The present invention relates to landing gear (5) having at least one undercarriage (10) comprising a landing gear leg (11) carrying at least one wheel (12). The undercarriage (10) includes a retraction actuator (20) having an electric motor (23), blocking means (30) for blocking the actuator in the
The present invention relates to landing gear (5) having at least one undercarriage (10) comprising a landing gear leg (11) carrying at least one wheel (12). The undercarriage (10) includes a retraction actuator (20) having an electric motor (23), blocking means (30) for blocking the actuator in the retraction position and for enabling the retraction actuator to be positioned in the “landing gear extended” position by gravity, first monitoring means (35) for monitoring the operation of the retraction actuator (20), first control means (65) for controlling the refraction actuator (20), and second control means (75) for controlling the blocking means (30).
대표청구항▼
1. A landing gear for an aircraft capable of landing vertically, the landing gear comprising at least one undercarriage, the undercarriage comprising a landing gear leg carrying at least one wheel, wherein the undercarriage comprises: a retraction actuator connected to the landing gear leg and provi
1. A landing gear for an aircraft capable of landing vertically, the landing gear comprising at least one undercarriage, the undercarriage comprising a landing gear leg carrying at least one wheel, wherein the undercarriage comprises: a retraction actuator connected to the landing gear leg and provided with an electric motor for moving an extendable actuator rod of the retraction actuator relative to a cylinder of the retraction actuator between a landing gear retracted position and a landing gear extended position, for the purposes of extending the wheel from a wheel bay and for retracting the wheel into the wheel bay;a fail-safe brake connected to the actuator rod for preventing movement of the actuator rod relative to the cylinder during a normal mode, and for enabling the extendable rod to be positioned in the extended position by gravity during an emergency mode;a first sensor for monitoring the operation of the retraction actuator, the first sensor being connected to a display for indicating the position of the retraction actuator and for indicating one of the normal mode or malfunction mode of the fail-safe brake; anda first controller for controlling the retraction actuator, anda second controller for controlling the fail-safe brake. 2. The landing gear according to claim 1, wherein the a fail-safe brake, wherein the fail-safe brake prevents movement of the extendable actuator rod in the absence of electricity. 3. The landing gear according to claim 1, wherein the electric motor includes a stator and a rotor, the rotor being secured to a screw and co-operating with the fail-safe brake, the extendable actuator rod provided with a nut arranged on the screw, the landing gear including anti-rotation means for preventing the nut from rotating with the screw so that rotation of the screw causes the nut to move in translation, the first sensor monitoring a first end-of-stroke of the actuator rod to ensure that the actuator rod is arranged in the retracted such that the retraction actuator is in the landing gear retracted position, and a second sensor monitoring the second end-of-stroke of the actuator rod to ensure that that the actuator rod is extended such that the refraction actuator is in the landing gear extended position. 4. The landing gear according to claim 1, wherein the first sensor is external to the retraction actuator for verifying that the retraction actuator is in the landing gear extended position. 5. The landing gear according to claim 1, wherein the undercarriage comprises: single brake means including an electric actuator for braking each wheel;second sensor for detecting malfunction of the brake means, the second sensor connected to a display member for signaling a malfunction of the brake means; anda third controller for controlling the brake means. 6. The landing gear according to claim 5, including fourth controller for controlling the brake means on the ground so as to cause the brake means to exert maximum braking. 7. The landing gear according to claim 5, wherein a third control line includes a control unit interposed between the brake means and the third controller, the control unit transmitting a braking order to the brake means as a function of input orders coming from the third controller and from programmed braking logic. 8. The landing gear according to claim 7, where the control unit includes a self-test module for verifying operation of the brake means before a landing. 9. The landing gear according to claim 1, wherein the first controller is connected to the retraction actuator by a single first control line, and/or the second controller is connected to the fail-safe brake by a single second control line, and/or a third controller is connected to a brake means by a single third control line. 10. The landing gear according to claim 9, wherein the first control line includes at least one data concentrator and a bi-directional connection. 11. The landing gear according to claim 1, wherein first the controller communicates with the first sensor and the electric motor of the retraction actuator and the display. 12. The landing gear according to claim 11, wherein the first controller includes a control system operable by a person. 