IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0936421
(2009-04-07)
|
등록번호 |
US-8408498
(2013-04-02)
|
우선권정보 |
DE-10 2008 017 574 (2008-04-07) |
국제출원번호 |
PCT/EP2009/002573
(2009-04-07)
|
§371/§102 date |
20101005
(20101005)
|
국제공개번호 |
WO2009/124728
(2009-10-15)
|
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
Dernier, Esq., Matthew B.
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
4 |
초록
▼
An aerodynamic body with an outside with a top and bottom in relation to the direction of airflow, with lateral end parts that form the lateral ends of the aerodynamic body when viewed across the direction of airflow, where in the interior of the aerodynamic body a duct with an airflow drive with a
An aerodynamic body with an outside with a top and bottom in relation to the direction of airflow, with lateral end parts that form the lateral ends of the aerodynamic body when viewed across the direction of airflow, where in the interior of the aerodynamic body a duct with an airflow drive with a drive motor and a compressor means that is driven by the aforesaid and that is arranged in the duct is arranged, with at least one inlet at the bottom and/or at at least one of the lateral end parts of the aerodynamic body and with at least one outlet at the top of the aerodynamic body for influencing the airflow at the aerodynamic body is arranged, where in the duct a sleeve is arranged which is rotatable by means of a drive motor, which sleeve includes at least one recess which at a particular rotational position of the sleeve can be made to at least in part coincide with the outlet at the top of the aerodynamic body so that the air that has been compressed by the compressor flows through the recess in the sleeve and through the outlet, as well as a high-lift system comprising such an aerodynamic body.
대표청구항
▼
1. An aerodynamic body for at least one of an airfoil, a leading-edge device and a trailing-edge device of an aircraft, comprising: an outside having a top and bottom in relation to a direction of airflow,lateral end parts that form lateral ends of the aerodynamic body when viewed across the directi
1. An aerodynamic body for at least one of an airfoil, a leading-edge device and a trailing-edge device of an aircraft, comprising: an outside having a top and bottom in relation to a direction of airflow,lateral end parts that form lateral ends of the aerodynamic body when viewed across the direction of airflow,arranged in an interior of the aerodynamic body, the duct including an airflow drive with a first drive motor and a compressor means that is driven by the aforesaid, and the duct having at least one inlet at one or more of: (i) the bottom, and (ii) at least one of the lateral end parts of the aerodynamic body, and having at least one outlet at the top of the aerodynamic body for influencing the airflow at the aerodynamic body,wherein a sleeve arranged within the duct which is rotatable by means of a second drive motor, which sleeve comprises at least one recess which at a particular rotational position of the sleeve is made to at least in part coincide with the at least one outlet at the top of the aerodynamic body so that the air that has been compressed by the compressor flows through the recess in the sleeve and through the outlet, anda flow-through adjustment device arranged at the outlet which can change a size of the outlet in order to influence the air throughput that occurs at the outlet. 2. The aerodynamic body of an aircraft according to claim 1, wherein at least one of: the recess of the rotatable sleeve has the form of a slit that extends in an axial direction of the sleeve, andthe sleeve comprises several recesses, which in circumferential direction of the sleeve, are arranged so as to be distributed over a circumference of the sleeve. 3. The aerodynamic body of an aircraft according to claim 1, wherein the outlet has the form of a slit that extends in span direction of the aerodynamic body. 4. The aerodynamic body of an aircraft according to claim 1, wherein the outlet comprises several apertures that are arranged one behind the other along the span direction of the aerodynamic body. 5. The aerodynamic body of an aircraft according to claim 4, wherein the outlet of the duct is formed by several slits at the top of the aerodynamic body with the longitudinal directions of said slits extending across the direction of airflow, and with said slits being arranged one behind the other when viewed in their longitudinal direction. 6. The aerodynamic body of an aircraft according to claim 4, wherein the outlet of the duct is formed by several slits at the top of the aerodynamic body of an aircraft, with the longitudinal directions of said slits extending across the direction of airflow, and with said slits being arranged one behind the other when viewed in the direction of airflow. 7. The aerodynamic body of an aircraft according to claim 1, wherein a width of the sleeve, which width extends in a circumferential direction of said sleeve, measures at least 75% of a width of the outlet at the top of the aerodynamic body of an aircraft, which width extends in the direction of airflow. 8. The aerodynamic body of an aircraft according to claim 1, wherein the flow-through adjustment device comprises an aperture part that is arranged on the outlet and that is pre-tensioned to the closed position of the inlet, which aperture part is set in such a manner that the aperture part at a predetermined first pressure occurring at the outlet moves to an open position, while at a predetermined second pressure occurring at the outlet moves to the closed position. 9. The aerodynamic body of an aircraft according to claim 1, wherein at the recess a further flow-through adjustment device is arranged that changes a size of the recess in order to influence the air throughput that occurs at the recess. 10. The aerodynamic body of an aircraft according to claim 9, wherein the further flow-through adjustment device comprises an aperture part that is arranged on the recess and that is pre-tensioned to the closed position of the inlet, which aperture part is set in such a manner that the aperture part at a predetermined first pressure occurring at the recess moves to an open position, while at a predetermined second pressure occurring at the recess moves to the closed position. 