Aircraft attitude control configuration
An aircraft attitude control configuration enables control surfaces to provide attitude control for an aircraft at hover or low air speed conditions. The aircraft attitude control configuration includes a plurality of thrusters mounted to an aircraft for thrusting air, a first control surface kinematically coupled to the aircraft at a position downstream of a first thruster to enable a first vector force to be generated by a portion of the thrusted air from the first thruster on the first control surface, and a second control surface kinematically coupled to the aircraft at a position downstream of a second thruster, the first and the second control surfaces being displaced symmetrically on opposite sides of a longitudinal axis of the aircraft, the second control surface being configured to be independently and differentially movable with respect to the first control surface to enable a second vector force to be generated by a portion of the thrusted air from the second thruster on the second control surface.
1. An aircraft attitude control configuration comprising:
a plurality of thrusters mounted to an aircraft for thrusting air;
a first control surface kinematically coupled to the aircraft at a position downstream of a first thruster to enable a first vector force to be generated by a portion of the thrusted air from the first thruster on the first control surface; and
a second control surface kinematically coupled to the aircraft at a position downstream of a second thruster, the first and the second control surfaces being displaced symmetrically on opposite sides of a longitudinal axis of the aircraft, the second control surface being configured to be independently and differentially movable with respect to the first control surface to enable a second vector force to be generated by a portion of the thrusted air from the second thruster on the second control surface.
2. The aircraft attitude control configuration of claim 1 further comprising:
a third control surface kinematically coupled to the aircraft, the third control surface and a portion of the thrusted air from a third thruster in the plurality of thrusters generates a third vector force on the third control surface.
3. The aircraft flight control configuration of claim 2 wherein the first control surface, the second control surface, and the third control surface are independently operable with respect to one another.
4. The aircraft flight control configuration of claim 1 further comprising:
a first stabilizer mounted on the aircraft; and
the first and the second control surfaces are kinematically coupled to the stabilizer at positions on the first stabilizer that are displaced symmetrically on opposite sides of the longitudinal axis of the aircraft.
5. The aircraft attitude control configuration of claim 4 further comprising:
a second stabilizer mounted on the aircraft; and
a third control surface kinematically coupled to the second stabilizer and being configured to be independently and differentially movable with respect to the first and the second control surfaces to enable a portion of the thrusted air from one of the thrusters in the plurality of thrusters to generate a third vector force on the third control surface.
6. The aircraft attitude control configuration of claim 5 wherein the third control surface is a rudder.
7. The aircraft attitude control configuration of claim 5 wherein the first control surface is a first elevator kinematically coupled to the first stabilizer and the second control surface is a second elevator kinematically coupled to the second stabilizer.
8. The aircraft attitude control configuration of claim 1 wherein the first control surface is a first stabilator and the second control surface is a second stabilator.
9. The aircraft attitude control configuration of claim 8 further comprising:
a third control surface kinematically coupled to the aircraft and being configured to be independently and differentially movable with respect to the first and the second stabilators to enable another portion of thrusted air from one of the thrusters in the plurality of thrusters to generate a vector force on the third control surface.
10. The aircraft attitude control configuration of claim 9 wherein the third control surface is a third stabilator.
11. An aircraft attitude control configuration comprising:
a plurality of thrusters mounted to an aircraft for thrusting air;
a first control surface; and
a second control surface, the first and the second control surfaces being kinematically coupled to the aircraft at a position downstream of the thruster and displaced symmetrically on opposite sides of a longitudinal axis, the first and the second control surfaces being configured to be independently and differentially movable with respect to one another to enable a portion of the thrusted air from the plurality of thrusters to generate a first vector force on the first control surface and another portion of the thrusted air from the plurality of thrusters to generate a second vector force on the second control surface.
12. The aircraft attitude control configuration of claim 11 further comprising:
a first tail boom;
a second tail boom;
a stabilizer mounted to the first and the second tail booms; and
the first and the second control surfaces being kinematically coupled to the stabilizer between the first and the second tail booms to the aircraft and being configured to be independently and differentially movable with respect to one another to enable a portion of the thrusted air from the plurality of thrusters to generate a first vector force on the first control surface and another portion of the thrusted air from the plurality of thrusters to generate a second vector force on the second control surface.
13. The aircraft attitude control configuration of claim 11 further comprising:
a movement encoder coupled to one of the first and the second control surfaces to generate data corresponding to a degree of rotation for the control surface coupled to the movement encoder.
14. The aircraft attitude control configuration of claim 13 wherein the movement encoder is a rotary encoder.
15. The aircraft attitude control configuration of claim 13 wherein the movement encoder is a displacement encoder.
16. The aircraft attitude control configuration of claim 11 further comprising:
a first stabilizer having a first and a second end, the stabilizer being mounted to the aircraft with the first and the second ends being on opposite sides of the longitudinal axis to form a horizontal stabilizer; and
the first and the second control surfaces being kinematically coupled to the horizontal stabilizer at positions that are displaced symmetrically on opposite sides of the longitudinal axis.
17. The aircraft attitude control configuration of claim 16 further comprising:
a vertical stabilizer mounted on the aircraft; and
a third control surface kinematically coupled to the vertical stabilizer and being configured to be independently and differentially movable with respect to the first and the second control surfaces coupled to the horizontal stabilizer to enable another portion of the thrusted air to generate a third vector force on the third control surface.
18. The aircraft attitude control configuration of claim 17 wherein the third control surface is a rudder.
19. The aircraft attitude control configuration of claim 11 further comprising:
a first stabilizer mounted to the aircraft;
a second stabilizer mounted to the aircraft; and
wherein the first control surface is a first elevator kinematically coupled to the first stabilizer and the second control surface is a second elevator kinematically coupled to the second stabilizer.
20. The aircraft attitude control configuration of claim 11 wherein the first control surface is a first stabilator and the second control surface is a second stabilator and both stabilators are kinematically coupled to the aircraft and configured for independent movement.