IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0620698
(2009-11-18)
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등록번호 |
US-8447445
(2013-05-21)
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발명자
/ 주소 |
- Onu, Dan
- Winter, John D.
- Carr, Candy L.
- Vijgen, Paul M.
- Emch, Gary A.
- Renzelmann, Michael E.
|
출원인 / 주소 |
|
대리인 / 주소 |
Ostrager Chong Flaherty & Broitman P.C.
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인용정보 |
피인용 횟수 :
0 인용 특허 :
8 |
초록
▼
The movable surfaces affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift/drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic adjustment control module provides command signals for optimum positio
The movable surfaces affecting the camber of a wing are dynamically adjusted to optimize wing camber for optimum lift/drag ratios under changing conditions during a given flight phase. In a preferred embodiment, an add-on dynamic adjustment control module provides command signals for optimum positioning of trailing edge movable surfaces, i.e., inboard flaps, outboard flaps, ailerons, and flaperons, which are used in place of the predetermined positions of the standard flight control system. The dynamic adjustment control module utilizes inputs of changing aircraft conditions such as altitude, Mach number, weight, center of gravity (CG), vertical speed and flight phase. The dynamic adjustment control module's commands for repositioning the movable surfaces of the wing are transmitted through the standard flight control system to actuators for moving the flight control surfaces.
대표청구항
▼
1. A dynamic adjustment control module used in an aircraft for enabling repositioning of movable surfaces of a wing of the aircraft during a given flight phase in order to optimize wing camber for optimum lift/drag ratios, comprising: a variable camber control logic implemented as software running o
1. A dynamic adjustment control module used in an aircraft for enabling repositioning of movable surfaces of a wing of the aircraft during a given flight phase in order to optimize wing camber for optimum lift/drag ratios, comprising: a variable camber control logic implemented as software running on an onboard computer for operating a computerized aircraft flight control system, wherein said variable camber control logic is configured to perform a predictive wing surface evaluation and adjustment by: determining an interval time,determining an approximately optimal wing surface position for a future time within said interval time, in response to inputs indicating actual flight conditions of the aircraft, andtransmitting command signals to the aircraft flight control system for repositioning the movable surfaces of the wing to said approximately optimal wing surface position. 2. A dynamic adjustment control module according to claim 1, wherein the variable camber control logic is enabled for operation during a cruise phase of the aircraft's flight. 3. A dynamic adjustment control module according to claim 2, wherein the variable camber control logic utilizes inputs for at least altitude, speed, and Mach number for actual flight conditions of the aircraft. 4. A dynamic adjustment control module according to claim 3, wherein the variable camber control logic computes optimum positions for the inboard flaps, outboard flaps, ailerons and flaperons of the wing. 5. A dynamic adjustment control module according to claim 3, wherein the variable camber control logic also utilizes inputs for weight and center-of-gravity of the aircraft. 6. A dynamic adjustment control module according to claim 3, wherein the variable camber control logic also utilizes inputs for vertical speed and pilot setting of Mode Control Panel altitude of the aircraft. 7. A dynamic adjustment control module according to claim 2, wherein the variable camber control logic computes optimum positions for the movable surfaces of the wing at approximately half-hour intervals during a cruise flight phase of several hours duration. 8. A dynamic adjustment control module according to claim 1, wherein the variable camber control logic is enabled to output optimum positions for the movable surfaces only if the actual flight conditions are detected to be in effect for a given amount of time as an enablement time threshold. 9. A dynamic adjustment control module according to claim 1, wherein the variable camber control logic includes a surface coordination function in which optimum positions for the ailerons and flaperons are computed while using existing positions for the flaps, in order to reduce the repositioning load on the flaps while taking advantage of greater repositioning tolerance of the ailerons and flaperons. 10. A dynamic adjustment control module according to claim 1, wherein the variable camber control logic includes a prediction function for aircraft weight in which the optimum positions for the movable surfaces are computed with a predicted weight later in time than the interval time in order to avoid the need for repositioning of the movable surfaces at the later time. 11. A dynamic adjustment control module according to claim 1, wherein the variable camber control logic includes a learning function in which aircraft and wing characteristics that vary over the life of the aircraft are stored and utilized as inputs in computing optimum positions for the movable surfaces. 12. A dynamic adjustment control module according to claim 1, wherein the variable camber control logic is further configured to: determine a stored fuel consumption value;determine a current fuel consumption value;compare the current fuel consumption value to the stored fuel consumption value; andactuate the wing surfaces to a stored position if the stored fuel consumption is lower than the current fuel consumption, or store the current wing surface positions if the current fuel consumption is lower than the stored fuel consumption. 13. A dynamic adjustment control module according to claim 1, wherein the variable camber control logic is further configured to: determine an optimal wing surface position for a future time within said interval time based on an inputted current flight path. 14. A computer configured to perform a predictive wing surface evaluation and adjustment for a wing of an aircraft by performing the following steps: determining an interval time,determining an approximately optimal wing surface position for the wing for a future time within said interval time, in response to inputs indicating current flight conditions of the aircraft, andtransmitting command signals to an aircraft flight control system for repositioning movable surfaces of the wing to said approximately optimal wing surface position. 15. A computer memory according to claim 14, further configured to cause the one or more processors to perform the following steps: determine a stored fuel consumption value;determine a current fuel consumption value;compare the current fuel consumption value to the stored fuel consumption value; andactuate the wing surfaces to a stored position if the stored fuel consumption is lower than the current fuel consumption, or store the current wing surface positions if the current fuel consumption is lower than the stored fuel consumption. 16. A dynamic adjustment control module according to claim 14, further configured to cause the one or more processors to perform the following steps: determine an optimal wing surface position for a future time within said interval time based on an inputted current flight path. 17. A computer implemented method for performing a predictive wing surface evaluation and adjustment for a wing of an aircraft by performing the following steps: determining an interval time,determining an approximately optimal wing surface position for the wing for a future time within said interval time, in response to inputs indicating current flight conditions of the aircraft, andtransmitting command signals to an aircraft flight control system for repositioning movable surfaces of the wing to said approximately optimal wing surface position. 18. A computer implemented method according to claim 17, further comprising: determining a stored fuel consumption value;determining a current fuel consumption value;comparing the current fuel consumption value to the stored fuel consumption value; andactuating the wing surfaces to a stored position if the stored fuel consumption is lower than the current fuel consumption, or store the current wing surface positions if the current fuel consumption is lower than the stored fuel consumption. 19. A computer implemented method according to claim 17, further comprising: determining an optimal wing surface position for a future time within said interval time based on an inputted current flight path.
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