초록 ▼

A rotor system for an aircraft including a rotor (1) with a drive part (2) mounted rotatable about a rotation axis (8) and supporting the proximal end (9) of at least one rotor blade (3). The rotor system comprises a jet turbine (4) for providing pressurized exhaust gas to a rotary structure (7) hav

A rotor system for an aircraft including a rotor (1) with a drive part (2) mounted rotatable about a rotation axis (8) and supporting the proximal end (9) of at least one rotor blade (3). The rotor system comprises a jet turbine (4) for providing pressurized exhaust gas to a rotary structure (7) having at least one jet nozzle outlet (6) and at least one jet stream duct (5) for transporting the pressurized exhaust gas from the turbine (4) to the jet nozzle outlet (6) to cause rotation of the rotary structure (7) by expelling the pressurized exhaust gas through the nozzle outlet (6). In addition, only the rotary structure (7) and not the rotor blade (3) comprise a jet stream duct (5) and a nozzle outlet (6).

대표청구항 ▼

1. A rotor system for an aircraft including a rotor (1) with a rotary structure (7, 7′) mounted rotatable about a rotation axis (8) and supporting a proximal end (9) of at least one rotor blade (3), wherein the rotor system comprises at least one jet turbine (4, 4′) for providing pressurised exhaust

1. A rotor system for an aircraft including a rotor (1) with a rotary structure (7, 7′) mounted rotatable about a rotation axis (8) and supporting a proximal end (9) of at least one rotor blade (3), wherein the rotor system comprises at least one jet turbine (4, 4′) for providing pressurised exhaust gas to the rotary structure (7, 7′), the rotary structure (7, 7′) having at least one jet nozzle outlet (6) and at least one jet stream duct (5, 5′) for transporting the pressurised exhaust gas from the jet turbine (4, 4′) to the jet nozzle outlet (6) to cause rotation of the rotary structure (7, 7′) by expelling the pressurised exhaust gas through the nozzle outlet (6), the rotor system having a support structure (20) for attaching the rotor system to an aircraft body, wherein only the rotary structure (7, 7′) and not the rotor blade (3, 3′) comprise a jet stream duct (5, 5′) and a nozzle outlet (6), the rotor system comprising an adjuster for adjusting yaw of the aircraft body relative to the earth, the adjuster being shaftless connected to the rotary structure (7), and further comprising a magnetic coupling between the support structure and the rotary structure (7), wherein the magnetic coupling comprises an integrated electromagnetic motor (51) rotationally coupling the rotary structure (7) to the support structure (20), wherein the electromagnetic motor comprises at least one permanent magnet (18) on the rotary structure (7) and at least one electromagnet (19) on the support structure (20), wherein the electromagnetic motor controls the yaw by advancing or retarding relative rotation between the at least one electromagnet on the support structure and the at least one permanent magnet on the rotary structure. 2. A rotor system (1) for an aircraft in combination with an attitude control mechanism, the rotor system including a rotor (1) with a rotary structure (7, 7′) mounted rotatable about a rotation axis (8) and supporting a proximal end (9) of at least one rotor blade (3), wherein the rotor system comprises at least one jet turbine (4, 4′) for providing pressurised exhaust gas to the rotary structure (7, 7′), the rotary structure (7, 7′) having at least one jet nozzle outlet (6) and at least one jet stream duct (5, 5′) for transporting the pressurised exhaust gas from the jet turbine (4, 4′) to the jet nozzle outlet (6) to cause rotation of the rotary structure (7, 7′) by expelling the pressurised exhaust gas through the nozzle outlet (6), the rotor system having a support structure (20) for attaching the rotor system to an aircraft body, wherein only the rotary structure (7, 7′) and not the rotor blade (3, 3′) comprise a jet stream duct (5, 5′) and a nozzle outlet (6), the attitude control mechanism comprising a 6-legged suspension with a first connection (35) connected to the support structure (20) and with a second connection (30) for connection to an aircraft body (31, 37), wherein the 6-legged suspension is created as a hexapod with six legs (34), the legs