Search Images Maps Play YouTube News Gmail Drive More »
Sign in
Screen reader users: click this link for accessible mode. Accessible mode has the same essential features but works better with your reader.


  1. Advanced Patent Search
Publication numberUS2099368 A
Publication typeGrant
Publication dateNov 16, 1937
Filing dateFeb 13, 1936
Priority dateApr 5, 1935
Publication numberUS 2099368 A, US 2099368A, US-A-2099368, US2099368 A, US2099368A
InventorsLevy Rene Lucien
Original AssigneeSiam
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Device for the automatic control of camber flaps and the like for airplanes
US 2099368 A
Abstract  available in
Previous page
Next page
Claims  available in
Description  (OCR text may contain errors)

Nov. 16, 1937.


CONTROL OF CAMBER FLAPS AND THE LIKE FOR AIRPLANES Filed Feb. 13, 1936 40 Serial No. 15,908, for

Patented Nov. 16, 1937.

UNITED STATES PATENT OFFICE I 2,099,368 DEVICE FOR THE AUTOMATIC CONTROL OF CAMBER FLAPS AND THE LIKE PLANES FOR Am Ren Lucien Levy, Montrouge, France, assignor to Socit dlnventions Aeronautiques et Mecaniques S. I. A. M., Fribourg, (Suisse) Application In France 1 Claim.

2. The hinge moment 'resulting from the reaction of air on the flap is rigorously limited to a 1.5 definite value, so that any increase of this stress (which might result either from an increase of speed of the airplane, or from a gust of wind) immediatelycauses retraction of the flap, the

duration of this retraction being moreover auto- 20 maticaliy limited to that of the cause which determined it.

The pilot can thus set the flaps-in action whatever may be the speed of the airplane. The flaps will leave the neutral position only when the I speed of the airplane will be lower than or equal to a definite value, and, moreover, their position will, at every instant, be the resultant of the stress of the reaction of air with the permanent stress to which they are subjected owing to the 30 device;

Likewise, when the pilot desires the airplane to fly off, the flaps are, when the airplane is stationary, set to the maximum of their displacement; inproportio-n as the airplane takes up 35 speed by rolling, the flaps are gradually retracted for assuming the position most favourable for flying off. t

Bythe device described in the United States patent application filed on April 11, 1935, under System for controlling the evolutions of a movable object in a fluid, in the name of the applicant, results of the same nature can be obtained by sending in the cylinder, designated by reference number 23 in Fig. 4 of this 45 patent application, air under a definite pressure by means of a distributor allowing at will, either to admit air under this pressure or to allow it to escape for retracting the flaps.

However, this arrangement has an incon- 5o venience in that it requires the presence of a source of compressed air on board, and, consequently, in that it does not allow utilization of the flaps when there is a failure in the supply of compressed air. I

The device according to the present invention is free of these inconveniences, as it is characterized by the fact that the energy necessary for causing downward movement of a flap has been February 13, 1936, Serial No. 63,805

April 5, 1935 stored during the preceding retractionof this flap, so that the setting in action of the latter for downward movement is independent of any source of energy external to the device.

The invention is diagrammatically illustrated in the accompanying drawing: I

.The flap l (operative position)l (retracted position) -pivoted at 2 at a suitable point of the wing A, is controlled by the rod 3 of a piston 4 movable in a hydraulic cylinder 5, which communicates, through a conduit 6, with a hydropneumatic accumulator I, known per se. It is to be noted that this accumulator encloses a piston 8 surmounted by a cushion of compressed air 9, whilst the lowerchamber ll! of the accumulator, underneath the piston, is filled with liquid, the latter also filling up the cylinder 5.

Through a conduit-4|, this cylinder is connected, at the rear of piston 4, with a pump I2 sucking the liquid from a tank l3 through a conduit M. A valve l5, interposed in a pipe I6,

allows, when it is opened, of putting the conduit l l directly in communication with the tank l3.

In its set or operative position, the flap l -is held by the pressure existing in the accumulator 1, the valve l5 being open. The pressure in the accumulator I is determined in such a manner that the flap I automatically retracts when the speed. of the airplane reaches a definite value.

For retracting the flap, the pilot closes the valve [5 and sets the pump l2 in action. The liquid delivered by the latter into conduit ll pushes back piston 4:- the flap retracts and, at the same time, the pressure increases in accumulator I. The energy thus supplied to the accumulator during the retracting operation of the flap will be used during the next downward movement of the flap since at this moment, owing to the fact that the valve I5 is opened, it is the accumulator which will supply the energy necessary for this downward movement.

What I claim as my invention and desire to secure by Letters Patent is:

A device for the control of an airplane camber fiap, or the like, comprising: a hydraulic cylinder, a piston movable in said cylinder, a hydro-pneumatic accumulator, a pipe line connecting this cylinder with said tank on one side of said piston, a liquid tank connected to said cylinder on the other side of the piston, a valve interposed in the pipe "line connecting the cylinder to the tank, a source ofhydraulicpressure allowing to move said piston in the direction corresponding to the increase of the pressure in said accumulator, and means for connecting said piston to the camber flap for actuating the latter in one direction and in the other.


Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2439183 *Mar 20, 1944Apr 6, 1948Page Herbert EHydraulic jack
US2476378 *Mar 12, 1945Jul 19, 1949Warner Aircraft CorpValve assembly
US2627249 *May 31, 1947Feb 3, 1953M & J Engineering CoFluid pressure operated positioning apparatus for motor valves
US2932951 *Mar 8, 1957Apr 19, 1960Gen Dynamics CorpForming apparatus
US3213176 *Mar 5, 1963Oct 19, 1965Elektrokemisk AsElectrode suspension mechanism and method of operating same
US3464315 *Jun 12, 1967Sep 2, 1969Chambersburg Eng CoMechanical pneumatic servo control system for high-speed impact devices
US3563346 *Feb 3, 1969Feb 16, 1971Automotive Prod Co LtdExtensible and contractable devices
US3667621 *Oct 20, 1970Jun 6, 1972Wisconsin Foundry And MachineFluid power system for a self-contained unloading unit
US3762278 *Oct 29, 1971Oct 2, 1973Komnatny IPulse piston drive
US3823758 *Dec 3, 1970Jul 16, 1974Allen Electric Equipment CoActuator assembly
US3912227 *Oct 17, 1973Oct 14, 1975Drilling Syst IntMotion compensation and/or weight control system
US4061296 *Dec 18, 1975Dec 6, 1977Andrew Kubek, Sr.Braking system for ski or float equipped aircraft
US4135547 *May 31, 1977Jan 23, 1979Baker International CorporationQuick disengaging valve actuator
US4537221 *Apr 24, 1984Aug 27, 1985Gewerkschaft Eisenhutte WestfaliaHydraulic control devices for use with mining apparatus
US4729224 *Jul 10, 1986Mar 8, 1988Mcateer James DInstallation, apparatus and method for actuating doors, gates and the like under extreme environmental conditions
US6385969 *Sep 8, 2000May 14, 2002Hoerbiger Hydraulik GmbhArrangement for hydraulic actuation of a movable component on a vehicle
U.S. Classification91/47, 92/134, 244/203, 244/78.1, 244/226
International ClassificationB64C3/50
Cooperative ClassificationB64C3/50
European ClassificationB64C3/50