Twin tension/torsion beam rotor system

• US 4,419,051 A
• Filed: 02/16/1982
• Issued: 12/06/1983
• Est. Priority Date: 02/16/1982
• Status: Expired due to Fees

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: DeRosa, Richard T.
• Primary Examiner(s): Powell, Jr., Everette A.
• Application Number:
  US06/348,889
• Time in Patent Office: 658 Days
• Field of Search: 416/134 A, 416/138 A, 416/140 A, 416/141
• US Class Current: 416/140
• CPC Class Codes: B64C 27/322 Blade travel limiting devices, e.g. droop stops
• CPC Class Codes: B64C 27/33 having flexing arms
• CPC Class Codes: B64C 27/58 Transmitting means, e.g. interrelated with initiating means or means acting on blades means acting on blades B64C27/72

Abstract

A rotor system for a helicopter including a tension/torsion component which is fabricated from composite material and as a compound curved, continuous loop twin tension/torsion beam. Each end of the twin tension/torsion beam includes two curved (wrapped) ends which are oriented substantially orthogonally. At one end the curved ends extend about the flap hinge, and at the other end the curved ends extend about the fold and lead/lag hinge of the rotor system. To accommodate the twin tension/torsion beam at the flap hinge a support fitting is provided with lugs which are made compatible with the rotor hub lugs, and to accommodate the twin tension/torsion beam at the fold and lead/lag hinge a pitch varying structure is provided with twin beam engaging clevis surfaces.

Claims

1. A rotor system for mounting rotor blades to a helicopter, comprising:

a rotor hub having at least two sets of mounting lugs, each set including a plurality of adjacent lugs each containing an aperture;

a support fitting for each set of mounting lugs, each said support fitting including a plurality of adjacent lugs each containing an aperture,

each set of mounting lugs and the lugs of a respective support fitting being engaged such that their respective apertures are aligned to receive a hinge pin forming thereby a flap hinge;

a plurality of elongated blade pitch varying means each connected at one end to a respective support fitting, and each defining a clevis for receiving a rotor blade securing pin forming thereby a fold hinge; and

a compound curved, continuous loop twin tension/torsion beam, double wrapped around the flap hinge at one end and double wrapped around the fold hinge.

2. The rotor system as defined in claim 1, wherein:

(i) one lug of each set of mounting lugs includes a bore and an outer surface in which the bore opens, said outer surface having a generally convex portion; and

(ii) each support fitting includes an outer surface between two adjacent lugs which has a generally concave portion and which is compatible with said generally convex portion both the convex portion and the concave portion cooperate to form a joint having as its center of rotation the center axis of said hinge pin.

3. The rotor system as defined in claim 2, further comprising:

a centrifugal force actuated droop stop pin carried by each support fitting, and biasing means for biasing the droop stop pin into said bore.

4. The rotor system as defined in claim 2, wherein:

(iii) the outer surface of said one lug included a generally flat portion which is joined with the generally convex portion, and said outer surface of the support fitting includes a generally flat portion which is joined with the generally concave portion, both generally flat portions serving as an in-flight droop stop.

5. The rotor system as defined in claim 1, wherein:

(i) each support fitting includes two adjacent lugs each having a curved-segment thin-walled portion about its aperture which engages the tension/torsion beam, thereby producing said double wrapped condition of the tension/torsion beam around the flap hinge; and

(ii) the clevis of each of the elongated blade pitch varying means includes two spaced curved-segment portions which engage the tension/torsion beam, thereby producing said double wrapped condition of the tension/torsion beam around the fold hinge.

6. The rotor system as defined in claim 5, further comprising:

a fairing having parallel extending upper and lower channels which receive the tension/torsion beam between its wrapped ends.

7. The rotor system as defined in claim 6, wherein:

(iii) said two adjacent lugs each further has an upper and lower channel extending from the curved-segment thin-walled portion, and oriented to align with the upper and lower channels in the fairing.

8. The rotor system as defined in claim 7, wherein:

(iv) the curved-segment portions of said two adjacent lugs are oriented substantially orthogonally to the curved-segment portions of said clevis.

9. The rotor system as defined in claim 1, wherein:

(i) each support fitting includes a receptacle; and

(ii) the elongated blade pitch varying means includes a pitch arm rotatably supported by a dry bearing positioned in said receptacle.

10. The rotor system as defined in claim 9, wherein:

(iii) the elongated blade pitch varying means further includes a torque tube connected to the pitch arm and said clevis for transmitting pitch arm motion to said clevis.

11. The rotor system as defined in claim 1, wherein:

(i) the tension/torsion beam is fabricated from predominately unidirectional glass fiber strands.

12. The rotor system as defined in claim 1, wherein:

(i) the hinge pin is surrounded by an elastomeric bearing in each lug of said plurality of adjacent lugs of each set of mounting lugs.

13. The rotor system as defined in claim 1, further comprising:

a fold actuator and lead/lag absorber connected to the support fitting and to said fold hinge.

14. The rotor system as defined in claim 13, wherein:

(i) the fold actuator and lead/lag absorber comprises a hydraulic piston and cylinder.