Composite cuff structure for helicopter rotors

• US 5,645,400 A
• Filed: 03/18/1996
• Issued: 07/08/1997
• Est. Priority Date: 03/18/1996
• Status: Expired due to Term

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Scherer, Karl B., Hunter, David H.
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): VERDIER, CHRISTOPHER M
• Application Number:
  US08/617,012
• Time in Patent Office: 477 Days
• Field of Search: 416/134 A, 416/138, 416/141, 416/230, 416/244 R
• US Class Current: 416/134.00A
• CPC Class Codes: B64C 27/33 having flexing arms

Abstract

A composite cuff structure (40) for mounting the root end (14e) of a rotor blade assembly (14) to the radial arms (24a, 24b) of a rotor assembly yoke (24) and for accommodating a twist disparity therebetween. The composite cuff structure (40) is generally tubular in shape and is fabricated from a composite material having reinforcing fibers (70) disposed in a binding matrix. The composite cuff structure (40), furthermore, includes a blade-receiving sleeve portion (42), a yoke mounting portion (44), spanwise fold portions (46) and sidelobe portions (48), which portions (42, 44, 46, 48) are structurally integrated to form a unitary body. The blade-receiving sleeve portion (42) is disposed in combination with the root end (14e) of the rotor blade assembly (14) and includes first and second blade mounting segments (42a, 42b), which define a rotor blade attachment plane P_B. The yoke mounting portion (44) is disposed in combination with the radial arms (24a, 24b) of the rotor assembly yoke (24) and includes fore and aft pairs (44-1, 44-2) of first and second yoke mounting segments (44a, 44b) defining a yoke attachment plane P_Y. The pairs (44-1, 44-2) of yoke mounting segments (44a, 44b) are, furthermore, disposed laterally of the blade mounting segments (42a, 42b). The spanwise fold portions (46) include first and second complementary curve segments (46a, 46b) for structurally interconnecting the blade and yoke mounting segments (42a, 42b, 44a, 44b) such that the rotor blade attachment plane P_B forms an angle θ with respect to the yoke attachment plane P_Y. The sidelobe portions (48) include fore and aft curved segments (48a, 48b) for structurally interconnecting the first and second yoke mounting segments (44a, 44b).

Claims

1. A composite cuff structure (40) for mounting a root end (14e) of a rotor blade assembly (14) to radial arms (24a, 24b) of a rotor assembly yoke (24), the composite cuff structure (40) characterized by:

a unitary body having a generally tubular shape and including;

a blade-receiving sleeve portion (42) for being disposed in combination with the root end (14e) of the rotor blade assembly (14), said blade-receiving portion (42) having first and second blade mounting segments (42a, 42b) which define a rotor blade attachment plane P_B,

a yoke mounting portion (44) for being disposed in combination with the radial arms (24a, 24b) of the rotor assembly yoke (24), said yoke mounting portion (44) having fore and aft pairs (44-1, 44-2) of first and second yoke mounting segments (44a, 44b), said pairs (44-1, 44-2) being disposed laterally of said blade mounting segments (42a, 42b), said yoke mounting segments (44a, 44b) defining a yoke attachment plane P_Y ;

spanwise fold portions (46) having first and second complementary curve segments (46a, 46b) for structurally interconnecting said blade and yoke mounting segments (42a, 42b, 44a, 44b), such that said rotor blade attachment plane P_B forms an angle θ

with respect to said yoke attachment plane P_Y ; and

sidelobe portions (48) having fore and aft curved segments (48a, 48b) for structurally interconnecting said first and second yoke mounting segments (44a, 44b);

said unitary body, furthermore, being fabricated from a composite material having reinforcing fibers (70) disposed in a binding matrix.

2. The composite cuff structure (40) according to claim 1

wherein said angle θ

is between about 4 degrees to about 30 degrees.

3. The composite cuff structure (40) according to claim 1

wherein said unitary body defines a longitudinal axis (40_L);

and

wherein said spanwise fold portions (46) define longitudinal contour lines (58) which are substantially parallel to said longitudinal axis (40_L).

4. The composite cuff structure (40) according to claim 1

wherein said first and second blade mounting segments (42a, 42b) and said first and second complementary curve segments (46a, 46b) each have a characteristic stiffness, said characteristic stiffness of at least one of said complementary curve segments (46a or 46b) being less than said characteristic stiffness of an adjacent blade mounting segment (42a or 42b).

5. The composite cuff structure (40) according to claim 4

wherein said characteristic stiffness of said at least one said complementary curve segments (46a or 46b) is between about 35% to about 75% of said characteristic stiffness of said adjacent blade mounting segment (42a, 42b).

6. The composite cuff structure (40) according to claim 4

wherein said characteristic stiffness of each of said first complementary curve segments (46a) is less than said characteristic stiffness of said adjacent blade mounting segment (42a or 42b).

7. The composite cuff structure (40) according to claim 4

wherein said characteristic stiffness of an outboard end (46e_o) of said at least one said complementary curve segments (46a or 46b) is between about 35% to about 75% of said characteristic stiffness of said adjacent blade mounting segment (42a, 42b).

8. The composite cuff structure (40) according to claim 3

wherein said composite material includes unidirectional and off-axis fibers (70), said unidirectional fibers (70) being substantially parallel to said longitudinal axis (40_L).

9. The composite cuff structure (40) according to claim 8

wherein said off-axis fibers (70) are oriented at ±

45/±

90 degrees relative to said longitudinal axis (40_L) to form a quasi-isotropic lay-up.

