A hydrostatic automatic flight servo system is provided. The automatic flight servo system includes a manifold that defines a first fluid chamber, and a hydraulic fluid is received in the first fluid chamber. The first fluid chamber includes a first bellows and a second bellows. The automatic flight
A hydrostatic automatic flight servo system is provided. The automatic flight servo system includes a manifold that defines a first fluid chamber, and a hydraulic fluid is received in the first fluid chamber. The first fluid chamber includes a first bellows and a second bellows. The automatic flight servo system includes a stick received at least partially within the manifold and pivotally coupled to the manifold. The stick includes a control arm fixedly coupled to the first bellows, and the stick is to receive an input. The automatic flight servo system includes a flight output system pivotally coupled to the manifold. The flight output system includes a second control arm received at least partially within the manifold and coupled to the second bellows such that the pivotal movement of the stick pivots the flight output system relative to the manifold.
대표청구항▼
1. A hydrostatic automatic flight servo system comprising: a manifold that defines a first fluid chamber and a second fluid chamber that is fluidly isolated from the first fluid chamber, with a hydraulic fluid received in the first fluid chamber and the second fluid chamber, the first fluid chamber
1. A hydrostatic automatic flight servo system comprising: a manifold that defines a first fluid chamber and a second fluid chamber that is fluidly isolated from the first fluid chamber, with a hydraulic fluid received in the first fluid chamber and the second fluid chamber, the first fluid chamber including a first bellows and a second bellows, and the second fluid chamber includes a third bellows and a fourth bellows;a stick received at least partially within the manifold and pivotally coupled to the manifold, the stick including a control arm fixedly coupled to the first bellows, the stick adapted to receive an input; anda flight output system pivotally coupled to the manifold, the flight output system including: a second control arm received at least partially within the manifold and coupled to the second bellows such that the pivotal movement of the stick pivots the flight output system relative to the manifold; andan output linkage coupled to the second control arm, the output linkage pivotally coupled to the manifold, the output linkage having a first linkage end adapted to be coupled to a flight surface,wherein the first fluid chamber further comprises a fifth bellows and a sixth bellows, and the fifth bellows and the sixth bellows are each movable along an axis that is substantially traverse to a longitudinal axis of the manifold. 2. The hydrostatic automatic flight servo system of claim 1, wherein the stick includes a third control arm and the output linkage includes a fourth control arm, and the third control arm is coupled to the third bellows and the fourth control arm is coupled to the fourth bellows. 3. The hydrostatic automatic flight servo system of claim 1, further comprising a first stability augmentation actuator having a first stability output shaft coupled to the fifth bellows and a second stability augmentation actuator having a second stability output shaft coupled to the sixth bellows, the first stability augmentation actuator moves the first stability output shaft to move the fifth bellows relative to the first fluid chamber to pivot the output linkage relative to the manifold, and the second stability augmentation actuator moves the second stability output shaft to move the sixth bellows relative to the first fluid chamber to pivot the output linkage relative to the manifold. 4. The hydrostatic automatic flight servo system of claim 3, wherein the second fluid chamber further comprises a seventh bellows and an eighth bellows, and the seventh bellows and the eighth bellows are each movable along an axis that is substantially traverse to the longitudinal axis of the manifold. 5. The hydrostatic automatic flight servo system of claim 4, wherein the first stability output shaft is coupled to the seventh bellows and the second stability output shaft is coupled to the eighth bellows such that the movement of the first stability output shaft moves the seventh bellows relative to the second fluid chamber to pivot the output linkage relative to the manifold and the movement of the second stability output shaft moves the eighth bellows relative to the second fluid chamber to pivot the output linkage relative to the manifold. 6. The hydrostatic automatic flight servo system of claim 1, wherein the manifold defines a third fluid chamber that contains the hydraulic fluid, the third fluid chamber fluidly isolated from the first fluid chamber and the third fluid chamber includes a ninth bellows and a tenth bellows. 