Actuator apparatus, in particular for an aircraft flight control
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-013/04
출원번호
US-0860941
(2001-05-18)
우선권정보
FR-0006550 (2000-05-22)
발명자
/ 주소
Rodrigues, Fernand
출원인 / 주소
TRW Systemes Aeronautiques Civils
대리인 / 주소
Blakely Sokoloff Taylor & Zafman
인용정보
피인용 횟수 :
3인용 특허 :
11
초록▼
Actuator apparatus, in particular for an airplane flight control. The apparatus has at least two main drive systems and a differential which connects outlet shafts from the two systems to a control shaft connected to an element to be actuated and also including a mechanism for locking each outlet sh
Actuator apparatus, in particular for an airplane flight control. The apparatus has at least two main drive systems and a differential which connects outlet shafts from the two systems to a control shaft connected to an element to be actuated and also including a mechanism for locking each outlet shaft of the drive systems when the system for driving it is no longer operating. The apparatus also includes at least one auxiliary drive motor and a clutch mechanism mounted on the outlet shaft of one of the main systems and suitable for automatically driving the outlet shaft using the auxiliary motor when the corresponding main drive system is not operating and for automatically locking the outlet shaft when the main drive system and the auxiliary motor are not operating.
대표청구항▼
Actuator apparatus, in particular for an airplane flight control. The apparatus has at least two main drive systems and a differential which connects outlet shafts from the two systems to a control shaft connected to an element to be actuated and also including a mechanism for locking each outlet sh
Actuator apparatus, in particular for an airplane flight control. The apparatus has at least two main drive systems and a differential which connects outlet shafts from the two systems to a control shaft connected to an element to be actuated and also including a mechanism for locking each outlet shaft of the drive systems when the system for driving it is no longer operating. The apparatus also includes at least one auxiliary drive motor and a clutch mechanism mounted on the outlet shaft of one of the main systems and suitable for automatically driving the outlet shaft using the auxiliary motor when the corresponding main drive system is not operating and for automatically locking the outlet shaft when the main drive system and the auxiliary motor are not operating. spherical dome shape; a plurality of fin lots defined in the base structure; a plurality of insert structures fitting into corresponding ones of the fin slots; a plurality of deployable fins mounted to the base structure and supported within the insert structures for movement between a stowed position and a deployed position. 2. The base of claim 1, wherein the base structure is a unitary, one-piece structure. 3. The base of claim 1, wherein the base structure is fabricated of titanium or a titanium alloy. 4. The base of claim 1, wherein the base structure includes an aft end having a plurality of cavities formed therein, the cavities separated by a set of corresponding radial ribs extending outwardly to a base outer surface. 5. The base of claim 1, wherein the base structure includes an aft end having a plurality of cavities formed therein, the cavities separated by a set of corresponding radial ribs, the radial ribs being joined together at said forward end to form said forward bulkhead. 6. The base of claim 5, wherein adjacent ribs are joined together at said forward end to form a conical structure. 7. The base of claim 5 wherein said forward bulkhead is adapted to carry a majority of loading experienced by the base structure during acceleration events. 8. The base of claim 5, wherein a soft material is disposed in said plurality of cavities. 9. The base of claim 1, further including a circumferential groove formed in a forward portion of the base structure for receiving therein an obturator structure. 10. A tactical base for a projectile, comprising: a base structure; a plurality of fin slots defined in the base structure; a plurality of insert structures fitting into corresponding ones of the fin slots a plurality of deployable fins mounted to the base structure and supported within the insert structures for movement between a stowed position and a deployed position, an adapter structure for securing the base structure to a forward section of the projectile, and wherein the base structure has a threaded portion at a forward end, and wherein said adapter structure threading engages with said threaded portion. 11. A tactical base for a projectile, comprising: a base structure; a plurality of fin slot defined in the base structure; a plurality of insert structures fitting into corresponding ones of the fin slots; a plurality of deployable fins mounted to the base structure and supported within the insert structures for movement between a stowed position and a deployed position, wherein the base structure has defined therein a plurality of cavities each of which are open at an aft base wall, and a plurality of radially extending walls defining said cavities and said fin slots, and wherein during firing of the projectile from a gun barrel, gasses at high pressure generated from a propellant enter said cavities and tend to deflect said walls into compression with said inserts and said fins, to prevent premature fin deployment before the projectile has left the gun barrel. 12. A base for a projectile, comprising: a base structure having a forward bulkhead in a hemispherical dome shape; a plurality of fin slots defined in the base structure; a plurality of deployable fins mounted to the base structure and supported within the fin slots for movement between a stowed position and a deployed position. 13. The base of claim 12, further comprising an adapter structure for securing the base structure to a forward section of the projectile. 14. The base of claim 12, wherein each of the fins are pivotally mounted in said slots for pivoting movement about a pivot point from said stowed position to said deployed position. 15. The base of claim 14, wherein the pivot point for each of the fins is disposed adjacent said aft end, and wherein each of the fins in said stowed position are pivoted forwardly about the pivot point. 16. The base of claim 14, wherein the fins have a center of gravity disposed inwardly of s
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이 특허에 인용된 특허 (11)
Townsend Richard E. (Huntington NY), Aircraft control system with a jam isolating coupling.
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