilizer and elevating rudder, all have the vertical tail of forming by fixed fin and yaw rudder at the positive back side of the afterbody of both sides machinery space; When aircraft will be converted to horizontal flight by hovering, the angular deflection forward of the elevating rudder of tailplane; Aircraft is up to the standard, and elevating rudder reset after the attitude;

Or 4), described wing is the trapezoidal straight wing that is positioned at both sides, driving compartment middle part, wing passes the machinery space middle part and the one section length that can produce enough lift when level cruise is flown that stretches out, the trailing edge of one section wing between driving compartment and the machinery space has wing flap, one section trailing edge outside the machinery space has aileron, the radiation of driving compartment afterbody is equipped with the X-shaped empennage of being made up of X-shaped stabilator and X-shaped rudder face, and guarantees that each face X-shaped empennage all has sufficient length to be exposed in the slip-stream of ducted fan generation; When aircraft will be converted to horizontal flight by hovering, the X-shaped rudder face angular deflection forward on the X-shaped empennage; Aircraft is up to the standard, and the X-shaped rudder face resets after the attitude;

Or 5), described wing is the double delta wing that is arranged in the driving compartment two sides of tail, this wing passes the machinery space afterbody and stretches out one section length that can produce enough lift when level cruise is flown, the trailing edge of one section wing between driving compartment and the machinery space has wing flap, one section trailing edge outside the machinery space has elevon, the back side in Vehicle nose has canard, all has the vertical tail of being made up of fixed fin and yaw rudder at the positive back side of the afterbody of both sides machinery space; When aircraft will be converted to horizontal flight by hovering, the angular deflection forward of the wing flap of double delta wing and elevon; Aircraft is up to the standard, and wing flap and elevon reset after the attitude;

Or 6), described wing is the delta wing that is positioned at both sides, driving compartment middle part, this wing passes the afterbody and the one section length that can produce enough lift when level cruise is flown that stretches out in the machinery space, the trailing edge of one section wing between driving compartment and the machinery space has wing flap, one section trailing edge outside the machinery space has elevon, all has the vertical tail of being made up of fixed fin and yaw rudder at the positive back side of the afterbody of both sides machinery space; When aircraft will be converted to horizontal flight by hovering, elevon is angular deflection forward; Aircraft is up to the standard, and elevon resets after the attitude.

The advantage that the present invention has owing to said structure is conspicuous: can vertical takeoff and landing (VTOL) and high-speed flight, simultaneously plumbness with flat fly to change mutually between the state very steady.

Description of drawings

The example of the indefiniteness that said structure of the present invention can provide by accompanying drawing further specifies.

Fig. 1 is a normal conventional layout Facad structure scheme drawing of the present invention;

Fig. 2 is a normal conventional layout of the present invention back side semi-sictional view structural representation;

Fig. 3 is the structure enlarged diagram of A among Fig. 2;

Fig. 4 is a normal conventional layout cockpit structure scheme drawing of the present invention;

Fig. 5 is that normal conventional layout of the present invention takes off vertically and the floating state structural representation;

Fig. 6 flies the status architecture scheme drawing before the normal conventional layout of the present invention;

Fig. 7 is an X empennage normal arrangement Facad structure scheme drawing of the present invention;

Fig. 8 is that X empennage of the present invention normal arrangement is taken off vertically and the floating state structural representation;

Fig. 9 flies the status architecture scheme drawing before the X empennage of the present invention normal arrangement;

Figure 10 is a canard configuration Facad structure scheme drawing of the present invention;

Figure 11 is a canard configuration structure scheme drawing of the present invention;

Figure 12 is that canard configuration of the present invention takes off vertically and the floating state structural representation;

Figure 13 flies the status architecture scheme drawing before the canard configuration of the present invention;

Figure 14 is an anury delta wing layout Facad structure scheme drawing of the present invention;

Figure 15 is that anury delta wing layout of the present invention takes off vertically and the floating state structural representation;

Figure 16 flies the status architecture scheme drawing before the anury delta wing layout of the present invention.

Among the figure: 1, cabin body; 2, hatch door; 3, hatchcover; 4A, trapezoidal straight wing; 4B, double delta wing; 4C, delta wing; 5, wing flap; 6A, aileron; 6B, elevon; 7, machinery space; 8, duct; 9, fan; 10, riser bar; 11, fairing; 12, horizontal stabilizer; 13, elevating rudder; 14, fixed fin; 15, yaw rudder; 16, energy disperser; 17, pillar; 18, wheel; 19, duct short limb; 20, parachute compartment; 21, coordinate axle; 22, universal-joint; 23, adapter shaft; 24, gear pair; 25, conical gear; 26, fan shaft; 27, retarder; 28, power-transfer clutch; 29, driving engine; 30, handle; 31, jociey stick; 32, health Tobe; 33, pedal; 34, height regulating rod; 35, airstair; 36, rectangular recess; 37, X type stabilator; 38, X type rudder face; 39, canard; 40, canard attaching parts.

