Method for producing a composite structure including a piezoelectric element

• US 6,162,313 A
• Filed: 07/22/1998
• Issued: 12/19/2000
• Est. Priority Date: 07/29/1997
• Status: Expired due to Term

• Current Assignee: Airbus Helicopters Deutschland Gmbh (Airbus SE)
• Original Assignee: Eurocopter Deutschland Gesellschaft Mit Beschrã¤Nkter Haftung (European Aeronautic Defence and Space Company EADS NV)
• Inventors: Bansemir, Horst, Emmerling, Stefan
• Primary Examiner(s): Ball, Michael W.
• Assistant Examiner(s): CORCORAN, GLADYS JOSEFINA-PIA
• Application Number:
  US09/120,588
• Time in Patent Office: 881 Days
• Field of Search: 156/160, 156/229, 156/161, 156/163, 156/221, 156/222, 156/223, 264/229, 310/325, 310/345, 310/368, 310/358, 29/25.35, 427/100
• US Class Current: 156/163
• CPC Class Codes: B64C 2027/7283 of the piezoelectric type
• CPC Class Codes: H10N 30/073 by fusion of metals or by adhesives
• CPC Class Codes: Y02T 50/30 Wing lift efficiency

Abstract

A composite structure (3) includes a piezoelectric element (1) sandwiched between fiber composite panels (2). The composite structure can be used as an actuator element. In a method for producing the composite structure, the fiber composite panels are pre-stressed and pre-strained by applying respective pre-stressing forces (F₁, F₂) in opposite directions along two substantially perpendicular axes in the plane of the panel. The pre-stressed and pre-strained condition of the fiber composite panels (2) is maintained, while the panels are adhesively bonded (5) surfacially onto the piezoelectric element (1). After the bonding is completed, the pre-stressing forces are removed from the fiber composite panels. As a result, in the finished composite structure (3), the fiber composite panels (2) are under internal tension, while the piezoelectric element (1) is under internal compression. The pre-stressing forces (F₁, F₂) are particularly selected in magnitude and direction to achieve the required resultant balance of tension and compression within the composite structure (3). The pre-compression of the piezoelectric element (1) should be sufficient so that operating loads on the composite structure do not result in tension loading of the piezoceramic element, while substantially maintaining the useful active strain range of the overall composite structure.

Claims

1. A method of producing a composite structure including a plate-shaped piezoelectric element sandwiched and adhesively bonded between two fiber composite panels, said method comprising the following steps:

a) applying at least one tensile pre-stressing force to each of said fiber composite panels respectively in a plane of each of said fiber composite panels so as to elongate each of said fiber composite panels in said plane, wherein said at least one pre-stressing force is applied to and is effective along a force direction lying in said plane;

b) while continuing and maintaining said applying of said at least one pre-stressing force, adhesively bonding said fiber composite panels respectively onto opposite surfaces of said piezoelectric element; and

c) after said adhesive bonding has securely bonded said fiber composite panels onto said piezoelectric element, discontinuing said applying of said at least one pre-stressing force, so that said fiber composite panels respectively relax in a direction opposite said force direction in said plane and thereby an internal stress is induced in said piezoelectric element.

2. The method according to claim 1, further comprising installing said composite structure as a component in an actuator for actuating a rotor of a helicopter.

3. The method according to claim 1, wherein said piezoelectric element is a piezoceramic element, and said step of adhesive bonding comprises applying an adhesive on an entire contact interface between said piezoceramic element and each said fiber composite panel.

4. The method according to claim 1, wherein said step a) comprises applying only a single said pre-stressing force to each said fiber composite panel along a single force axis.

5. The method according to claim 1, wherein said step a) comprises applying two pre-stressing forces included in said at least one pre-stressing force, to each of said fiber composite panels, respectively along two substantially perpendicular force axes.

6. The method according to claim 1, wherein said at least one pre-stressing force applied to each said fiber composite panel in said step a) causes a pre-straining of each said fiber composite panel before said step b), and said step b) further comprises maintaining said pre-straining.

7. The method according to claim 1, wherein said adhesive bonding in said step b) comprises applying a pressing force substantially perpendicularly onto outer major surfaces of said fiber composite panels.

8. The method according to claim 1, wherein said applying of said at least one pre-stressing force comprises applying at least one external mechanical tension force to each said fiber composite panel.

9. The method according to claim 8, wherein said applying of at least one mechanical tension force comprises engaging opposite edges of each said fiber composite panel in a tension applying machine and then applying said mechanical tension force using said tension applying machine.

10. The method according to claim 1, wherein said step a) further comprises selecting and controlling a magnitude of said at least one pre-stressing force.

11. The method according to claim 10, wherein said step a) further a comprises selecting and controlling a direction of application of said at least one pre-stressing force.

12. The method according to claim 10, wherein said magnitude of said at least one pre-stressing force is selected and controlled so that after said step c), each said fiber composite panel is under an internal tension and said internal stress in said piezoelectric element is an internal compression.

13. The method according to claim 12, wherein said magnitude of said at least one pre-stressing force is selected and controlled so that said internal compression in said piezoelectric element is greater in magnitude than a tension force that will be effective on said piezoelectric element in a final installed arrangement of said composite structure, such that said piezoelectric element will always remain under internal compression.

