公开(公告)号：WO1986000670A1

公开(公告)日：1986-01-30

申请号：PCT/US1985001313

申请日：1985-07-10

Applicant: SUNDSTRAND CORPORATION

Inventor： SUNDSTRAND CORPORATION ,  BURANDT, Wesley, A.

IPC: F04B17/06

CPC classification number: F04B1/324 ,  F04B49/002

Abstract: A hydraulic presssure intensifier for boosting normal system pressure in a hydraulic system to a higher level in order to increase the force provided by a pressure-operated actuator. The hydraulic pressure intensifier has a motor-pump unit (10) with a rotatable cylinder block (62) with cyclinders defining piston chambers and each having a movable piston (68) therein. A wobbler (70) controls the stroke of the pistons and the motor-pump unit functions as both a pump and a motor by means of porting to said cylinders including a supply pressure port (76), an intensified pressure port (77) and a return pressure port (78). The motor-pump unit has normal maximum and minimum speed limits and when operating at different flow rates the speed thereof varies accordingly. In order to maintain the speed of the motor-pump unit within normal limits, the wobbler is adjustable to vary the stroke of the pistons and thereby vary the speed of rotation of the cylinder block for the same rate of fluid flow. The wobbler can be infinitely variable between limit positions or only between limit positions and the adjustment can be made automatically in response to a speed-responsive flyweight governor-controlled valve structure (88).

公开(公告)号：WO1986000968A1

公开(公告)日：1986-02-13

申请号：PCT/US1985001389

申请日：1985-07-19

Applicant: SUNDSTRAND CORPORATION

Inventor： SUNDSTRAND CORPORATION ,  BURANDT, Wesley, A.

IPC: F16H57/10

CPC classification number: B64C13/34 ,  F16H1/46 ,  F16H2001/2881

Abstract: A multiple-stage geared rotary actuator having a plurality of balanced compound differentials providing a multiple-stage output and for converting a high-speed, low-torque input to a low-speed, high torque output for moving a member, such as an aircraft flight control surface (44). The balanced compound planetary differentials each have a plurality of tubular planet gear shafts (64, 77, 92) with a center gear (62, 76, 90) and outer gears (67, 68, 78, 79, 94, 96) at opposite sides of the center gear and with the tubular planet gear shafts (64, 77, 92) of the planetary differentials being in axial alignment. The maximum deflection resulting from bending forces acting on the tubular planet gear shafts (64, 77, 92) is minimized by changing the boundary conditions at the ends of the tubular planet gear shafts (64, 77, 92). This change in the boundary conditions is achieved by the use of structure positioned within the tubular planet gear shafts and extending through the length of the rotary gear actuator and common to all of the axially aligned tubular planet gear shafts, with one embodiment of such support structure being a bolt (225) which preloads the adjacent tubular planet gear shafts (64, 77, 92). The support of the tubular planet gear shafts enables the design of a geared rotary actuator using longer tubular planet gear shafts for increased torque-transmitting capability while keeping tubular planet gear shaft deflections within acceptable limits for optimum gear mesh.

公开(公告)号：WO1985003126A1

公开(公告)日：1985-07-18

申请号：PCT/US1984002099

申请日：1984-12-24

Applicant: SUNDSTRAND CORPORATION

Inventor： SUNDSTRAND CORPORATION ,  BURANDT, Wesley, A.

IPC: G01M13/02

CPC classification number: G01M13/02 ,  B64C13/28 ,  B64C13/34 ,  Y10S475/90

Abstract: A failure detection mechanism for a geared rotary actuator having plural output stages (26, 28, 30). Each output stage has a planetary gearing set (48, 49, 50) and the failure detection mechanism senses relative movement between planet gear shafts (54, 72, 76) of adjacent planetary gearing sets when there is normal drive through one planetary gearing set and a back-drive through the other. The failure detection mechanism includes structure (95, 96, 98, 99) operable when a failure is sensed to either prevent further drive through the geared rotary actuator, or to activate mechanism, to signal to a pilot of an aircraft for example, that the failure has occured.

公开(公告)号：EP0167593A1

公开(公告)日：1986-01-15

申请号：EP85900550.0

申请日：1984-12-24

Applicant: SUNDSTRAND CORPORATION

Inventor： BURANDT, Wesley, A.

IPC: G01L3 ,  B64C13 ,  B64D45 ,  F16H1 ,  F16H61 ,  F16H63 ,  G01M13

CPC classification number: G01M13/02 ,  B64C13/28 ,  B64C13/34 ,  Y10S475/90

Abstract: Mécanisme de détection de défaillances pour un dispositif d'actionnement rotatif à engrenages, possédant une pluralité d'étages de sortie (26, 28, 30). Chaque étage de sortie possède un ensemble d'engrenages planétaires (48, 49, 50) et le mécanisme de détection de défaillances détecte le mouvement relatif entre les arbres des engrenages planétaires (54, 72, 76) d'ensembles adjacents d'engrenages planétaires lorsqu'il y a un entraînement normal par un ensemble d'engrenages planétaires et une marche arrière par l'autre ensemble. Le mécanisme de détection de défaillances comprend une structure (95, 96, 98, 99) pouvant être actionnée lors de la détection d'une défaillance, soit pour empêcher un entraînement ultérieur par le dispositif rotatif à engrenages, soit pour actionner un mécanisme, signalant par exemple au pilote d'un aéronef qu'une défaillance s'est produite.