11. The aerodynamic body of an aircraft according to claim 1, wherein the flow-through adjustment device is actively controlled. 12. The aerodynamic body of an aircraft according to claim 1, wherein the airflow drive is an axial compressor and the compressor means comprises impeller blades whose rotary axis extends in longitudinal direction of the duct. 13. The aerodynamic body of an aircraft according to claim 1, wherein the compressor is a radial compressor and the compressor means comprises a compressor impeller. 14. The aerodynamic body of an aircraft according to claim 1, wherein the sleeve is rotationally coupled to the compressor means so that the first drive motor of the compressor means is the second drive motor of the sleeve. 15. A high-lift system of an aircraft comprising: an aerodynamic body, comprising: an outside having a top and bottom in relation to a direction of airflow,lateral end parts that form lateral ends of the aerodynamic body when viewed across the direction of airflow,a duct arranged in an interior of the aerodynamic body, the duct including an airflow drive with a first drive motor and a compressor means that is driven by the aforesaid, and the duct having at least one inlet at one or more of: (i) the bottom, and (ii) at least one of the lateral end parts of the aerodynamic body, and having at least one outlet at the top of the aerodynamic body for influencing the airflow at the aerodynamic body,a sleeve arranged within the duct which is rotatable by means of a second drive motor, which sleeve comprises at least one recess which at a particular rotational position of the sleeve is made to at least in part coincide with the at least one outlet at the top of the aerodynamic body so that the air that has been compressed by the compressor flows through the recess in the sleeve and through the outlet, anda flow-through adjustment device arranged at the outlet which can change a size of the outlet in order to influence the air throughput that occurs at the outlet, anda control device by means of which the drive device of at least one of the sleeve and the compressor means is functionally coupled, and which control device comprises a control function to form positioning signals or positioning commands for setting at least one of: a rotational position of the sleeve in the duct, the speed of rotation of the sleeve, a rotational position of the compressor means, and the speed of rotation of the compressor means. 16. The high-lift system according to claim 15, wherein the control device is an input device for receiving at least one of: sensor data and system data, and the control function determines the positioning commands for setting at least one of: a rotational position of the sleeve in the duct, and the speed of rotation of the sleeve, depending on the adjustment state of the aerodynamic body of an aircraft. 17. The high-lift system according to claim 15, wherein: the control device comprises an input device by means of which the control device can receive at least one of: sensor data and system data, andthe control function determines the positioning commands for setting at least one of: a rotational position of the sleeve in the duct, and the speed of rotation of the sleeve, depending on the at least one of: sensor data and system data. 18. The high-lift system according to claim 15, wherein: the input device of the control device is equipped to receive data from the flight control system of the aircraft, andthe control function determines the positioning commands for setting at least one of: a rotational position of the sleeve in the duct, and the speed of rotation of the sleeve, depending on the data of a flight control system. 19. The high-lift system according to claim 18, wherein: the data received by the flight control system of the aircraft comprises at least one of:the rotational position of the sleeve in the duct and the speed of rotation of the sleeve, andthe control function determines the positioning commands relating to at least one of: the rotational position of the sleeve in the duct and the speed of rotation of the sleeve depending on the adjustment position of the aerodynamic body of an aircraft. 20. The high-lift system according to claim 18, wherein the control function determines the positioning commands relating to at least one of: the rotational position of the sleeve in the duct and the speed of rotation of the sleeve, depending on air data that has been transmitted by the flight control system and depending on at least one of: an angle of attack of the aircraft, a speed, and a flight attitude of the aircraft. 21. The high-lift system according to claim 15, wherein: the control device for commanding at least one of: the rotational position of the sleeve in the duct and the speed of rotation of the sleeve comprises a comparison function that compares at least one of: transmitted air data and the adjustment position of the aerodynamic body of an aircraft with a first desired value and with a second desired value,when the first desired value is attained in some regions the control function generates control commands for activating the drive of the sleeve, andwhen the second desired value is attained in some regions the control function generates control commands for stopping the drive of the sleeve and transmits the aforesaid to the flow-through adjustment device. 22. The high-lift system according to claim 15, wherein the aerodynamic body comprises at least one pressure sensor that is arranged on the aerodynamic body for the purpose of measuring the static pressure of the airflow, and that is functionally connected to the input device for the purpose of transmitting the measured pressure to the control function, and the control function is designed in such a manner that it determines positioning commands depending on the measured pressure. 23. The high-lift system according to claim 22, wherein: the control device comprises a comparison function by means of which the pressures on the at least one inlet and on the at least one outlet are compared, andthe positioning commands are determined depending on the pressure differential determined.
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