14. The method according to claim 12, wherein said magnitude of said at least one pre-stressing force is selected and controlled so that a residual strain remaining in said fiber composite panels after said step c) is minimized.

15. The method according to claim 12, wherein said fiber composite panels have a certain panel stiffness S_v =E_v ·

t_v and said piezoelectric element has a certain element stiffness S_p =E_p ·

t_p, wherein E_v is the modulus of elasticity of said panels, t_v is the total thickness of said panels, E_p is the modulus of elasticity of said piezoelectric element, t_p is the thickness of said piezoelectric element, and a stiffness ratio S is defined as S=S_v /S_p, and wherein said magnitude of said pre-stressing force is selected and controlled such that said internal compression in said piezoelectric element does not exceed a compressive strength limit of said piezoelectric element and such that a pre-stressing ratio V defined as V=ε

_v /ε

_e wherein ε

_v is said pre-stressing force and ε

_e is said internal compression will satisfy the relationship V=(1+S)/S.

16. The method according to claim 12, wherein said fiber composite panels have a total cumulative thickness t_v and a modulus of elasticity E_v, and said piezoelectric element has a thickness t_p and a modulus of elasticity E_p, wherein a stiffness ratio S is defined as S=(E_v ·

t_v)/(E_p ·

t_p), and wherein said step of selecting and controlling said pre-stressing force comprises selecting a desired magnitude ε

_e of said internal compression of said piezoelectric element and then selecting and controlling said applied pre-stressing force to have said magnitude of said pre-stressing force defined by ε

_v =ε

_e (1/S+1).

17. The method according to claim 12, wherein said step of selecting and controlling said pre-stressing force comprises:

selecting a desired magnitude ε

_e of said internal compression in said piezoelectric element, selecting a desired coefficient of active strain η

.sub.ε

defined as η

.sub.ε

=ε

_a /ε

_p, wherein ε

_a is the active strain of said composite structure during actuation of said piezoelectric element and ε

_p is the active strain of said piezoelectric element during actuation thereof by itself not arranged in said composite structure,

determining a required magnitude ε

_v of said pre-stressing force according to ##EQU6## and selecting and controlling said magnitude of said applied pre-stressing force to be said required magnitude ε

_v.

18. The method according to claim 17, further comprising selecting at least one of a material for said fiber composite panels, a thickness dimension for said fiber composite panels, a material for said piezoelectric element, and a thickness dimension for said piezoelectric element, such that a stiffness ratio S defined as:

##EQU7## wherein E_v is the modulus of elasticity of said material for said fiber composite panels, t_v is a total of said thickness dimension of all layers of said fiber composite panels, E_p is the modulus of elasticity of said material for said piezoelectric element, t_p is said thickness dimension of said piezoelectric element,

satisfies the equation S=1/η

.sub.ε

-1.

19. The method according to claim 1, wherein said at least one tension force comprises two tensile pre-stressing forces, and said applying in said step a) comprises applying said two tension forces to each said fiber composite panel respectively along two substantially perpendicular force axes lying in said plane of each said fiber composite panel.

20. The method according to claim 1, wherein said continuing and maintaining said applying of said at least one pre-stressing force in said step b) comprises holding said pre-stressing force constant during said step b).

21. The method according to claim 1, wherein said step b) further comprises maintaining said piezoelectric element in a neutral unstressed condition during said step b), and wherein said discontinuing said applying of said at least one pre-stressing force in said step c) causes each said fiber composite panel to impose said internal stress onto said piezoelectric element as a reaction stress.

22. The method according to claim 6, wherein said continuing and maintaining said applying of said at least one pre-stressing force and said maintaining of said pre-straining in said step b) comprises holding said pre-straining of each said fiber composite panel constant during said step b).

23. The method according to claim 1, wherein said composite structure has a flat planar configuration, with said piezoelectric element and said fiber composite panels each extending respectively flat and parallel to said plane.

24. A method of producing a composite structure including a plate-shaped piezoelectric element sandwiched and adhesively bonded between two fiber composite panels, said method comprising the following steps:

a) straining and thereby elongating each of said fiber composite panels into an elongated condition in at least one strain direction respectively in a flat plane of each of said fiber composite panels;

b) while holding said fiber composite panels in said elongated condition, adhesively bonding said fiber composite panels respectively onto opposite surfaces of said piezoelectric element; and

c) after said step b), discontinuing said holding of said fiber composite panels in said elongated condition and allowing said fiber composite panels to relax opposite said straining in said at least one strain direction, thereby imposing an internal compression stress in said piezoelectric element.

25. The method according to claim 24, wherein said step b) further comprises maintaining said piezoelectric element in a neutral unstressed condition during said step b).

26. The method according to claim 24, wherein said steps a), b) and c) are carried out such that said fiber composite panels have a residual internal tension stress upon completion of said step c).

27. The method according to claim 24, wherein said composite structure has a flat planar configuration, with said piezoelectric element and said fiber composite panels each extending respectively flat and parallel to said plane.