comprising a longitudinally extendable actuators (36), where the six legs are connected to the support structure (20) at three points and to the body 31 at three points such that each two adjacent legs have one common connection point at their one ends and two different connection points at their opposite ends, wherein the attitude control mechanism comprises the longitudinally extendable actuators for extending or shortening the legs and thereby displacing a centre of gravity (32) of the aircraft relatively to the vertical centre line (33) of the aircraft body (31) for controlled adjustment of attitude of the aircraft, wherein the rotary structure (7) is coupled to the support structure (20), the support structure (20) is located at the rotary structure (7) above and remote from the aircraft body, the hexapod is above the aircraft body, and no rotational rotor shaft extends from the rotary structure (7) to the aircraft body. 3. A rotor system according to claim 1, wherein the electromagnetic motor is of the asynchronous induction type motor. 4. Rotor system according to claim 1, wherein the jet turbine (4) is a radial flow type jet turbine located coaxially with the rotation axis (8) of the rotor system (1). 5. A rotor system according to claim 4, wherein the jet turbine (4) has a support structure (20) with a first side for non-rotational connection to an aircraft body (31, 37) and with an opposite, second side, which is rotationally coupled to a radial flow jet disc (14) with compressor blades (11), and wherein an inlet opening (12) for inlet of air is provided on the second side of the support structure (20). 6. Rotor system according to claim 5, wherein the jet disc (14) has turbine blades (17) provided in a plane of the ducts (5) of the rotary structure (7). 7. A rotor system for an aircraft including a rotor (1) with a rotary structure (7, 7′) mounted rotatable about a rotation axis (8) and supporting a proximal end (9) of at least one rotor blade (3), wherein the rotor system comprises at least one jet turbine (4, 4′) for providing pressurised exhaust gas to the rotary structure (7, 7′), the rotary structure (7, 7′) having at least one jet nozzle outlet (6) and at least one jet stream duct (5, 5′) for transporting the pressurised exhaust gas from the jet turbine (4, 4′) to the jet nozzle outlet (6) to cause rotation of the rotary structure (7, 7′) by expelling the pressurised exhaust gas through the nozzle outlet (6), wherein only the rotary structure (7, 7′) and not the rotor blade (3, 3′) comprise a jet stream duct (5, 5′) and a nozzle outlet (6), wherein the jet turbine (4) is a radial flow type jet turbine located coaxially with the rotation axis (8) of the rotor system (1), wherein the jet turbine (4) has a support structure (20) with a first side for non-rotational connection to an aircraft body (31, 37) and with an opposite, second side, which is rotationally coupled to a radial flow jet disc (14) with compressor blades (11), and wherein an inlet opening (12) for inlet of air is provided on the second side of the support structure (20), wherein the jet disc (14) has a disc base (14′) on which compressor blades (11) are provided, the compressor blades (11) having an adjacent part (11′) fastened to the disc base (14′) and a distal part (11″), being distal from the disc base (14′), wherein on the distal parts (11″) of the compressor blades (11), a disc member (15) is provided, connecting the distal parts (11″) of the compressor blades (11) with turbine blades (17), and wherein a combustion chamber (16) is provided on the support structure (20). 8. A rotor system according to claim 5, wherein the jet turbine comprises an integrated electromagnetic starter motor (50) coupling the jet disc (14) to the support structure (20). 9. A rotor system according to claim 8, wherein the electromagnetic starter motor has permanent magnets (21) as part of the disc jet (14) and electromagnets (22) as part of the support structure (20). 10. A rotor system according to claim 8, wherein the electromagnetic starter motor is of the asynchronous induction type motor. 11. A rotor system according to claim 1, wherein the aircraft comprises an aircraft body below the rotary structure and wherein the adjuster, the support structure, and the rotary structure are remote from the aircraft body.