1. A pixel device of a transflective-type liquid crystal panel comprising:
an upper panel;
a lower panel assembled beneath said upper panel and further having an upper surface divided into a reflective region and a transmission region;
a liquid crystal layer interposed between said upper panel and said lower panel; and
a liquid crystal film, which is set with an opposing spiral direction with respect to that of said liquid crystal layer, formed on said liquid crystal layer to compensate retardation of said liquid crystal layer,
wherein a stacked structure comprises said liquid crystal layer in the reflective region and said liquid crystal film, the stacked structure acts as an optical modulation structure adapted to as a quarter-wave plate when no operation voltage being applied.
2. The pixel device of claim 1, wherein a retardation difference between said liquid crystal film and said liquid crystal layer in said transmission region is less than 30 nm.
3. The pixel device of claim 1, wherein respective liquid crystal molecules in said liquid crystal film and said liquid crystal layer are perpendicular to each other.
4. The pixel device of claim 1, wherein respective liquid crystal molecules in said liquid crystal film and said liquid crystal layer make an angle of 80 to 100 degrees.
5. The pixel device of claim 1, wherein a twist angle difference between said liquid crystal film and said liquid crystal layer is less than 10 degrees.
6. The pixel device of claim 1, further comprising a first polarizer on an upper surface of said upper panel and a second polarizer on a lower surface of said lower panel, and respective transmission axes of the first polarizer and the second polarizer are perpendicular to each other.
7. The pixel device of claim 1, wherein said liquid crystal film is a polymer film.
8. The pixel device of claim 1, wherein said liquid crystal layer is one of a twisted nematic type, a super twisted nematic type, and an hybrid nematic type, and said liquid crystal layer and said liquid crystal film belong to the same type.
9. The pixel device of claim 1, wherein the pixel device is applied in a normal-black transflective-type liquid crystal display.
10. A pixel device of a transflective-type liquid crystal panel comprises:
an upper panel having a first polarizer formed on an upper surface thereof;
a lower panel, which has a second polarizer formed on a lower surface thereof, assembled beneath said upper panel and having an upper surface thereof divided into a reflective region and a transmission region, wherein respective transmission axes of the first polarizer and the second polarizer are perpendicular to each other;
a liquid crystal layer interposed between said upper panel and said lower panel; and
a liquid crystal film, which is set with an opposing spiral direction with respect to said liquid crystal layer, formed on said liquid crystal layer, wherein respective liquid crystal molecules in said liquid crystal film and said liquid crystal layer are perpendicular to each other to compensate retardation of said liquid crystal layer so as to have a backlight shielded by said first polarizer;
wherein a thickness of said liquid crystal layer in the reflective region is smaller than that in the transmission region, and a stacked structure composed of said liquid crystal layer in the reflective region and said liquid crystal film performs as an optical modulation structure like a quarter-wave plate when no operation voltage being applied.
11. The pixel device of claim 10, wherein said liquid crystal film is set with another retardation the same as said liquid crystal layer in amount but opposite in direction.
12. The pixel device of claim 10, wherein a retardation difference between said liquid crystal film and said liquid crystal layer in said transmission region is less than 30 nm.
13. The pixel device of claim 10, wherein a twist angle difference between said liquid crystal film and said liquid crystal layer is less than 10 degrees.
14. The pixel device of claim 10, wherein said liquid crystal film is a polymer film.
15. The pixel device of claim 10, wherein said liquid crystal layer is one of a twisted nematic type, a super twisted nematic type, and a hybrid nematic type, and said liquid crystal layer and said liquid crystal film are of the same type.
16. The pixel device of claim 10, wherein the pixel device is applied in a normal-black transflective-type liquid crystal display.
The claims below are in addition to those above.
All refrences to claim(s) which appear below refer to the numbering after this setence.