The specific embodiment

The invention will be further described below in conjunction with drawings and Examples:

Embodiment one, referring to accompanying

drawing

1,2,3,4,5, with 6 in the individual lift device of normal conventional layout, comprise driving compartment, the ducted fan propulsion system, duct short limb 19, wing 4A, tailplane and vertical tail, it is characterized in that: described driving compartment is positioned at the aircraft middle part, the driving compartment basis is a cabin body 1, body 1 front in cabin has hatch door 2, head is a hatchcover 3, aircraft is whole during the aircraft vertical takeoff and landing (VTOL) is attitude straight up, chaufeur is corresponding to be stood in the driving compartment, and aircraft integral body is level attitude forward during the aircraft horizontal flight, and chaufeur is corresponding prostrate in driving compartment; Described ducted fan propulsion system is positioned at the driving compartment both sides, the ducted fan propulsion system comprises the driving engine 29 that is positioned at machinery space 7, power-transfer clutch 28, retarder 27, support the riser bar 10 of duct, wherein the axis of the fan shaft 26 of fan 9 is parallel with the longitudinal axis of aircraft, and from birds-eye view, the line between the axle center of two fan shafts 26 overlaps with the lateral axis of aircraft; Described wing is the trapezoidal straight wing 4A that is positioned at both sides, driving compartment 1 middle part, this wing passes machinery space 7 middle parts and stretches out one section length that can produce enough lift when level cruise is flown, one section trailing edge between driving compartment and the machinery space has wing flap 5, one section trailing edge outside the machinery space has aileron 6A, between the afterbody of both sides machinery space and driving compartment afterbody, all have the tailplane of forming by horizontal stabilizer 12 and elevating rudder 13, all have the vertical tail of forming by fixed fin 14 and yaw rudder 15 at the positive back side of the afterbody of both sides machinery space; When aircraft will be converted to horizontal flight by hovering, the angular deflection forward of the elevating rudder of tailplane; Aircraft is up to the standard, and elevating rudder reset after the attitude.

In the above-mentioned normal conventional layout individual lift device, described ducted fan propulsion system is installed in the both sides of driving compartment by duct short limb 19; Be installed between the fan shaft 26 of fan 9 of ducted fan propulsion system of driving compartment both sides and have the synchronous transmission mechanism of power, be to coordinate axle 21 in the middle of the synchronous transmission mechanism of described power, that coordinates axle 21 both sides symmetries is furnished with universal-joint 22, this universal-joint outwards has adapter shaft 23, described adapter shaft passes duct short limb 19 and riser bar 10, by gear pair 24 and conical gear 25 engagements that are installed on the fan shaft 26, make the rotating speed of both sides fan 9 keep identical, and make when a side driving engine and hinder for some reason when quitting work, the opposite side live engine can carry out the synchronous transmission of power by the synchronous transmission mechanism of power, and aircraft can be force-landed safely; At this moment, the power-transfer clutch of sick engine one side is disconnected, with the load of the driving engine that reduces the opposite side normal operation; The setting angle of both sides fan 9 is opposite, and hand of rotation is also opposite, and the anti-torsion that both sides fan rotation is produced is cancelled out each other, and does not produce spin when making aircraft hovering; The section of described riser bar 10 is single protruding aerofoil profile, the number of sheets and fan 9 are identical or be multiple, setting angle is opposite with fan 9, make the slip-stream of the fan race rotation of being divided by, linearly discharge, and join with both sides duct short limb 19 in the both sides duct 8 and be two leaf riser bars, the 10 maximum ga(u)ge places that two straight lines install respectively and have living space to hold adapter shaft 23; Described fixed fin 14 ends have energy disperser 16, pillar 17 and wheel 18, on the ground by the wheel on four fixed fins 14 18 stable support aircraft; Described driving compartment size appropriateness can be stood with the satisfied normal adult of an idiotype and wherein be driven; The aerofoil profile of described wing 4A is plano-convex aerofoil profile or asymmetric biconvex aerofoil profile; Have parachute compartment 20 at the back side of driving compartment head, there is parachute the inside, in order to force-landing with parachute when aircraft runs out of steam; Described driving engine 29 is piston engine or propeller turbine or turboaxle motor.

The inner bottom of the driving compartment 1 in the said structure is provided with airstair 35; Airstair 35 tops have rectangular recess 36; Rectangular recess 36 both sides have the pedal 33 on height regulating rod 34 and the height regulating rod 34; Be provided with health Tobe 32 and jociey stick 31 according to organization of human body at driving compartment 1 inwall; The axle head of fan shaft 26 has fairing 11; Middle part, the back side at driving compartment is provided with handle 30.

