Load mitigation system for a multi-dimensional transducer array

• US 5,238,208 A
• Filed: 06/11/1991
• Issued: 08/24/1993
• Est. Priority Date: 06/11/1991
• Status: Expired due to Fees

• Current Assignee: Raytheon Company (Rtx Corporation)
• Original Assignee: E-Systems LLC
• Inventors: Davis, James M.
• Primary Examiner(s): BAREFOOT, GALEN L
• Application Number:
  US07/713,092
• Time in Patent Office: 805 Days
• Field of Search: 244/118.1, 244/1 R, 244/82, 244/75 A, 244/137.4, 244/135 R, 244/129.1, 343/705, 73/188
• US Class Current: 244/118.1
• CPC Class Codes: G01P 13/02 Indicating direction only, e.g. by weather vane

Abstract

A streamlined housing for supporting a multi-dimensional electromagnetic transducer array is attached to an aircraft fuselage via a pivot support. The streamlined housing is supported by the pivot support in a torsionally unrestrained manner allowing a plane containing the longitudinal axis and pivot axis of the housing to remain substantially parallel to the plane of an incident airstream. Static aeroelastic stability is provided by mounting to the aft portion of the streamlined housing one or more rigidly attached stabilizer fins. Dynamic aeroelastic stability is provided by incorporating within the streamlined housing an adjustable ballast weight.

Claims

1. An aerodynamic structure for supporting a plurality of transducers arranged in a three-dimensional array while mitigating aerodynamic impact and structural load on a host structure comprising:

a three-dimensional aerodynamically streamlined housing for supporting a plurality of transducers arranged in a three-dimensional array, said housing having a nose portion, a body portion and a tail portion shaped to effectively contain said three-dimensional array;

at least one rigidly attached stabilizer fin mounted to the tail portion of the housing for inhibiting dynamic aeroelastic instability; and

an adjustable ballast weight positioned within the nose portion of the housing for inhibiting dynamic aeroelastic instability; and

means for rotatably mounting in a torsionally unrestrained manner the aerodynamically streamlined housing to the host structure comprising a pivot means having a first end mounted to the housing at the body portion and a second end mounted to the host structure.

2. The aerodynamic structure as in claim 1 wherein the nose and tail portions have an aerodynamically streamlined shape and the body portion has a substantially tubular shape.

3. The aerodynamic structure as in claim 1 wherein the body portion has a substantially cylindrical shape.

4. The aerodynamic structure as in claim 1 wherein the body portion has a substantially ellipsoidal shape.

5. The aerodynamic structure as in claim 1 wherein the means for rotatably mounting allows the streamlined housing to pivot in a torsionally unrestrained manner for orientation in a plane containing the longitudinal axis of said housing and pivot axis substantially parallel with an incident airstream.

6. An aerodynamic load mitigation system for supporting a plurality of transducers arranged in a three-dimensional array on a host structure comprising:

a housing for supporting a plurality of transducers arranged in a three-dimensional array, said housing having a nose portion, a body portion, and a tail portion shaped to effectively contain said three-dimensional array;

a pivot mechanism having a first end attached to the host structure and rotatably attached at a second end to the body portion of the housing to mount the housing in a torsionally unrestrained manner, said pivot mechanism having a pivotal axis located between the opposed longitudinal ends of the housing;

means for mitigating the aerodynamic impact and structural load on the host structure; and

a plurality of transducers arranged in a three-dimensional array mounted to and supported by said housing.

7. The aerodynamic load mitigation system as in claim 6 wherein said means for mitigating comprises:

means for providing static aeroelastic stability; and

means for providing dynamic aeroelastic stability.

8. The aerodynamic load mitigation system as in claim 7 wherein said means for providing static aeroelastic stability comprises one or more rigidly attached stabilizer fins mounted on an aft portion of the housing.

9. The aerodynamic load mitigation system as in claim 7 wherein said means for providing dynamic aeroelastic stability comprises an adjustable ballast weight positioned within the nose portion of the housing to suppress self-excited aeroelastic instability through inertial cross-coupling.

10. The aerodynamic load mitigation system as in claim 6 wherein said means for mitigating aerodynamic impact and structural load on the host aircraft comprises one or more fins mounted to an aft portion of the housing and a ballast weight mounted within a nose portion of the housing, said ballast weight having a predetermined inertial value to provide system dynamic inertial balancing.

11. An aerodynamic structure for supporting a plurality of transducers arranged in a three-dimensional array while mitigating aerodynamic effects on a host aircraft comprising:

a three-dimensional housing for supporting the plurality of transducers arranged in a three-dimensional array, said housing having a nose portion, a body portion and a tail portion shaped to effectively contain said three-dimensional array;

means attached to the tail portion of the housing for providing static aeroelastic stability comprising one or more stabilizer fins attached to the housing;

means mounted within the nose portion of the housing for suppressing self-excited aeroelastic instability through cross-coupling to provide dynamic aeroelastic stability comprising an adjustable ballast weight; and

a pivot mechanism for rotatably mounting the housing in a torsionally unrestrained manner to the host aircraft having a first end mounted to the housing at the body portion and a second end mounted to the host aircraft.

12. The aerodynamic structure as in claim 11 wherein said housing comprises a hollow, substantially tubular center portion having two substantially conical end portions attached to the opposed ends of said center portion.

13. The aerodynamic structure as in claim 11 wherein said adjustable ballast weight has a predetermined mass and location within the housing to effect dynamic inertial cross-coupling between system nodes.

14. The aerodynamic structure as in claim 11 wherein said pivot mechanism allows a plane containing the longitudinal axis and pivot axis of the housing to substantially align itself parallel to the plane of an incident airstream.