Patent Application
20060120873
The present invention relates to a blade fold system for a helicopter, and more particularly to a rotor blade positioning system which positions each rotor blade prior to blade folding while minimizing applied strain to elastomeric bearings within the rotor head.
While the flight capabilities of helicopters makes them effective vehicles for a wide variety of missions, operation of helicopters in certain circumstances may be limited by the overall structural envelopes thereof. The large radial dimensions of helicopter rotor assemblies results in helicopters having relatively large structural envelopes, which may limit their utility in some circumstances.
Helicopters, particularly military helicopters utilized for maritime flight operations, may be required to conduct operations from ships for extended periods of time. Shipboard space is generally at a premium, and the large structural envelopes of helicopters means that stowage during periods of non-use requires a relatively significant allocation of such limited space. Furthermore, strategic and tactical considerations in the military utilization of helicopters has led to a requirement for helicopters having main rotor assemblies that may be readily reconfigured for rapid deployment, routine transport, and/or stowage through reduction in structural envelopes.
Several options are available to reduce the structural envelopes of helicopters to facilitate rapid deployment, routine transport, stowage, and/or to reduce the vulnerability thereof to environmental conditions. One option is to design the main rotor assemblies thereof so that the main rotor blades may be folded about the main rotor hub assembly. Main rotor blade folding operations are typically implemented automatically.
One helicopter with an automatic blade folding system is the CH-53E. The CH-53E is currently the world's largest shipboard compatible helicopter. A significant consideration in the design of the CH-53E is shipboard compatibility. The CH-53E in a stored configuration effectively defines the maximum structural envelope which will fit on the elevators and in the hangar deck of United States Marine Corps Amphibious Assault Ships.
Prior to folding blades on any helicopter, the blades must be located and locked in a pre-set blade fold position such that a blade hinge axis is oriented to allow folding of each blade to its proper folded position. On aircraft such as CH-53E, blade positioning is accomplished using a series of hydraulic actuators and stops. The current CH-53E rotor head utilizes a hydraulic actuated piston incorporated into the damper as a pitch lock. Accumulator pressure drives the damper to hold the blade in the pre-set blade fold position in which the yoke is driven to full lag or lead position. The swashplate is then located in a pre-set position such that each blade is at the correct pitch angle for the blade pitch locks to engage. Since pitch motion occurs between the sleeve and the spindle, a hydraulic actuated pin on the sleeve engages a lug on the spindle to lock the spindle and sleeve together to prevent pitch motion. These components function independently as the current CH-53E rotor head employs separate conventional bearings for pitch, flap, and lead/lag blade motions.
Elastomeric rotor heads with elastomeric bearings provide numerous advantages over conventional rotor head assemblies which utilize separate bearings for pitch, flap, and lead/lag blade motions. Elastomeric rotor heads provide such significant advantages, that current aircraft such as the CH-53E may be modernized to include an elastomeric rotor head.
Current blade folding systems are not transferable to an elastomeric rotor head as the elastomeric bearings and visco-elastic damper are essentially springs which are always biased toward a predetermined position. Deflection away from the predetermined position strains the elastomeric bearings and visco-elastic damper. Significant deflection over prolonged time periods, such as during a blade fold position, may eventually damage the elastomeric rotor head system.
Accordingly, it is desirable to provide a blade folding system for an elastomeric rotor head system which positions each rotor blade prior to blade folding while minimizing applied strain to elastomeric bearings within the rotor head.
The rotor blade folding system according to the present invention generally includes an electric motor mounted to a damper housing of the damper assembly to drive a damper gear train and selectively lock a damper rod relative the damper housing in a blade fold position to minimize strain on an elastomeric bearing.
In operation, a blade fold controller operates the electric motor to rotate a sleeve about the damper axis such that an outer circumferential jackscrew drives a plunger along the damper axis toward the damper rod. Concurrently therewith, an inner circumferential jackscrew of the sleeve drives a puller along the damper axis until a puller bushing contacts a damper rod puller stop. The plunger and the puller trap the damper rod in a predetermined blade fold position. The damper assembly is locked at a predetermined length such that the elastomeric bearing is isolated when the rotor blade is folded. Once each yoke is locked by the damper assembly in the blade fold position, the blade fold controller drives the rotary actuator to rotate each rotor blade to a predetermined blade fold angle.
To unfold the blades, the blade fold controller reverses the rotary actuator to return the rotor blade to a flight position and reverses the electric motor to release the damper rod such that the yoke and damper assembly returns to a flight configuration.
