A system and method for reducing aerodynamic drag is disclosed. A compression seal is attached to the inboard edges of the stabilizer and elevators of an airplane. The seal blocks airflow in a gap located between these inboard edges and a fuselage. The shape of the compression seal changes as the sh
A system and method for reducing aerodynamic drag is disclosed. A compression seal is attached to the inboard edges of the stabilizer and elevators of an airplane. The seal blocks airflow in a gap located between these inboard edges and a fuselage. The shape of the compression seal changes as the shape of the gap changes due to movement of the stabilizer and elevators during flight to effectively block airflow through the gap during flight. By blocking the airflow, the seal reduces the aerodynamic drag of the airplane.
대표청구항▼
1. A system for reducing aerodynamic drag, comprising: an adjustable flight control surface of an airplane;a bulb seal connected to the flight control surface such that the bulb seal blocks airflow through a non-constant gap located between the flight control surface and a fuselage of the airplane;
1. A system for reducing aerodynamic drag, comprising: an adjustable flight control surface of an airplane;a bulb seal connected to the flight control surface such that the bulb seal blocks airflow through a non-constant gap located between the flight control surface and a fuselage of the airplane; anda fastener connecting the bulb seal to the flight control surface, the fastener including a non-metallic seal retainer extending along an attachment surface of the bulb seal, wherein the non-metallic seal retainer is configured to provide support to the bulb seal as external pressures from the fuselage deform the bulb seal,a nut plate retainer strip located between a nut plate and the seal retainer, anda bolt that connects the nut plate to the flight control surface through the nut plate retainer strip, the seal retainer, and the attachment surface of the bulb seal. 2. The system of claim 1, wherein the bulb seal is composed of a non-metallic material. 3. The system of claim 1, wherein the bulb seal is composed of silicone. 4. The system of claim 1, wherein the flight control surface is a horizontal stabilizer. 5. The system of claim 1, wherein the flight control surface is an elevator. 6. The system of claim 1, wherein the bulb seal is connected to the flight control surface with a row of fasteners through a seal retainer. 7. The system of claim 6, wherein the retainer is composed of a carbon composite fabric. 8. The system of claim 6, wherein the bulb seal and the seal retainer include slotted holes. 9. The system of claim 8, wherein the row of fasteners connects the seal retainer to the flight control surface through the slotted holes of the seal retainer and the bulb seal. 10. A method of reducing aerodynamic drag, comprising: placing an exterior surface of a handle of a P-bulb seal adjacent to an inboard edge of an adjustable flight control surface of an airplane;positioning a fastener adjacent to an opposite exterior surface of the handle of the P-bulb seal;locating a nut plate retainer strip between a nut plate and a non-metallic seal retainer;utilizing a bolt to connect the nut plate to the flight control surface through the nut plate retainer strip, the seal retainer, and the handle of a P-bulb seal; andattaching the handle of the P-bulb seal to the flight control surface with the fastener, wherein a bulb of the P-bulb seal fills a non-constant gap located between the flight control surface and a fuselage of the airplane, andwherein the non-metallic seal retainer is configured to provide support to the P-bulb seal as external pressures from the fuselage deform the P-bulb seal. 11. The method of claim 10, further comprising applying a low friction coating on the fuselage. 12. The method of claim 10, wherein the flight control surface is a trailing edge panel of a horizontal stabilizer. 13. The method of claim 10, wherein the flight control surface is an elevator panel of an elevator. 14. The method of claim 10, wherein the bulb of the P-bulb seal changes shape as the flight control surface moves relative to the fuselage during flight. 15. A system for reducing aerodynamic drag, comprising: a fuselage of an airplane;an adjustable flight control surface of the airplane, wherein a non-constant gap is located between the fuselage and the flight control surface;a seal attached to the flight control surface that contacts the fuselage as the flight control surface is adjustable during flight; anda fastener connecting the bulb seal to the flight control surface, the fastener including a non-metallic seal retainer extending along an attachment surface of the bulb seal, wherein the non-metallic seal retainer is configured to provide support to the bulb seal as external pressures from the fuselage deform the bulb seal,a nut plate retainer strip located between a nut plate and the seal retainer, anda bolt that connects the nut plate to the flight control surface through the nut plate retainer strip, the seal retainer, and the attachment surface of the bulb seal. 16. The system of claim 15, wherein the flight control surface is a horizontal stabilizer. 17. The system of claim 15, wherein the flight control surface is an elevator. 18. The system of claim 15, wherein the seal is a compression seal.
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