7. The hydrostatic automatic flight servo system of claim 6, wherein the first control arm of the stick is fixedly coupled to the ninth bellows. 8. The hydrostatic automatic flight servo system of claim 7, further comprising an actuator having an output shaft, the output shaft fixedly coupled to the tenth bellows such that movement of the output shaft pivots the stick. 9. The hydrostatic automatic flight servo system of claim 8, wherein the manifold defines a fourth fluid chamber that contains the hydraulic fluid, the fourth fluid chamber fluidly isolated from the first fluid chamber and the third fluid chamber, the fourth fluid chamber including an eleventh bellows and a twelfth bellows, with the output shaft of the actuator fixedly coupled to the eleventh bellows. 10. The hydrostatic automatic flight servo system of claim 9, wherein the stick includes a third control arm, and the third control arm is fixedly coupled to the twelfth bellows. 11. The hydrostatic automatic flight servo system of claim 8, wherein the output shaft includes a first end and a second end, the first end fixedly coupled to the tenth bellows and including a stop, and the hydrostatic automatic flight servo system further comprises a spring housing coupled about the stop, with a spring disposed within the spring housing. 12. A hydrostatic automatic flight servo system comprising: a manifold that defines a first fluid chamber, with a hydraulic fluid received in the first fluid chamber, the first fluid chamber including a first bellows and a second bellows;a stick received at least partially within the manifold and pivotally coupled to the manifold, the stick including a control arm fixedly coupled to the first bellows, the stick adapted to receive an input; anda flight output system pivotally coupled to the manifold, the flight output system including a second control arm received at least partially within the manifold and coupled to the second bellows such that the pivotal movement of the stick pivots the flight output system relative to the manifold,wherein the first fluid chamber further defines a first fluid subchamber and a second fluid subchamber, the first fluid subchamber fluidly coupled to the first fluid chamber via a first valve and the second fluid subchamber fluidly coupled to the first fluid chamber via a second valve. 13. A hydrostatic automatic flight servo system comprising: a manifold that defines a first fluid chamber, a second fluid chamber and a third fluid chamber, with a hydraulic fluid received in each of the first fluid chamber, the second fluid chamber and the third fluid chamber, the first fluid chamber fluidly isolated from the second fluid chamber and the third fluid chamber fluidly isolated from the first fluid chamber and the second fluid chamber, the first fluid chamber including a first bellows and a second bellows, the second fluid chamber including a third bellows and a fourth bellows, and the third fluid chamber including a fifth bellows and a sixth bellows;a stick received at least partially within the manifold and pivotally coupled to the manifold, the stick including a first control arm fixedly coupled to the first bellows and the fifth bellows, and a second control arm fixedly coupled to the third bellows, the first control arm spaced apart from the second control arm;an output linkage pivotally coupled to the manifold, the output linkage including a third control arm spaced apart from a fourth control arm, each of the third control arm and the fourth control arm received at least partially within the manifold, the third control arm fixedly coupled to the second bellows and the fourth control arm fixedly coupled to the fourth bellows such that the pivotal movement of the stick pivots the output linkage relative to the manifold; andan actuator having an output shaft, the output shaft fixedly coupled to the sixth bellows such that movement of the output shaft pivots the stick. 14. The hydrostatic automatic flight servo system of claim 13, wherein the manifold defines a fourth fluid chamber that contains the hydraulic fluid, the fourth fluid chamber fluidly isolated from the first fluid chamber, the second fluid chamber and the third fluid chamber, the fourth fluid chamber including a seventh bellows and an eighth bellows, with the output shaft of the actuator fixedly coupled to the seventh bellows and the second control arm of the stick is fixedly coupled to the eighth bellows.
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이 특허에 인용된 특허 (5)
Hanlon, Casey; Wilkens, Dean R.; Bandera, Pablo; Davis, Toren S., Aircraft flight control user interface linkage system.
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