Said structure is after like this work----driver enters cabin body 1 by airstair 35, and pin stands on the pedal 33 by height regulating rod 34 health is adjusted to conveniently operate the joystick 31 position of hand, with the health Tobe health is fixed in the cabin body 1.Airstair 35 is kept well in the rectangular recess 36 that is placed between two legs, hatch door 2 and hatchcover 3 are tightly locked, observe by hatchcover 3, when taking off vertically, the driver stand in the driving compartment, by wing flap 5 and the aileron 6A backward angular deflection (be equivalent to make the wing of plano-convex aerofoil profile or asymmetric biconvex aerofoil profile eliminate sinuousness) of maneuvering system with wing 4A; Start the engine 29 then, the power of driving engine is by power-transfer clutch 28 and retarder 27, pass to fan 9, fan 9 high speed revolutions produce downward slip-stream, overcome aircraft gravity, and aircraft is pulled away from ground, though wing is blown in ducted fan slip-stream at this moment, but wing has lost sinuousness relatively, and the aerodynamic force of wing front and back is offset, and aircraft is translation and aloft hovering backward not; When aircraft will be converted to horizontal flight by hovering, elevating rudder 13 angular deflection forward of tailplane, the slip-stream of the ducted fan of flowing through makes tailplane generation moment backward, make aircraft tilt forward around transverse axis, corresponding ducted fan also tilts forward, a part that produces in lift component backward is offset aircraft forward, also corresponding the leaning forward of wing 4A this moment, at this moment wing flap 5 and aileron 6A are resetted, make wing recover sinuousness, the slip-stream of ducted fan makes will produce the lift that a part makes progress in the aerodynamic force that produces on the wing, along with aircraft moves forward more and more sooner, the angle of attack is also more and more littler, wing 4A will produce bigger lift gradually, strengthen this trend, the suffered gravity of aircraft will be transferred to wing 4A fully from ducted fan and bear, ducted fan promote aircraft realize the high speed horizontal flight (at this moment chaufeur prostrate driving, the health of chaufeur is being born in 32 holders of health Tobe), elevating rudder 13 reset simultaneously, after the horizontal flight, aircraft is by aileron 6A, and tailplane and vertical tail are handled; Landing process and take-off process contrary.When aircraft aloft floating state need distinguish backward skew, skew left, skew to the right, lift-over left, during lift-over to the right, by to the aircraft tailplane, the control respectively of vertical tail and aileron 6A can realize.When park on ground, hold handle 30 by the people and pass through wheel 18 at the mobile aircraft of ground-surface rolling.

Embodiment two, individual lift device referring to the X empennage normal arrangement in accompanying

drawing

7,8 and 9, comprise driving compartment, ducted fan propulsion system, duct short limb 19, wing 4A and X empennage, it is characterized in that: described driving compartment is positioned at the aircraft middle part, the basis of driving compartment is a cabin body 1, body 1 front in cabin has hatch door 2, head is a hatchcover 3, aircraft is whole during the aircraft vertical takeoff and landing (VTOL) is attitude straight up, chaufeur is corresponding to be stood in the driving compartment, aircraft integral body is level attitude forward during the aircraft horizontal flight, and chaufeur is corresponding prostrate in driving compartment; Described ducted fan propulsion system is positioned at the driving compartment both sides, the ducted fan propulsion system comprises the driving engine 29 that is positioned at machinery space 7, power-transfer clutch 28, retarder 27, support the riser bar 10 of duct, be positioned at the fan 9 of duct 8, wherein the axis of the fan shaft 26 of fan 9 is parallel with the longitudinal axis of aircraft, from birds-eye view, the line between the axle center of two fan shafts 26 overlaps with the lateral axis of aircraft; Described wing is the trapezoidal straight wing 4A that is positioned at both sides, driving compartment middle part, this wing passes machinery space 7 middle parts and stretches out one section length that can produce enough lift when level cruise is flown, the radiation of driving compartment afterbody is equipped with the X-shaped empennage of being made up of X-shaped stabilator 37 and X-shaped rudder face 38, and guarantee that each face X-shaped empennage all has sufficient length to be exposed in the slip-stream of ducted fan generation, when aircraft will be converted to horizontal flight by vertical takeoff, X-shaped rudder face 38 angular deflection forward on the X-shaped empennage; Aircraft is up to the standard, and X-shaped rudder face 38 resets after the attitude.

In the above-mentioned X empennage normal arrangement individual lift device, described ducted fan propulsion system is installed in the both sides of driving compartment by duct short limb 19; Be installed between the S. A. 26 of fan 9 of ducted fan propulsion system of driving compartment both sides and have the synchronous transmission mechanism of power, be to coordinate axle 21 in the middle of the synchronous transmission mechanism of described power, that coordinates axle 21 both sides symmetries is furnished with universal-joint 22, this universal-joint outwards has adapter shaft 23, described adapter shaft passes duct short limb 19 and riser bar 10, by gear pair 24 and conical gear 25 engagements that are installed on the fan shaft 26, make the rotating speed of both sides fan 9 keep identical, and make when a side driving engine and hinder for some reason when quitting work, the opposite side live engine can carry out the synchronous transmission of power by the synchronous transmission mechanism of power, and aircraft can be force-landed safely; At this moment, the power-transfer clutch of sick engine one side is disconnected, with the load of the driving engine that reduces the opposite side normal operation; The setting angle of both sides fan 9 is opposite, and hand of rotation is also opposite, and the anti-torsion that both sides fan rotation is produced is cancelled out each other, and does not produce spin when making aircraft hovering; The section of described riser bar 10 is single protruding aerofoil profile, and the number of sheets and fan 9 are identical or be multiple, and setting angle is opposite with fan 9, makes the slip-stream of the fan race rotation of being divided by, and linearly discharges; And in both sides duct 8, join and be two leaf riser bars, the 10 maximum ga(u)ge places that two straight lines install respectively and have living space to hold adapter shaft 23 with both sides duct short limb 19; Described X stabilator 37 ends have energy disperser 16, pillar 17 and wheel 18, on the ground by the wheel on four X stabilators 37 18 stable support aircraft; Described driving compartment size appropriateness can be stood with the satisfied normal adult of an idiotype and wherein be driven; The aerofoil profile of described wing 4A is plano-convex aerofoil profile or asymmetric biconvex aerofoil profile; Have parachute compartment 20 at the back side of driving compartment head, there is parachute the inside, in order to force-landing with parachute when aircraft runs out of steam; Described driving engine 29 is piston engine or propeller turbine or turboaxle motor.

