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, 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 ▼

The invention claimed is: 1. An aircraft flight control system for dynamic adjustment of a wing's movable surfaces for effecting variable camber, comprising: a flight control system for sending command signals to movable surfaces on the wing; an actuator system for receiving said command signals an

The invention claimed is: 1. An aircraft flight control system for dynamic adjustment of a wing's movable surfaces for effecting variable camber, comprising: a flight control system for sending command signals to movable surfaces on the wing; an actuator system for receiving said command signals and positions the movable surfaces of the wing corresponding to said command signals; and a dynamic adjustment control module for computing and outputting optimal wing surface positions; the dynamic adjustment control module being programmed to perform a predictive wing surface evaluation and adjustment by determining an interval time, at each interval time, determining an approximately optimal wing surface position for a time approximately one half the interval time in the future, and positioning the wing surfaces to said optimal wing surface position. 2. An aircraft flight control system according to claim 1, wherein the flight phase in which the dynamic adjustment control module is used is the cruise flight phase. 3. An aircraft flight control system according to claim 2, wherein the dynamic adjustment control module utilizes inputs for at least altitude, speed, and Mach number for actual flight conditions of the aircraft. 4. An aircraft flight control system according to claim 3, wherein the dynamic adjustment control module computes optimum positions for inboard flaps, outboard flaps, ailerons and flaperons of the wing. 5. An aircraft flight control system according to claim 3, wherein the dynamic adjustment control module also utilizes inputs for weight and center-of-gravity of the aircraft. 6. An aircraft flight control system according to claim 3, wherein the dynamic adjustment control module also utilizes inputs for vertical speed and pilot setting of an autopilot Mode Control Panel altitude parameter of the aircraft. 7. An aircraft flight control system according to claim 3, wherein the dynamic adjustment control module computes optimum positions for the movable surfaces of the wing, at the same order of magnitude rates as non variable camber related surface commands, during a cruise flight phase of several hours duration. 8. An aircraft flight control system according to claim 3, wherein the dynamic adjustment control module 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. An aircraft flight control system according to claim 1, wherein the dynamic adjustment control module 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 repositioning load on the flaps while taking advantage of greater repositioning tolerance of the ailerons and flaperons. 10. An aircraft flight control system according to claim 1, wherein the dynamic adjustment control module includes a prediction function for aircraft weight in which the optimal wing surface positions 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. An aircraft flight control system according to claim 1, wherein the dynamic adjustment control module 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. The aircraft flight control system of claim 1, wherein: the dynamic adjustment control module is further programmed to, at each interval of time: determine a stored fuel consumption value; determine a current fuel consumption value; compare the current fuel consumption value to the stored fuel consumption value, actuate 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. The aircraft flight control system of claim 1, wherein: the dynamic adjustment control module is farther programmed to determine an optimal wing surface position for a time approximately one half the interval time in the future based upon an inputted current flight path.