1. An aircraft (F) with wings (1; 1a, 1b) and a system for minimizing the influence of unsteady flow states, wherein the wing consists of a respective main wing (M) and at least one control flap (S) adjustably arranged relative thereto, an adjusting drive (21) for activating the at least one control flap (S), as well as a sensor arrangement for acquiring the setting position of the control flap (S), and the aircraft further exhibits:
a presetting device (30) for generating desired parameters (30a) corresponding to flight states of the aircraft,
a flight state sensor arrangement (40) for generating flight state data (40a),
a flight control device, which is functionally connected with the presetting device (30), the adjusting drive (21) and the sensor arrangement for acquiring the setting position of the control flap (S), so as to adjust the aircraft to the flight states corresponding to the desired parameters (30a),
characterized in that the system for minimizing the influence of unsteady flow states exhibits:
at least one arrangement (15) of flow-influencing devices (16) for influencing the fluid flow over the surface segment (10), which are functionally connected with the flight control device, and incorporated in at least one surface segment (10; 11a, 12a; 11b, 12b) of the main wing (M) of each wing (M; 1a, 1b) extending in a respective wingspan direction andor at least one control flap (S),
a detection device for detecting unsteady flow states acting on the aircraft,
an actuating function that is functionally connected with the flow-influencing devices (16) to influence the flow in the different segments of a wing (1; 1a, 1b), designed in such a way that the latter, based on the unsteady flow states detected by the detection device and setting position of the control flap (S) acquired by the sensor arrangement, actuate the flow-influencing devices (16) so as to minimize the influence of unsteady free flow states on the aircraft.
2. An aircraft (F) with wings (1; 1a, 1b) and a system for minimizing the influence of unsteady flow states, wherein the wing consists of a respective main wing (M) and at least one control flap (S) adjustably arranged relative thereto, a adjusting drive (21) for activating the at least one control flap (S), a sensor arrangement for acquiring the setting position of the control flap (S), and at least one trailing edge flap, wherein the aircraft further exhibits:
a presetting device (30) for generating desired parameters (30a) corresponding to flight states of the aircraft,
a flight state sensor arrangement (40) for generating flight state data (40a),
a flight control device, which is functionally connected with the presetting device (30), the adjusting drive (21) and the sensor arrangement for acquiring the setting position of the control flap (S), so as to set the aircraft to the flight states corresponding to the desired parameters (30a).
characterized in that the system for minimizing the influence of unsteady flow states exhibits:
at least one arrangement (15) of flow-influencing devices (16) for influencing the fluid flow over the surface segment (10), which are functionally connected with the flight control device, and incorporated in at least one surface segment (10; 11a, 12a; 11b, 12b) of a trailing edge flap of each wing (M; 1a, 1b) extending in a respective wingspan direction,
a detection device for detecting unsteady flow states acting on the aircraft,
an actuating function that is functionally connected with the flow-influencing devices (16) to influence the flow in the different segments of the trailing edge flap, designed in such a way that the latter, based on the unsteady flow states detected by the detection device and setting position of the control flap (S) acquired by the sensor arrangement, actuate the flow-influencing devices (16) so as to minimize the influence of unsteady flow states on the aircraft.
3. The aircraft (F) according to claim 2, characterized in that the system for minimizing the influence of unsteady flow states exhibits:
at least one arrangement (15) of flow-influencing devices (16) for influencing the fluid flow over the surface segment (10), which are functionally connected with the flight control device, and incorporated in at least one surface segment (10; 11a, 12a; 11b, 12b) of the main wing (M) of each wing (M; 1a, 1b) extending in a respective wingspan direction andor at least one control flap (S),
an actuating function that is functionally connected with the flow-influencing devices (16) to influence the flow in the different segments of a wing (1; 1a, 1b), designed in such a way that the latter, based on the unsteady flow states detected by the detection device and setting position of the control flap (S) acquired by the sensor arrangement, actuate the flow-influencing devices (16) so as to minimize the influence of unsteady free flow states on the aircraft.
4. The aircraft (F) according to one of the preceding claims, characterized in that the actuating function is functionally integrated with the flight control device, so that commands for the flow-influencing devices (16) are taken into account with respect to controlling the aircraft according to the commands for the adjustable flap.
5. The aircraft (F) according to one of the preceding claims, characterized in that at least one surface segment (10; 11a, 12a; 11b, 12b) of the main wing (M) of each wing (M; 1a, 1b) extending at least in a respective wingspan direction incorporates an arrangement (15) of flow-influencing devices (16) for influencing the fluid flow over the surface segment (10) and at least one flow state sensor arrangement (17) for measuring the flow state in the respective surface segment (10; 11a, 12a; 11b, 12b), which is functionally connected with the actuating device, wherein the actuating device for each segment determines actual values for the flow state in the respective segment from the flow state sensor arrangement (17) respectively accompanying the latter, and actuates the flow-influencing devices (16) in such a way that the desired values ascertained by the actuating device are desired for minimizing the influence of unsteady free flow states.
6. The aircraft (F) according to one of the preceding claims, characterized in that
the detection device for detecting unsteady flow states acting on the aircraft is functionally connected with the flight state sensor arrangement (40) and exhibits a filter function used to identify unsteady flow states,
the actuating function for influencing the flow in the different segments of a wing (1; 1a, 1b) is functionally connected with the detection device and designed to use the identified unsteady flow states to actuate the flow-influencing devices (16) in such a way as to influence the flow of the fluid steaming over the surface segment (10) to reduce the effects of the unsteady free flow states on the aircraft.