The inner bottom of the driving compartment in the said structure is provided with airstair 35; Airstair 35 tops have rectangular recess 36; Rectangular recess 36 both sides have the pedal 33 on height regulating rod 34 and the height regulating rod 34; Be provided with health Tobe 32 and jociey stick 31 according to organization of human body at driving compartment 1 inwall; The axle head of fan shaft 26 has fairing 11; Middle part, the back side at driving compartment is provided with handle 30.

Said structure is after like this work----driver enters cabin body 1 by airstair 35, and pin stands on the pedal 33 by height regulating rod 34 health is adjusted to conveniently operate the joystick 31 position of hand, with health Tobe 32 health is fixed in the cabin body 1.Airstair 35 is kept well in the rectangular recess 36 that is placed between two legs, hatch door 2 and hatchcover 3 are tightly locked, observe by hatchcover 3, when taking off vertically, the driver stand in the driving compartment, by wing flap 5 and the aileron 6A backward angular deflection (be equivalent to make the wing of plano-convex aerofoil profile or asymmetric biconvex aerofoil profile eliminate sinuousness) of maneuvering system with wing 4A; Start the engine 29 then, the power of driving engine is by power-transfer clutch 28 and retarder 27, pass to fan 9, fan 9 high speed revolutions produce downward slip-stream, overcome aircraft gravity, and aircraft is pulled away from ground, though wing 4A is blown in ducted fan slip-stream at this moment, but wing 4A has lost sinuousness relatively, and the aerodynamic force of wing front and back is offset, and aircraft is translation and aloft hovering backward not; When aircraft will be converted to horizontal flight by hovering, X-shaped rudder face 38 angular deflection forward on the X-shaped empennage, the slip-stream of the ducted fan of flowing through makes X-shaped empennage generation moment backward, make aircraft tilt forward around transverse axis, corresponding ducted fan also tilts forward, a part that produces in lift component backward is offset aircraft forward, also corresponding the leaning forward of wing 4A this moment, at this moment wing flap 5 and aileron 6A are resetted, make wing recover sinuousness, the slip-stream of ducted fan makes will produce the lift that a part makes progress in the aerodynamic force that produces on the wing, along with aircraft moves forward more and more sooner, the angle of attack is also more and more littler, wing 4A will produce bigger lift gradually, strengthen this trend, the suffered gravity of aircraft will be transferred to wing 4A fully from ducted fan and bear, ducted fan promote aircraft realize the high speed horizontal flight (at this moment chaufeur prostrate driving, the health of chaufeur is being born in 32 holders of health Tobe), X-shaped rudder face 38 resets simultaneously, after the horizontal flight, aircraft is handled by the X-shaped empennage; Landing process and take-off process contrary.When aircraft aloft floating state need distinguish backward skew, skew left, skew to the right, lift-over left during lift-over to the right, can realize by the control to the X-shaped empennage.When park on ground, hold handle 30 by the people and pass through wheel 18 at the mobile aircraft of ground-surface rolling.

Embodiment three, individual lift device referring to canard configuration in accompanying

drawing

10,11,12 and 13, comprise driving compartment, ducted fan propulsion system, duct short limb 19, wing 4B, canard 39 and vertical tail, it is characterized in that: described driving compartment is positioned at the aircraft middle part, the basis of driving compartment is a cabin body 1, body 1 front in cabin has hatch door 2, head is a hatchcover 3, aircraft is whole during the aircraft vertical takeoff and landing (VTOL) is attitude straight up, chaufeur is corresponding to be stood in the driving compartment, aircraft integral body is level attitude forward during the aircraft horizontal flight, and chaufeur is corresponding prostrate in driving compartment; Described ducted fan propulsion system is positioned at the driving compartment both sides, the ducted fan propulsion system comprises the driving engine 29 that is positioned at machinery space 7, power-transfer clutch 28, retarder 27, support the riser bar 10 of duct, be positioned at the fan 9 of duct 8, wherein the axis of the fan shaft 26 of fan 9 is parallel with the longitudinal axis of aircraft, from birds-eye view, the line between the axle center of two fan shafts 26 overlaps with the lateral axis of aircraft; Described wing is the double delta wing 4B that is arranged in the driving compartment two sides of tail, this wing passes machinery space 7 afterbodys and stretches out one section length that can produce enough lift when level cruise is flown, one section trailing edge between driving compartment and the machinery space has wing flap 5, one section trailing edge outside the machinery space has elevon 6B, have canard 39 at the back side of Vehicle nose, all have the vertical tail of forming by fixed fin 14 and yaw rudder 15 at the positive back side of the afterbody of both sides machinery space; When aircraft will be converted to horizontal flight by vertical takeoff, the aileron 5 of double delta wing 4B and elevon 6B angular deflection forward; Aircraft is up to the standard, and aileron 5 and elevon 6B reset after the attitude.

