Aircraft having the ability for hovering flight, fast forward flight, gliding flight, short take-off, short landing, vertical take-off and vertical landing
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-015/02
B64C-015/12
B64C-029/00
B64C-009/00
출원번호
US-0281445
(2007-03-02)
등록번호
US-8181903
(2012-05-22)
우선권정보
CH-0345/06 (2006-03-03)
국제출원번호
PCT/CH2007/000109
(2007-03-02)
§371/§102 date
20080902
(20080902)
국제공개번호
WO2007/098634
(2007-09-07)
발명자
/ 주소
Posva, David
출원인 / 주소
Posva, David
대리인 / 주소
The Nath Law Group
인용정보
피인용 횟수 :
8인용 특허 :
17
초록▼
Aircraft having two, preferably four or more, rotors (20) in wing hatches (10) which can be closed. The closure mechanism has, at the top, individually curved elements on a rollshutter (scroll/roller blind) (40) and, at the bottom, a set of longitudinal fins (30). One or more propeller/impeller driv
Aircraft having two, preferably four or more, rotors (20) in wing hatches (10) which can be closed. The closure mechanism has, at the top, individually curved elements on a rollshutter (scroll/roller blind) (40) and, at the bottom, a set of longitudinal fins (30). One or more propeller/impeller drives are firmly connected to the stabilator (60), which can be pivoted over a wide extent. In hovering flight, the wing hatches (10) are opened and the impeller drives (60), together with the stabilator, are pivoted largely vertically downwards. During the transition to cruise flight, the large flaperons (100) are lowered, and the propeller/impeller drives (60), together with the stabilator, are slowly pivoted to the horizontal. When the forward speed is sufficient, the wing hatches (10) are closed, the rotors (20) are stopped, and the flaperons (100) are raised somewhat again. The pilot has unobstructed visibility through the gap between the wingtips (70).
대표청구항▼
1. A vertical take-off and landing aircraft having at least two main wings, the aircraft, comprising: a) a part of each main wing holding two closable round wing hatches, with internal rotors which accelerate air downwards, which can be fully closed or opened according to use and non-use of the inte
1. A vertical take-off and landing aircraft having at least two main wings, the aircraft, comprising: a) a part of each main wing holding two closable round wing hatches, with internal rotors which accelerate air downwards, which can be fully closed or opened according to use and non-use of the internal rotors;b) an upper wing hatch closure mechanism positioned on the upper side of each of the main wings;c) a lower wing hatch closure mechanism, positioned on the lower side of each main wing, comprising a set of longitudinal fins extending parallel to a longitudinal axis of the aircraft, which turn about the longitudinal axis, which enable a continuous and rapidly modifiable deflection of the fins exiting air to the left and right, said fins further capable of effecting closing of the wing hatches on the lower side of each main wing by turning about the longitudinal axis; andd) an elevator or stabilator positioned in the rear, above the level of the main wings, separated from a fuselage of the aircraft and main wings, and which has attached gondolas holding thrust devices consisting of at least one of the group consisting of impellers, free propellers, jet turbines and rocket engines, and which are optimized for cruise flight but also functional in hover flight, and whereby the elevator or stabilator with the gondolas can be tilted from vertically down to horizontally to the rear about a cross-axis or lateral axis so that the air exit stream, exhaust jet stream or exiting air blast neither touches the main wings nor the fuselage, and whereby air intake cones of the thrust devices do not significantly affect the aerodynamics of the main wings or the fuselage. 2. The aircraft of claim 1, wherein the upper wing hatch closure mechanism comprises, for each of the main wings, a roll-shutter comprising a scroll or roller blind, with plural elements forming a curved aerodynamic shape, configured to roll up on a spindle in each main wing, aside of the wing hatch, in order to open the wing hatch on top for hover flight, wherein for cruise flight, the unrolling of the roll-shutter allows the elements slide along the hatch edges into their positions above the wing as an upper hatch closure, in order to close the wing hatch on top. 3. An aircraft according to claim 2, wherein the main wings have a configuration characterized by two wing tips, which extend to the front aside of the cockpit window, respectively a gap between the front parts of the wings for unobstructed visibility. 4. An aircraft according to claim 3, characterized by two connected bars shaping a vertex, respectively an arched bar, between the two front wing tips, which neither obstructs the view nor the aerodynamics significantly, but prevents the aircraft from becoming hooked up in the event of a collision with cables in the air and helps protect the cockpit glass when maneuvering and taxiing on the ground. 5. An aircraft according to claim 2, further comprising: a tongue-and-groove arrangement along the plural elements of the roll-shutter, the tongue-and-groove arrangement to hold the roll-shutter elements in place to securely resist the lift and drag forces in cruise flight. 6. An aircraft according to claim 5, further comprising sealing tubes provided to effect sealing at front and rear edges of the roll-shutter. 7. The aircraft of claim 1, wherein the wing hatch closure mechanism on the upper side of the main wings comprises plural elements, curved to form an aerodynamic shape, which glide individually aside the wing hatch to open the wing hatches for hover flight, and wherein for the cruise flight, the elements are pushed out along the wing hatch edges to be positioned above the wing hatch and pushed together, in order to close the wing hatch on top. 8. The aircraft of claim 1, further comprising rotor drives for the rotors comprising one or more engines selected from the group consisting of electric motors and combustion engines with at least one engine transferring its power to a central axis of each rotor, through at least one of the group consisting of shafts, chains and belts. 9. The aircraft of claim 1, wherein the main wings have configurations characterized by two wing tips, the wings and wing tips which extend to the front aside of a pilot's cockpit window, provide a gap between the front parts of the wings for unobstructed forward visibility. 