1. A method for causing a computer to render ink using a dynamic rendering object as attached to a component, said dynamic rendering object having an interface, and said component having an input interface, a synchronous interface, and an asynchronous interface, said method comprising:
receiving ink from said component that orders how data is handled, said ink being received over said dynamic rendering object’s interface which is attached to said synchronous interface on the component;
rendering said ink for subsequent display on a display device wherein said rendering occurs in synchronization with the computer receiving said ink;
temporarily caching said rendered ink transmitting said ink from said dynamic rendering object;
receiving a notification from another rendering object, said another rendering object being connected to said asynchronous interface of said component said notification indicating to said dynamic rendering object that said another rendering object has received information relating to said ink from said component; and
clearing said cache of said rendered ink in response to said notification.
2. The method of according to claim 1, wherein said rendering step provides a user with the appearance of uninterrupted ink flowing from a stylus.
3. The method of according to claim 1, wherein said dynamic rendering object is part of a synchronous plug-in collection attached to said component.
4. The method of according to claim 1, further comprising the step of:
passing data to an additional object connected to said rendering object.
5. A computer-readable medium having a program stored thereon, said program for rendering ink using a dynamic rendering object as attached to a component, said dynamic rendering object having an interface, and said component having an input interface, a synchronous interface, and an asynchronous interface, said program comprising the steps of:
receiving ink from said component that orders how data is handled, said ink being received over said dynamic rendering object’s interface which is attached to said synchronous interface on the component;
rendering said ink for subsequent display on a display device said rendering occurring in synchronization with receipt of said ink;
temporarily caching said rendered ink; transmitting said ink from said dynamic rendering object;
receiving a notification from another rendering object, said another rendering object being connected to said asynchronous interface of said component said notification indicating to said dynamic rendering object that said another rendering object has received information relating to said ink from said component; and
clearing said cache of said rendered ink in response to said notification.
6. The computer-readable medium of claim 5, wherein said rendering step provides a user with the appearance of uninterrupted ink flowing from a stylus.
7. The computer-readable medium of claim 5, wherein said dynamic rendering object is part of a synchronous plug-in collection attached to said component.
8. The computer-readable medium of claim 5, said program further comprising the step of:
passing data to an additional object connected to said dynamic rendering object.
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 characterized by a flight envelope, comprising:
a laterally extending wing;
a plurality of pitch-control devices, each pitch-control device being mounted at a separate lateral location along the wing, and each pitch-control device being configured to apply pitch-control torque at its lateral location, wherein the wing is characterized by a torsional flexibility adapted to allow the plurality of pitch control devices to control localized pitch at their lateral wing locations to a degree substantial enough to be significant for flight control; and
a control system configured to control the plurality of pitch-control devices based upon the relative localized pitches at the plurality of lateral locations.
2. The aircraft of claim 1, wherein each pitch-control device is adapted to cause a control surface pitch effect and a control surface flap effect, and wherein each pitch-control device includes a boom connecting the wing to a control surface aft of the trailing edge of the wing at a distance adequate to cause the control surface pitch effect to dominate the control surface flap effect.
3. The aircraft of claim 1, wherein the control system is configured to operate the pitch-control devices under a protocol adapted to control and alter wing dihedral based upon the dihedral of the wing.
4. The aircraft of claim 3, wherein the protocol actively provides for dihedral control and alteration that maintains the wing bending stresses within safety limits.
5. The aircraft of claim 1, and further comprising a plurality of motors, wherein the control system is configured to separably control the thrust from the plurality of motors based upon fore-and-aft wing loads between the motors.
6. The aircraft of claim 1, wherein the pitch-control devices include both fixed and controllable horizontal surfaces.
7. The aircraft of claim 4, wherein the protocol is configured to direct outboard pitch-control devices with more downward pitching pitch-control torques than pitch-control torques of inboard pitch-control devices.
8. The aircraft of claim 1, wherein the aircraft is controlled without the use of elevators.
9. An aircraft characterized by a flight envelope, comprising:
a laterally extending wing;
a means for separately actuating the pitch of the wing at a plurality of lateral locations along the wing, wherein the wing is characterized by a torsional flexibility adapted to allow the means for separately actuating to actuate localized pitch at the plurality of lateral locations to a degree substantial enough to be significant for flight control; and
a means for controlling the means for separately actuating based upon the relative localized pitches at the plurality of lateral locations.
10. A method of controlling an aircraft characterized by a flight envelope, comprising:
separately actuating the pitch of a laterally extending wing at a plurality of lateral locations along the wing, wherein the wing is characterized by a torsional flexibility adapted to allow the means for separately actuating to actuate localized pitch at the plurality of lateral locations to a degree substantial enough to be significant for flight control; and
controlling the means for separately actuating based upon the relative localized pitches at the plurality of lateral locations.
11. The method of claim 10, wherein the step of controlling includes directing the pitch-control devices under a protocol configured to control and alter wing dihedral based upon the dihedral of the wing.