In the above-mentioned canard configuration individual lift device, described ducted fan propulsion system is installed in the both sides of driving compartment by duct short limb 19; Be installed between the S. A. 26 of fan 9 of ducted fan propulsion system of driving compartment both sides and have the synchronous transmission mechanism of power, be to coordinate axle 21 in the middle of the synchronous transmission mechanism of described power, that coordinates axle 21 both sides symmetries is furnished with universal-joint 22, this universal-joint outwards has adapter shaft 23, described adapter shaft passes duct short limb 19 and riser bar 10, by gear pair 24 and conical gear 25 engagements that are installed on the fan shaft 26, make the rotating speed of both sides fan 9 keep identical, and make when a side driving engine and hinder for some reason when quitting work, the opposite side live engine can carry out the synchronous transmission of power by the synchronous transmission mechanism of power, and aircraft can be force-landed safely; At this moment, the power-transfer clutch of sick engine one side is disconnected, with the load of the driving engine that reduces the opposite side normal operation; The setting angle of both sides fan 9 is opposite, and hand of rotation is also opposite, and the anti-torsion that both sides fan rotation is produced is cancelled out each other, and does not produce spin when making aircraft hovering; The section of described riser bar 10 is single protruding aerofoil profile, and the number of sheets and fan 9 are identical or be multiple, and setting angle is opposite with fan 9, makes the slip-stream of the fan race rotation of being divided by, and linearly discharges; And in both sides duct 8, join and be two leaf riser bars, the 10 maximum ga(u)ge places that two straight lines install respectively and have living space to hold adapter shaft 23 with both sides duct short limb 19; Described fixed fin 14 ends have energy disperser 16, pillar 17 and wheel 18, on the ground by the wheel on four fixed fins 14 18 stable support aircraft; Described canard 39 is installed in the outer wall at duct 8 back sides by canard attaching parts 40; Described driving compartment size appropriateness can be stood with the satisfied normal adult of an idiotype and wherein be driven; The aerofoil profile of described wing 4B is plano-convex aerofoil profile or asymmetric biconvex aerofoil profile; Have parachute compartment 20 at the back side of driving compartment head, there is parachute the inside, in order to force-landing with parachute when aircraft runs out of steam; Described driving engine 29 is piston engine or propeller turbine or turboaxle motor.

Said structure is after like this work----driver enters cabin body 1 by airstair 35, and pin stands on the pedal 33 by height regulating rod 34 health is adjusted to conveniently operate the joystick 31 position of hand, with health Tobe 32 health is fixed in the cabin body 1.Airstair 35 is kept well in the rectangular recess 36 that is placed between two legs, hatch door 2 and hatchcover 3 are tightly locked, observe by hatchcover 3, when taking off vertically, the driver stand in the driving compartment, by wing flap 5 and the elevon 6B backward angular deflection of maneuvering system with double delta wing 4B, (being equivalent to make the wing of plano-convex aerofoil profile or asymmetric biconvex aerofoil profile to eliminate sinuousness), start the engine 29 then, the power of driving engine passes to fan 9 by power-transfer clutch 28 and retarder 27, and fan 9 high speed revolutions produce downward slip-stream, overcome aircraft gravity, aircraft is pulled away from ground, though wing 4B is blown in ducted fan slip-stream at this moment, wing has lost sinuousness relatively, the aerodynamic force of wing front and back is offset, and aircraft is translation and aloft hovering backward not; When aircraft will be converted to horizontal flight by hovering, the wing flap 5 of double delta wing 4B and elevon 6B reset and continue angular deflection forward, wing is recovered and the increase sinuousness, the slip-stream of the ducted fan of flowing through makes wing generation moment backward, make aircraft tilt forward around transverse axis, corresponding ducted fan also tilts forward, a part that produces in lift component backward is offset aircraft forward, meanwhile wing 4B is also corresponding leans forward, the slip-stream of ducted fan makes will produce the lift that a part makes progress in the aerodynamic force that produces on the wing, along with aircraft moves forward more and more sooner, the angle of attack is also more and more littler, wing 4B will produce bigger lift gradually, meanwhile canard 39 also will produce lift, strengthen this trend, the suffered gravity of aircraft will be transferred to wing 4B and canard 39 is born fully from ducted fan, ducted fan promote aircraft realize the high speed horizontal flight (at this moment chaufeur prostrate driving, the health of chaufeur is being born in 32 holders of health Tobe), wing flap 5 and elevon 6B reset simultaneously, after the horizontal flight, aircraft is handled by elevon 6B on the wing and vertical tail; Landing process and take-off process contrary.When aircraft aloft floating state need distinguish backward skew, skew left, skew to the right, lift-over left during lift-over to the right, can realize by the control respectively to elevon 6B and vertical tail.When park on ground, by the people hold handle 30 by wheel at the mobile aircraft of ground-surface rolling.