10. The aircraft of claim 9, due to the small wing loading in cruise flight enhanced by the unobstructed visibility to the front and down, allows the same steep approach angle for both flight modes, so the pilot can switch at any time between the hover flight modus and the cruise flight modus and still aim and land on the same touch-down point, however, in cruise mode with much smaller angle of attack and correspondingly larger forward and descend speed resulting in the need of a short rolling distance when landing in cruise mode, wherein the rolling distance in cruise mode landing can be minimized through the use of the rotors at touch-down. 11. The aircraft of claim 1, characterized by large ailerons at the trailing edge of the main wings, used as flaperons, which not only permit the regulation of the lift force, but also enables a slow flight, at the transition from hovering flight modus into the cruise flight modus, with a minimized angle of attack, so that the forces generated by the rotors) in the main wings do not interfere with the acceleration of the aircraft. 12. The aircraft of claim 1, wherein are individually ignitable and individually, through discharge outlets, releasable solid fuel rockets at various points on the aircraft, so that they generate an upward force in relation to the aircraft coordinate system and an individual torque. 13. An aircraft according to claim 1, wherein: the part of each main wing that holds the closable round wing hatches comprise one half or more of that wing. 14. An aircraft according to claim 1, wherein: the part of each main wing that holds the closable round wing hatches comprise one half or more of that wing; andthe part of each main wing holding two or more closable round wing hatches. 15. The aircraft of claim 1, further comprising rotor drives for the rotors comprising a plurality of engines selected from the group consisting of electric motors and combustion engines with one engine situated in the center of each rotor, and at least one remaining engine outside the rotor area, transferring power to a central axis of at least one rotor on each wing, through at least one of the group consisting of shafts, chains and belts. 16. An aircraft according to claim 1, wherein the two closable wing hatches of each wing comprise a front round wing hatch having a planar area smaller than that of a rear wing hatch. 17. An aircraft according to claim 1, wherein: the connection of the elevator or stabilator with the rest of the aircraft is implemented as a twin boom structure. 18. A vertical take-off and landing aircraft having main wings, the aircraft, comprising: a) a part of each main wing holding two closable round wing hatches, with internal rotors which accelerate air downwards, which can be fully closed or opened according to use and non-use of the internal rotors;b) a lower wing hatch closure mechanism, positioned on the lower side of each main wing, comprising a set of longitudinal fins extending parallel to a longitudinal axis of the aircraft, which turn about the longitudinal axis, which enable a continuous and rapidly modifiable deflection of the fins exiting air to the left and right, said fins further capable of effecting closing of the wing hatches on the lower side of each main wing by turning about the longitudinal axis; andc) an elevator or stabilator positioned in the rear, above the level of the main wings, separated from a fuselage of the aircraft and main wings, and which has attached gondolas holding thrust devices consisting of at least one of the group consisting of impellers, free propellers, jet turbines and rocket engines, and which are optimized for fast cruise flight but are also functional in hover flight, and whereby the elevator or stabilator with the gondolas can be tilted from vertically down to horizontally to the rear about a cross-axis or lateral axis so that the air exit stream, exhaust jet stream or exiting air blast neither touches the main wings nor the fuselage, and whereby air intake cones of the thrust devices do not significantly affect the aerodynamics of the main wings or the fuselagewherein the main wings have configurations characterized by two wing tips, the wings and wing tips which extend to the front aside of a pilot's cockpit window, provide a gap between the front parts of the wings for unobstructed forward visibility, and further characterized by two connected bars shaping a vertex, respectively an arched bar, between the two front wing tips, which neither obstructs the view nor the aerodynamics significantly, but prevents the aircraft from becoming hooked up in the event of a collision with cables in the air and helps protect the cockpit glass when maneuvering and taxiing on the ground. 19. A vertical take-off and landing aircraft having main wings, the aircraft, comprising: a) a part of each main wing holding two closable round wing hatches, with internal rotors which accelerate air downwards, which can be fully closed or opened according to use and non-use of the internal rotors;b) an upper wing hatch closure mechanism positioned on the upper side of each of the main wings;c) a lower wing hatch closure mechanism, positioned on the lower side of each main wing, comprising a set of longitudinal fins extending parallel to a longitudinal axis of the aircraft, which turn about the longitudinal axis, which enable a continuous and rapidly modifiable deflection of the fins exiting air to the left and right, said fins further capable of effecting closing of the wing hatches on the lower side of each main wing by turning about the longitudinal axis;d) an elevator or stabilator positioned in the rear, above the level of the main wings, separated from a fuselage of the aircraft and main wings, and which has attached gondolas holding thrust devices consisting of at least one of the group consisting of impellers, free propellers, jet turbines and rocket engines, and which are optimized for fast cruise flight but are also functional in hover flight, and whereby the elevator or stabilator with the gondolas can be tilted from vertically down to horizontally to the rear about a cross-axis or lateral axis so that the air exit stream, exhaust jet stream or exiting air blast neither touches the main wings nor the fuselage, and whereby air intake cones of the thrust devices do not significantly affect the aerodynamics of the main wings or the fuselage; andtwo wing tips, which extend to the front aside of the cockpit window, respectively a gap between the front parts of the wings for unobstructed visibility.
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이 특허에 인용된 특허 (17)
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