13. An aircraft capable of landing vertically, the aircraft comprising: landing gear having least one retractable undercarriage leg carrying at least one wheel;a retraction actuator including an extendable actuator rod for movement relative to a cylinder between a first and second actuator rod position, wherein the actuator rod is connected to the undercarriage leg for moving the undercarriage leg between a landing gear refracted position and a landing gear extended position respectively, wherein in the landing gear refracted position the wheel is retracted into an aircraft bay, and in the extend position, the wheel is extended from the aircraft bay;an electric motor connected to the actuator rod for moving actuator rod between the first and second actuator rod positions;a fail-safe brake connected to the actuator rod for preventing movement of the actuator rod relative to the cylinder during a normal mode, and for enabling the extendable rod to be positioned in the extended position by gravity during an emergency mode;a first sensor for monitoring the operation of the retraction actuator,a display in communication with the first sensor and the fail-safe brake and adapted for indicating the position of the actuator rod and for indicating one of the normal mode or malfunction mode of the fail-safe brake;a first controller for controlling the retraction actuator, anda second controller for controlling the fail-safe brake,wherein if the display indicates to an operator of the aircraft that the fail-safe brake is in the malfunction mode and the undercarriage leg is in the landing gear retracted position, the second controller is operable by the operator to extend the undercarriage leg by gravity to the landing gear extended position. 14. The aircraft according to claim 13, wherein the undercarriage comprises: single brake means including an electric actuator for braking each wheel;second sensor for detecting malfunction of the brake means, the second sensor connected to the display for signaling a malfunction of the brake means; anda third controller for controlling the brake means,wherein if the display indicates the malfunction of the brake means, the operated in directed to undertake a vertical landing procedure that does not require use of the brake means. 15. The aircraft according to claim 13, wherein the fail-safe brake prevents movement of the extendable actuator rod in the absence of electricity in the malfunction mode. 16. The aircraft according to claim 13, wherein the electric motor includes a stator and a rotor, the rotor being secured to a screw and co-operating with the fail-safe brake, the extendable actuator rod provided with a nut arranged on the screw, the landing gear including anti-rotation means for preventing the nut from rotating with the screw so that rotation of the screw causes the nut to move in translation, the first sensor monitoring a first end-of-stroke of the actuator rod to ensure that the actuator rod is arranged in the retracted such that the retraction actuator is in the landing gear retracted position, and a second sensor monitoring the second end-of-stroke of the actuator rod to ensure that that the actuator rod is extended such that the retraction actuator is in the landing gear extended position. 17. The landing gear according to claim 16, further comprising a display in communication with the first sensor and the fail-safe brake and adapted for indicating the position of the actuator rod and for indicating one of the normal mode or malfunction mode of the fail-safe brake, wherein if the display indicates to an operator of the aircraft that the fail-safe brake is in the malfunction mode and the undercarriage leg is in the landing gear retracted position, the second controller is operable by the operator to extend the undercarriage leg by gravity to the landing gear extended position. 18. The landing gear according to claim 16, wherein the fail-safe brake prevents movement of the extendable actuator rod in the absence of electricity in the malfunction mode. 19. A landing gear for an aircraft capable of landing vertically, the landing gear having at least one undercarriage leg carrying at least one wheel, wherein the landing gear comprises: a refraction actuator for moving the undercarriage leg between a landing gear refracted position and a landing gear extended position, wherein in the landing gear retracted position the wheel is retracted into an aircraft bay, and in the extend position, the wheel is extended from the aircraft bay, the retraction actuator including: a cylinder;an extendable actuator rod for movement relative to the cylinder between first and second actuator rod positions corresponding to the landing gear retracted position and the landing gear extended position respectively;a nut arranged on a screw extending from the actuator rod; andan anti-rotation device for preventing the nut from rotating with the screw so that rotation of the screw causes the nut to move in translation;an electric motor connected the screw for moving the actuator rod between the first and second actuator rod positions;a fail-safe brake connected to the actuator rod for preventing movement of the actuator rod relative to the cylinder during a normal mode, and for enabling the extendable rod to be positioned in the extended position by gravity during an emergency mode;a first sensor for monitoring the first end-of-stroke of the actuator rod to ensure that the actuator rod is arranged in the retracted position and thereby that the undercarriage leg is in the landing gear retracted position;a second sensor monitoring the second end-of-stroke of the actuator rod to ensure that that the actuator rod is the extended position and thereby that the undercarriage leg is in the landing gear extended position;a first controller for controlling the retraction actuator, anda second controller for controlling the fail-safe brake,wherein the electric motor includes a stator and a rotor, the rotor being secured to a screw and co-operating with the fail-safe brake.
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이 특허에 인용된 특허 (5)
Hadley, Kevin Richard; Timms, Mark David, Actuator.
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