Embodiment four, individual lift device referring to anury delta wing layout in accompanying

drawing

14,15 and 16, comprise driving compartment, ducted fan propulsion system, duct short limb 19, wing 4C and vertical tail, it is characterized in that: described driving compartment is positioned at the aircraft middle part, the basis of driving compartment is a cabin body 1, body 1 front in cabin has hatch door 2, head is a hatchcover 3, aircraft is whole during the aircraft vertical takeoff and landing (VTOL) is attitude straight up, chaufeur is corresponding to be stood in the driving compartment, aircraft integral body is level attitude forward during the aircraft horizontal flight, and chaufeur is corresponding prostrate in driving compartment; Described ducted fan propulsion system is positioned at the driving compartment both sides, the ducted fan propulsion system comprises the driving engine 29 that is positioned at machinery space 7, power-transfer clutch 28, retarder 27, support the riser bar 10 of duct, be positioned at the fan 9 of duct 8, wherein the axis of the fan shaft 26 of fan 9 is parallel with the longitudinal axis of aircraft, from birds-eye view, the line between the axle center of two fan shafts 26 overlaps with the lateral axis of aircraft; Described wing is the delta wing 4C that is positioned at both sides, driving compartment middle part, this wing passes the afterbody and the one section length that can produce enough lift when level cruise is flown that stretches out in the machinery space 7, one section trailing edge between driving compartment and the machinery space has wing flap 5, one section trailing edge outside the machinery space has elevon 6B, all has the vertical tail of being made up of fixed fin 14 and yaw rudder 15 at the positive back side of the afterbody of both sides machinery space; When aircraft will be converted to horizontal flight by hovering, the elevon 6B angular deflection forward of delta wing 4C; Aircraft is up to the standard, and elevon 6B resets after the attitude.

In the above-mentioned anury delta wing layout individual lift device, described ducted fan propulsion system is installed in the both sides of driving compartment by duct short limb 19; Be installed between the S. A. 26 of fan 9 of ducted fan propulsion system of driving compartment both sides and have the synchronous transmission mechanism of power, be to coordinate axle 21 in the middle of the described secure synchronization mechanism, that coordinates axle 21 both sides symmetries is furnished with universal-joint 22, this universal-joint outwards has adapter shaft 23, described adapter shaft passes duct short limb 19 and riser bar 10, by gear pair 24 and conical gear 25 engagements that are installed on the fan shaft 26, make the rotating speed of both sides fan 9 keep identical, and make when a side driving engine and hinder for some reason when quitting work, the opposite side live engine can carry out the synchronous transmission of power by the synchronous transmission mechanism of power, and aircraft can be force-landed safely; At this moment, the power-transfer clutch of sick engine one side is disconnected, with the load of the driving engine that reduces the opposite side normal operation; The setting angle of both sides fan 9 is opposite, and hand of rotation is also opposite, and the anti-torsion that both sides fan rotation is produced is cancelled out each other, and does not produce spin when making aircraft hovering; The section of described riser bar 10 is single protruding aerofoil profile, the number of sheets and fan 9 are identical or be multiple, setting angle is opposite with fan 9, make the slip-stream of the fan race rotation of being divided by, linearly discharge, and both sides duct 8 in, join and two leaf riser bars, the 10 maximum ga(u)ge places that are two straight lines installations respectively have living space to hold adapter shaft 23 with both sides duct short limb 19; Described fixed fin 14 ends have energy disperser 16, pillar 17 and wheel 18, on the ground by the wheel on four fixed fins 14 18 stable support aircraft; Described driving compartment size appropriateness can be stood with the satisfied normal adult of an idiotype and wherein be driven; The aerofoil profile of described wing 4C is plano-convex aerofoil profile or asymmetric biconvex aerofoil profile; Have parachute compartment 20 at the back side of driving compartment head, there is parachute the inside, in order to force-landing with parachute when aircraft runs out of steam; Described driving engine 29 is piston engine or propeller turbine or turboaxle motor.

The inner bottom of the driving compartment in the said structure is provided with airstair 35; Airstair 35 tops have rectangular recess 36; Rectangular recess 36 both sides have the pedal 33 on height regulating rod 34 and the height regulating rod 34; Be provided with health Tobe 32 and jociey stick 31 according to organization of human body at the driving compartment inwall; The axle head of fan shaft 26 has fairing 11; Middle part, the back side at driving compartment 1 is provided with handle 30.