The present invention therefore provides a blade folding system for an elastomeric rotor head system which positions each rotor blade prior to blade folding while minimizing applied stress to elastomeric bearings within the rotor head.
The various features and advantages of this invention will become apparent to those skilled in the art from the following detailed description of the currently preferred embodiment. The drawings that accompany the detailed description can be briefly described as follows:
Referring to
The yoke 36 is mounted to the rotor hub 26 through the elastomeric bearing 38 such that the blade assembly 24 may be moved in flapping, pitch and lead/lag motions as generally understood. The damper assembly 40 reacts with the yoke 36 to dampen lead/lag motions and vibration of the blade assembly 24.
A rotor blade folding system 44 generally includes the blade pitch lock assembly 42, the rotary actuator 32, a retractable blade retaining pin 33, the damper assembly 40 and a blade fold controller 47 (illustrated schematically) to selectively position each rotor blade assembly 24 in a particular folded position to minimize the aircraft structural envelope (
Referring to
A rod mount 52 extends from near an end of the damper rod 46 and a housing mount 54 extends from the damper housing 50. The mount 52 and 54, which are ball mounts, other links or a combination of them, mount the damper assembly 40 between the rotor hub 26 and the yoke 36 of each blade assembly 24 (
Referring to
The electric motor 56 includes an output shaft 58 which drives an output gear 60. The output gear 60 is in meshing engagement with a sleeve 62 at gear teeth 64. The sleeve 62 is rotationally mounted upon a sleeve bearing 66 which is mounted about an inner damper housing 68 such that the sleeve 62 rotates about the damper axis D in response to operation of the electric motor 46.
The sleeve 62 includes an outer circumferential jackscrew 70 and an inner circumferential jackscrew 72. The outer circumferential jackscrew 70 and the inner circumferential jackscrew 72 are preferably oppositely directed screw threads. That is, the outer circumferential jackscrew 70 is right hand and the inner circumferential jackscrew 72 is left hand or vice-versa. It should be understood that other threaded members or gears other than a jackscrew or in combination therewith may also be used with the present invention.
The outer circumferential jackscrew 70 engages a plunger screw thread 74 which is located within the inner diameter of a plunger 76. The plunger 76 includes an anti-rotation feature 78 which includes a radial pin 80 which extends into a housing slot 82 such that the plunger 76 slides along the axis D but does not rotate.
The inner circumferential jackscrew 72 engages a puller screw thread 84 located along a length of a puller 86. The puller 86 includes an anti-rotation feature 88 such that the puller 86 slides along the axis D but does not rotate. In one example, the puller 86 is splined at 90 and the inner damper housing 68 is splinted at 92.
The puller 86 slides within a tubular hollow cavity 93 formed within the damper rod 46. Preferably, a puller bushing 94 moves with the puller 86 and is slidable within the damper rod 46 to selectively contact a damper rod puller stop 96 (in the position illustrated in
A blade fold controller 47 (illustrated schematically) operates the electric motor 56 to drive the output gear 60 which is in meshing engagement with the sleeve 62. The sleeve 62 rotates about the damper axis D such that the outer circumferential jackscrew 70 cooperates with the plunger screw thread 74 to drive the plunger 76 along axis D toward the damper rod 46. Eventually, the plunger 76 moves into the position shown in
Once the plunger 76 and the puller 86 trap the damper rod 46 and the damper assembly 40 is locked, each rotor blade assembly 24 may be positioned in pitch by articulating the swashplate prior to engaging the blade pitch lock assembly 42 (
Referring to
To unfold the blades, the blade fold controller 47 reverses the rotary actuator 32 to unfold the rotor blades 28 (α to zero) then retracts the plunger 76 and the puller 86 to release the damper rod 46 such that damper assembly 40 (
It should be understood that relative positional terms such as “forward,” “aft,” “upper,” “lower,” “above,” “below,” and the like are with reference to the normal operational attitude of the vehicle and should not be considered otherwise limiting.
Although particular step sequences are shown, described, and claimed, it should be understood that steps may be performed in any order, separated or combined unless otherwise indicated and will still benefit from the present invention.
The foregoing description is exemplary rather than defined by the limitations within. Many modifications and variations of the present invention are possible in light of the above teachings. The preferred embodiments of this invention have been disclosed, however, one of ordinary skill in the art would recognize that certain modifications would come within the scope of this invention. It is, therefore, to be understood that within the scope of the appended claims, the invention may be practiced otherwise than as specifically described. For that reason the following claims should be studied to determine the true scope and content of this invention.