10. A composite cuff structure (40) for mounting a root end (14e) of a rotor blade assembly (14) to radial arms (24a, 24b) of a rotor assembly yoke (24), the composite cuff structure (40) characterized by:

a unitary body having a generally tubular shape and defining a longitudinal axis (40_L), said unitary body including;

a blade-receiving sleeve portion (42) for being disposed in combination with the root end (14e) of the rotor blade assembly (14), said blade-receiving portion (42) having first and second blade mounting segments (42a, 42b) which define a rotor blade attachment plane P_B,

a yoke mounting portion (44) for being disposed in combination with the radial arms (24a, 24b) of the rotor assembly yoke (24), said yoke mounting portion (44) having fore and aft pairs (44-1, 44-2) of first and second yoke mounting segments (44a, 44b), said pairs (44-1, 44-2) being disposed laterally of said blade mounting segments (42a, 42b), said yoke mounting segments (44a, 44b) defining a yoke attachment plane P_Y ;

spanwise fold portions (46) having first and second complementary curve segments (46a, 46b) for structurally interconnecting said blade and yoke mounting segments (42a, 42b, 44a, 44b), such that said rotor blade attachment plane P_B forms an angle θ

with respect to said yoke attachment plane P_Y, said angle θ

being between about 4 degrees to about 30 degrees with respect to said yoke attachment plane P_Y,

said spanwise fold segments (46a, 46b), furthermore defining longitudinal mold lines (58), said longitudinal mold lines (58) being substantially parallel to said longitudinal axis (40_L); and

sidelobe portions (48) having fore and aft curved segments (48a, 48b) for structurally interconnecting said first and second yoke mounting segments (44a, 44b);

said unitary body, furthermore, being fabricated from a composite material having reinforcing fibers (70) disposed in a binding matrix.

11. A rotor hub assembly (10) having a rotor assembly yokes (24) for driving a plurality of rotor blades assemblies (14), the rotor blades assemblies (14) each having a root end (14e) for mounting to radial arms (24a, 24b) of each rotor assembly yoke, the root end portion (14e) and the respective radial arms (24a, 24b) having a twist disparity therebetween, said rotor hub assembly (10) being characterized by:

a composite cuff structure (40) for mounting in combination with the root end (14e) of each rotor blade assembly (14) and the radial arms (24a, 24b) of each rotor assembly yoke (24), each said composite cuff structure (40) defining a unitary body having a generally tubular shape, said unitary body including;

a blade-receiving sleeve portion (42) for being disposed in combination with the root end (14e) of the rotor blade assembly (14), said blade-receiving portion (42) having first and second blade mounting segments (42a, 42b) which define a rotor blade attachment plane P_B,

a yoke mounting portion (44) for being disposed in combination with the radial arms (24a, 24b) of the rotor assembly yoke (24), said yoke mounting portion (44) having fore and aft pairs (44-1, 44-2) of first and second yoke mounting segments (44a, 44b), said pairs (44-1, 44-2) being disposed laterally of said blade mounting segments (42a, 42b), said yoke mounting segments (44a, 44b) defining a yoke attachment plane P_Y ;

spanwise fold portions (46) having first and second complementary curve segments (46a, 46b) for structurally interconnecting said blade and yoke mounting segments (42a, 42b, 44a, 44b), such that said rotor blade attachment plane P_B forms an angle θ

with respect to said yoke attachment plane P_Y ; and

sidelobe portions (48) having fore and aft curved segments (48a, 48b) for structurally interconnecting said first and second yoke mounting segments (44a, 44b);

said unitary body, furthermore, being fabricated from a composite material having reinforcing fibers (70) disposed in a binding matrix.

12. The composite cuff structure (40) according to claim 11

wherein said angle θ

is between about 4 degrees to about 30 degrees.

13. The composite cuff structure (40) according to claim 11

wherein said unitary body defines a longitudinal axis (40_L);

and

wherein said spanwise fold portions (46) define longitudinal contour lines (58) which are substantially parallel to said longitudinal axis (40_L).

14. The composite cuff structure (40) according to claim 11

wherein said first and second blade mounting segments (42a, 42b) and said first and second complementary curve segments (46a, 46b) each have a characteristic stiffness, said characteristic stiffness of at least one of said complementary curve segments (46a or 46b) being less than said characteristic stiffness of an adjacent blade mounting segment (42a or 42b).

15. The composite cuff structure (40) according to claim 14

wherein said characteristic stiffness of said at least one said complementary curve segments (46a or 46b) is between about 35% to about 75% of said characteristic stiffness of said adjacent blade mounting segment (42a, 42b).

16. The composite cuff structure (40) according to claim 14

wherein said characteristic stiffness of each of said first complementary curve segments (46a) is less than said characteristic stiffness of said adjacent blade mounting segment (42a or 42b).

17. The composite cuff structure (40) according to claim 14

wherein said characteristic stiffness of an outboard end (46e_o) of said at least one said complementary curve segments (46a or 46b) is between about 35% to about 75% of said characteristic stiffness of said adjacent blade mounting segment (42a, 42b).

18. The composite cuff structure according to claim 13

wherein said composite material includes unidirectional and off-axis fibers (70), said unidirectional fibers (70) being substantially parallel to said longitudinal axis (40_L).

19. The composite cuff structure according to claim 18

wherein said off-axis fibers (70) are oriented at ±

45/±

90 degrees relative to said longitudinal axis (40_L) to form a quasi-isotropic lay-up.