Said structure is after like this work----driver enters cabin body 1 by airstair 35, and pin stands on the pedal 33 by height regulating rod 34 health is adjusted to conveniently operate the joystick 31 position of hand, with health Tobe 32 health is fixed in the cabin body 1.Airstair 35 is kept well in the rectangular recess 36 that is placed between two legs, hatch door 2 and hatchcover 3 are tightly locked, observe by hatchcover 3, when taking off vertically, the driver stand in the driving compartment, by wing flap 5 and the elevon 6B backward angular deflection of maneuvering system with wing 4C, (being equivalent to make the wing wing of the wing or asymmetric biconvex of plano-convex to eliminate sinuousness), start the engine 29 then, and the power of driving engine is by power-transfer clutch 28, and retarder 27 passes to fan 9, fan 9 high speed revolutions produce downward slip-stream, overcome aircraft gravity, aircraft is pulled away from ground, at this moment, though wing 4C is blown in the ducted fan slip-stream, but wing has lost sinuousness relatively, and the aerodynamic force of wing front and back is offset, and aircraft is translation and aloft hovering backward not; When aircraft will be converted to horizontal flight by hovering, the wing flap 5 of delta wing 4C resets, simultaneously elevon 6B is resetted and continue angular deflection forward, the aerodynamic force backward that the aerodynamic force backward that the slip-stream of the ducted fan of flowing through produces one section wing outside the machinery space produces greater than one section wing between driving compartment and the machinery space, make aircraft tilt forward around transverse axis, corresponding ducted fan also tilts forward, a part that produces in lift component backward is offset aircraft forward, meanwhile wing is also corresponding leans forward, the slip-stream of ducted fan makes will produce the lift that a part makes progress in the aerodynamic force that produces on the wing, along with aircraft moves forward more and more sooner, the angle of attack is also more and more littler, wing 4C will produce bigger lift gradually, strengthen this trend, the suffered gravity of aircraft will be transferred to wing 4C fully from ducted fan and bear, ducted fan promote aircraft realize the high speed horizontal flight (at this moment chaufeur prostrate driving, the health of chaufeur is being born in 32 holders of health Tobe), elevon 6B resets simultaneously, after the horizontal flight, aircraft is handled by elevon 6B and vertical tail; Landing process and take-off process contrary.When aircraft aloft floating state need distinguish backward skew, skew left, skew to the right, lift-over left during lift-over to the right, can realize by the control respectively to elevon and vertical tail.When park on ground, hold handle 30 by the people and pass through wheel 18 at the mobile aircraft of ground-surface rolling.

The present invention not only has only above-mentioned 4 kinds of distribution forms, by with driving compartment, duct short limb 19, on the matrix that synchronous transmission mechanism of power and ducted fan propulsion system constitute, use wing, tailplane, vertical tail, X empennage and canard be composite construction respectively, can form other distribution forms, does not describe in detail one by one at this.

The present invention is an individual lift device, also can be expanded into double aircraft, can also use as unmanned vehicle or model airplane in addition.

In sum, the present invention has realized can vertical takeoff and landing (VTOL) and high-speed flight, and can be between the two smooth conversion.

Claims

1. an individual lift device comprises driving compartment, ducted fan propulsion system, duct short limb (19), wing, empennage or canard, it is characterized in that:

1), described driving compartment is positioned at the aircraft middle part, the driving compartment basis is cabin body (1), cabin body (1) front has hatch door (2), head is hatchcover (3), aircraft is whole during the aircraft vertical takeoff and landing (VTOL) is attitude straight up, chaufeur is corresponding to be stood in the driving compartment, and aircraft integral body is level attitude forward during the aircraft horizontal flight, and chaufeur is corresponding prostrate in driving compartment;

2), described ducted fan propulsion system is positioned at the driving compartment both sides, the ducted fan propulsion system comprises, be positioned at the driving engine (29) of machinery space (7), power-transfer clutch (28), retarder (27), the riser bar (10) of support duct, be positioned at the fan (9) of duct (8), wherein the axis of the fan shaft (26) of fan (9) is parallel with the longitudinal axis of aircraft, and from birds-eye view, the line between two fan shafts (26) axle center overlaps with the lateral axis of aircraft;

3), described wing is the trapezoidal straight wing (4A) that is positioned at both sides, driving compartment middle part, this wing passes machinery space (7) middle part and the one section length that can produce enough lift when level cruise is flown that stretches out, the trailing edge of one section wing between driving compartment and the machinery space has wing flap (5), one section trailing edge outside the machinery space has aileron (6A), between the afterbody of both sides machinery space and driving compartment afterbody, all have the tailplane of forming by horizontal stabilizer (12) and elevating rudder (13), all have the vertical tail of forming by fixed fin (14) and yaw rudder (15) at the positive back side of the afterbody of both sides machinery space; When aircraft will be converted to horizontal flight by hovering, the elevating rudder of tailplane (13) angular deflection forward; Aircraft is up to the standard, and elevating rudder (13) reset after the attitude;

