Heliplane rotor thermal management for maintaining dimensional stability
First Claim
1. A method for maintaining rigidity of a rotor system, the method comprising:
- providing an aircraft havinga rotor system including a hub defining a cavity,a plurality of blades coupled to the hub and each defining a duct in fluid communication with the cavity,a plurality of tip jets secured to the blades in fluid communication with the ducts,a mast having the hub rotationally mounted thereto,a swashplate surrounding the mast and coupled to the blades and to a plurality of swashplate actuators, anda shroud surrounding the mast and defining an air channel in fluid communication with the cavity;
during a first portion of a flight, transmitting air having a temperature within a first temperature range through the rotor system;
during a second portion of the flight including sustained longitudinal flight, orienting the mast, rotor hub, and blades to be effective to induce autorotation of the blades; and
during the second portion, inputting heat to the rotor system effective to maintain mechanical slack in the relative movement between the mast and plurality of blades within a predetermined tolerance.
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Accused Products
Abstract
A rotor system is disclosed for a reactive drive rotary wing aircraft. Apparatus and methods are disclosed for maintaining the rigidity of the rotor and eliminating play between flight controls and the rotor by mounting swashplate actuators to a flange rigidly secured to the mast. Apparatus and methods are disclosed for thermal management of the rotor in order to avoid bearing failure or loss of bearing preload. Methods include modulating the temperature of oil pumped over one or more of the mast bearing, swashplate bearing, and spindle bearing. The temperature of air passively or actively drawn through rotor may also be modulated to maintain bearing temperature within a predetermined range. Structures for reducing pressure losses and drag on components due to air flow through the rotor are also disclosed. A rotor facilitating thermal management by oil and air flow is also disclosed.
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Citations
20 Claims
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1. A method for maintaining rigidity of a rotor system, the method comprising:
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providing an aircraft having a rotor system including a hub defining a cavity, a plurality of blades coupled to the hub and each defining a duct in fluid communication with the cavity, a plurality of tip jets secured to the blades in fluid communication with the ducts, a mast having the hub rotationally mounted thereto, a swashplate surrounding the mast and coupled to the blades and to a plurality of swashplate actuators, and a shroud surrounding the mast and defining an air channel in fluid communication with the cavity; during a first portion of a flight, transmitting air having a temperature within a first temperature range through the rotor system; during a second portion of the flight including sustained longitudinal flight, orienting the mast, rotor hub, and blades to be effective to induce autorotation of the blades; and during the second portion, inputting heat to the rotor system effective to maintain mechanical slack in the relative movement between the mast and plurality of blades within a predetermined tolerance. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10)
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11. A rotorcraft comprising:
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an airframe; a rotor system comprising a mast mounted to the airframe, a hub rotatably mounted to the mast and defining a cavity, a shroud surrounding the mast and defining an air channel in fluid communication with the cavity, a plurality of blades mounted to the hub, each blade of the plurality of blades defining a duct in fluid communication with the cavity, and a tip jet mounted to each blade of the plurality of blades to be in fluid communication with the duct corresponding thereto; a compressed air source; a flight control system mounted to the airframe, the flight control system being operably connected to the compressed air source and programmed to direct heated compressed air from the compressed air source through the air channel, cavity, and ducts to the tip jets during a first portion of a flight, ignite the tip jets only during said directing, and direct the heated compressed air to the rotor system during a second portion of the flight including sustained longitudinal flight at a rate effective to maintain mechanical slack in the relative motion between the mast and each blade within a predetermined tolerance. - View Dependent Claims (12, 13, 14, 15, 16, 17, 18, 19, 20)
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Specification