Dual hull airship controlled by thrust vectoring
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64B-001/68
B64B-001/00
출원번호
US-0523238
(2003-08-11)
등록번호
US-7350746
(2008-04-01)
우선권정보
IT-MI2002A1815(2002-08-09)
국제출원번호
PCT/EP03/008950
(2003-08-11)
§371/§102 date
20050119
(20050119)
국제공개번호
WO04/016503
(2004-02-26)
발명자
/ 주소
Gili,Piero
Icardi,Ugo
Ruotolo,Romualdo
Battipede,Manuela
Vercesi,Piercarlo
출원인 / 주소
Nautilus S.p.A.
Politecnico Di Torino
대리인 / 주소
Hedman & Costigan, P.C.
인용정보
피인용 횟수 :
6인용 특허 :
8
초록▼
A highly maneuverable aircraft with aerostatic lift consists, in particular, of a non-rigid airship (10) which can be piloted or radio-controlled; the airship (10) is sustained by helium and consists of two spindle-shaped elements side by side (11) joined by a connecting structure (12) to form a cha
A highly maneuverable aircraft with aerostatic lift consists, in particular, of a non-rigid airship (10) which can be piloted or radio-controlled; the airship (10) is sustained by helium and consists of two spindle-shaped elements side by side (11) joined by a connecting structure (12) to form a characteristic catamaran shape, without deflecting aerodynamic control surfaces as the command system consists of a set of several adjustable electric motors, each driving a variable-pitch propeller (13).
대표청구항▼
The invention claimed is: 1. Aircraft with aerostatic lift, comprising a structure, which includes at least two non-rigid spindle-shaped elements side by side (11), joined by at least one connecting element (12), said aircraft also being provided with a movement and attitude control system with a s
The invention claimed is: 1. Aircraft with aerostatic lift, comprising a structure, which includes at least two non-rigid spindle-shaped elements side by side (11), joined by at least one connecting element (12), said aircraft also being provided with a movement and attitude control system with a set of several electric motors, of which at least one is adjustable with rotation around an axis perpendicular to the rotation axis of said motor, each of which drives a propeller (13) with fixed or variable pitch, wherein at least one of the propellers (13) is mounted on a vertical arm (14) extending from the connecting element (12) and disposed at a distance from the whole body centre of gravity, and wherein the aircraft consists of an airship (10), which can be piloted or radio-controlled, without deflecting aerodynamic control surfaces and sustained by helium, said movement and attitude control system being solely of the propulsive type, with a ballonets system wherein for each hull during the climbing phase, ballonets deflate progressively, from the outer to the central sector and during the descent phase, ballonets inflate progressively from the central to the outer sectors. 2. Aircraft with aerostatic lift as in claim 1, characterised in that it comprises pressurised structural elements appropriately assembled inside said connecting element (12) between the two spindle-shaped elements (11). 3. Aircraft with aerostatic lift as in claim 1, characterised in that said control system is fly-by-wire and completely automatic, according to which at least one of this propeller (13) is mounted on vertical arm (14) extending from the connecting element (12), disposed at a distance from the whole body centre of gravity, piloting is performed by means of controls with a throttle lever, a stick and a group control, said automatic control system being suitable for transferring the appropriate commands to the motors in order to perform the required manoeuvres. 4. Aircraft with aerostatic lift as in claim 3, characterised in that said first four motors are provided with propeller discs on vertical planes and are fitted on arms (14) having a vertical axis, while said fifth and sixth motor, with horizontal propeller disc and invertible thrust direction, are fitted in a central position between said two spindle-shaped elements (11). 5. Aircraft with aerostatic lift as in claim 1, characterised in that said airship (10) has a configuration with five or six motors, the first four of which are used for forward flight for the longitudinal, directional and lateral control, and the fifth and sixth motor are used for rapid ascent and descent. 6. Aircraft with aerostatic lift as in claim 1, characterised in that said airship (10) has a configuration with four motors, two of which are used for forward flight and directional control and the other two for rapid ascent and descent and longitudinal control. 7. Aircraft with aerostatic lift as in claim 6, characterised in that said first two motors, with propeller discs on vertical planes, are fitted on a horizontal transverse bar, arranged at the sides of the gondola, and are used for directional control of the aircraft, while the other two motors, having horizontal propeller disc with invertible thrust direction, are fitted in a central position between said two spindle-shaped elements (11). 8. Aircraft with aerostatic lift as in claim 1, characterised in that it features a couple of retractile landing devices formed by rods properly connected by sliding screws, which are almost adherent to the envelopes during the flight, while are moved outward for landing. 9. Aircraft with aerostatic lift, comprising a structure, which includes at least two non-rigid spindle-shaped elements side by side (11), joined by at least one connecting element (12), said aircraft also being provided with a movement and attitude control system with a set of several electric motors, of which at least one is adjustable with rotation around an axis perpendicular to the rotation axis of said motor, each of which drives a propeller (13) with fixed or variable pitch, wherein at least one of the propellers (13) is mounted on a vertical arm (14) extending from the connecting element (12) and disposed at a distance from the whole body centre of gravity, and wherein the aircraft consists of an airship (10), which can be piloted or radio-controlled, without deflecting aerodynamic control surfaces and sustained by helium, said movement and attitude control system being solely of the propulsive type, wherein said airship (10) is provided with ballonets system (15), at least one for each spindle-shaped element(11), in order to vary the altitude within a pre-set range without loss of gas, said ballonets (15) being intercommunicating like the volumes of gas of said spindle shaped elements (11) said ballonets (15) communicate by means of a second duct (16), provided with two controlled single-acting valves (17), while said spindle-shaped elements (11) communicate by means of a second duct (18) provided with a first controlled single-acting valve (19) and a second single-acting valve (20), coupled with an aperture for inflating said spindle-shaped elements (11), said ballonets (15) being kept pressurized by a third single-acting valve (21), at the inlet of which a dynamic intake(23) is provided with an inflation aperture, and a compressor (22).
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