Or 4), described wing is the trapezoidal straight wing (4A) that is positioned at both sides, driving compartment middle part, wing passes machinery space (7) middle part and the one section length that can produce enough lift when level cruise is flown that stretches out, the trailing edge of one section wing between driving compartment and the machinery space has wing flap (5), one section trailing edge outside the machinery space has aileron (6A), the radiation of driving compartment afterbody is equipped with the X-shaped empennage of being made up of X-shaped stabilator (37) and X-shaped rudder face (38), and guarantees that each face X-shaped empennage all has sufficient length to be exposed in the slip-stream of ducted fan generation; When aircraft will be converted to horizontal flight by hovering, X-shaped rudder face (38) angular deflection forward on the X-shaped empennage; Aircraft is up to the standard, and X-shaped rudder face (38) resets after the attitude;

Or 5), described wing is the double delta wing (4B) that is arranged in the driving compartment two sides of tail, this wing passes machinery space (6) afterbody and stretches out one section length that can produce enough lift when level cruise is flown, the trailing edge of one section wing between driving compartment and the machinery space has wing flap (5), one section trailing edge outside the machinery space has elevon (6B), have canard (39) at the back side of Vehicle nose, all have the vertical tail of forming by fixed fin (14) and yaw rudder (15) at the positive back side of the afterbody of both sides machinery space; When aircraft will be converted to horizontal flight by hovering, the wing flap (5) of double delta wing (4B) and elevon (6B) angular deflection forward; Aircraft is up to the standard, and wing flap and elevon reset after the attitude;

Or 6), described wing is the delta wing (4C) that is positioned at both sides, driving compartment middle part, this wing passes the afterbody and the one section length that can produce enough lift when level cruise is flown that stretches out in the machinery space (7), the trailing edge of one section wing between driving compartment and the machinery space has wing flap (5), one section trailing edge outside the machinery space has elevon (6B), all has the vertical tail of being made up of fixed fin (14) and yaw rudder (15) at the positive back side of the afterbody of both sides machinery space; When aircraft will be converted to horizontal flight by hovering, elevon (6B) angular deflection forward; Aircraft is up to the standard, and elevon (6B) resets after the attitude.

2. individual lift device according to claim 1 is characterized in that: described ducted fan propulsion system is installed in the both sides of driving compartment by duct short limb (19).

3. individual lift device according to claim 1, it is characterized in that: be installed between the fan shaft (26) of fan (9) of ducted fan propulsion system of driving compartment both sides and have the synchronous transmission mechanism of power, be to coordinate axle (21) in the middle of the synchronous transmission mechanism of described power, that coordinates axle (21) both sides symmetry is furnished with universal-joint (22), this universal-joint outwards has adapter shaft (23), described adapter shaft passes duct short limb (19) and riser bar (10), by gear pair (24) and conical gear (25) engagement that is installed on the fan shaft (26), make the rotating speed of both sides fan keep identical, and make when a side driving engine and hinder for some reason when quitting work, the opposite side live engine can carry out the synchronous transmission of power by the synchronous transmission mechanism of power, and aircraft can be force-landed smoothly.

4. individual lift device according to claim 1 is characterized in that: the setting angle of both sides fan (9) is opposite, and hand of rotation is also opposite, and the anti-torsion that both sides fan rotation is produced is cancelled out each other, and does not produce spin when making aircraft hovering.

5. individual lift device according to claim 1, it is characterized in that: the section of described riser bar (10) is single protruding aerofoil profile, and the number of sheets is identical with fan (9) or be multiple, and setting angle and fan (9) are opposite, make the slip-stream of fan eliminate race rotation, linearly discharge; And join with both sides duct short limbs (19) in the both sides duct (8) and be two leaf riser bar (10) the maximum ga(u)ge places that two straight lines install respectively and have living space to hold adapter shaft (23).

6. individual lift device according to claim 1, it is characterized in that: described fixed fin (14) end has energy disperser (16), pillar (17) and wheel (18), on the ground by the wheel (18) on four fixed fins (14) stable support aircraft.

7. individual lift device according to claim 1 is characterized in that: described X-shaped stabilator (37) end has energy disperser (16), pillar (17) and wheel (18), on the ground by the wheel (18) on the X-shaped stabilator (37) stable support aircraft.

8. individual lift device according to claim 1 is characterized in that: described canard (39) is installed in the outer wall at duct (8) back side by canard attaching parts (40).

9. individual lift device according to claim 1 is characterized in that: described driving compartment size appropriateness is driven to be fit to the normal adult of an idiotype.

10. individual lift device according to claim 1 is characterized in that: the aerofoil profile of described wing is plano-convex aerofoil profile or asymmetric biconvex aerofoil profile.

11. individual lift device according to claim 1 is characterized in that: have parachute compartment (20) at the back side of driving compartment head, there is parachute the inside, in order to force-landing with parachute when aircraft runs out of steam.

12. individual lift device according to claim 1 is characterized in that: described driving engine (29) is piston engine or propeller turbine or turboaxle motor.