7. The aircraft (F) according to one of the preceding claims, characterized in that
the detection device for detecting unsteady flow states acting on the aircraft is functionally connected with the flow state sensor arrangement (17) and exhibits a filter function used to identify unsteady flow states,
the actuating function for influencing the flow in the different segments of a wing (1; 1a, 1b) is functionally connected with the detection device and designed to use the identified unsteady flow states to actuate the flow-influencing devices (16) in such a way as to influence the flow of the fluid steaming over the surface segment (10) to reduce the effects of the unsteady flow states on the aircraft.
8. The aircraft (F) according to one of the preceding claims, characterized in that
the detection device exhibits sensors for detecting loads andor displacements of turbulences acting on the aircraft,
the actuating function for influencing the flow in the different segments of a wing (1; 1a, 1b) is functionally connected with the detection device and designed to use the identified unsteady flow states to actuate the flow-influencing devices (16) in such a way as to influence the flow of the fluid flow over the surface segment (10) to reduce the effects of the unsteady flow states on the aircraft.
9. The aircraft (F) according to one of the preceding claims, characterized in that detection device is designed in such a way as to ascertain desired values for the flow state on the surface segments (10; 11a, 12a; 11b, 12b) as a function of the flight state data transferred by the flight state sensor arrangement (40) in order to set a distribution of lift over the span of the main wing (M), and use the flow state data ascertained by the respective flow state sensor arrangements (17) to find deviations, and from that to derive unsteady flow states acting on the aircraft.
10. The aircraft (F) according to one of the preceding claims, characterized in that the detection device exhibits acceleration sensors (39), which are arranged on the wing for measuring accelerations that locally arise on the wing due to unsteady flow states acting on the aircraft.
11. The aircraft according to one of the preceding claims, characterized in that the arrangement of flow-influencing devices (16) is comprised of flow passage openings situated in one segment or several segments, and of a flow-generating device (for exhaust andor aspiration purposes) situated in the wing, through which fluid is purged from the flow passage openings, so as to influence the lift coefficient locally arising at the segment.
12. The aircraft according to one of the preceding claims, characterized in that the arrangement of flow-influencing devices (16) exhibits flow passage openings arranged in a segment or several segments, and a suction device situated in the wing and flow-connected with the aspirating openings, through which fluid is aspirated from the flow passage openings to influence the lift coefficient locally arising at the segment.
13. The aircraft according to claim 11 or 12, characterized in that the flow-generating device is designed to generate a continuous volumetric flow in order to reduce the effects of unsteady flow states on the aircraft when it is activated by the actuating function.
14. The aircraft according to claim 11 or 12, characterized in that the flow-generating device is designed in such a way as to generate a pulsed volumetric flow in order to reduce the effects of unsteady flow states on the aircraft when it is activated by the actuating function.
15. The aircraft according to claim 14, characterized in that the actuating function exhibits a function that generates the frequency of the pulsed volumetric flow as a function of the values for unsteady flow states ascertained by the detection device in order to reduce the influence of unsteady flow states on the aircraft.
16. The aircraft according to claim 11 or 12, characterized in that the flow-generating device exhibits a synthetic actuator, which, in order to reduce the effects of the unsteady flow states on the aircraft, is designed to generate an aspiration and purging of a volumetric flow, which is accommodated by means of an actuator in an actuator chamber of the synthetic actuator, or ejected from the latter.
17. The aircraft according to one of the preceding claims, characterized in that the arrangement of flow-influencing devices (16) consists of loudspeaker devices situated in one segment or several segments, which when activated generate air oscillations that can influence the lift coefficient locally arising at the segment.
18. The aircraft according to one of the preceding claims, characterized in that the arrangement of flow-influencing devices (16) can consist of piezo actuators situated on the surface of the wing, which are arranged in one segment or several segments, and when activated generate air oscillations that can influence the lift coefficient locally arising at the segment.
19. The aircraft according to claim 18, characterized in that the arrangement of flow-influencing devices (16) additionally exhibits a adjustable flap and actuator for adjusting the latter, wherein the desired commands for the flow-influencing devices (16) are comprised of desired commands for the flow-generating device and desired commands for an actuator for adjusting the adjustable flap.
20. The aircraft according to one of the preceding claims, characterized in that the at least one segment consists of several segments arranged one in back of the other as viewed in the wingspan direction.