US2342548A - Airplane stabilizer - Google Patents

Description

Patented Feb. 22, 1944 UNITED STATES PATENT OFFICE AIRPLANE STABILIZER Armand Lavoie, Donnacona, Quebec, Canada Application June 30, 1941, Serial No. 400,401

4 Claims.

The present invention pertains to a novel airplane stabilizer or device for preventing undesired nose diving. The principal object of the invention is to provide a device which automatically levels the plane when it commences to go into a nose dive.

This object is accomplished by a weighted means that moves axially in the plane to give the ailerons and elevators a compensating adjustment. While various suspended weights are employed for stabilizing operations, I am not aware of an axially movable Weight for this purpose. One advantage of a weight so mounted is that it gives proper balance to the plane while climbing, as will presently be described.

Preferably two weighted members are provided in the fuselage and are linked respectively to the ailerons and elevators. When the plane dives, the weighted members shift forward by gravity and set the ailerons and elevators for climbing, whereby the level of the plane is restored.

The connections to the ailerons, however, have a separable portion whereby the connections are rendered inoperative as the weighted members move rearwardly in climbing. Thus, they present no resistance to the desired adjustment of the ailerons for climbing.

When a nose dive is intended, the appropriate movement of the control stick operates brakes acting on the weighted members to hold the latter from operating the ailerons. Thus, the latter are under the complete manual control of the pilot from the control stick during an intended diving operation.

The invention is fully disclosed by way of example in the following description and in the accompanying drawing in which:

Figure 1 is a side elevation of an airplane equipped according to the invention;

Figure 2 is a longitudinal section of the stabilizer;

Figure 3 is a section on the line 3 3 of Figure 2;

Figure 4 is a detail longitudinal section showing the weighted member locked;

Figure 5 is a detail longitudinal section, and

Figure 6 is a plan view of an airplane equipped according to the invention.

Reference to these views will now be made by use of like characters which are employed to designate corresponding parts throughout.

In Figure 1 is illustrated an airplane of conventional design and comprising a fuselage I with ailerons 2 extending therefrom in the usual manner. For each aileron, the fuselage carries an elongated box-like guide member 3 having a weight mounted to slide therein axially of the plane. The weight may be of any suitable construction adapted to slide by gravity but is preferably in the form of a vessel 4 having rollers 5 on all four sides and engaging the inner walls of the member 3. substance 6 such as mercury.

To the forward end of the vessel 4 is hinged a rod 'I terminating at its forward end in a disk 8 received in a coupling tube 9, as shown in Figure 5. Each aileron 2 is mounted on a journalled shaft Ill from which extends a lever II. The latter is pivoted to a rod I2 also extending into the coupling tube 9 and there provided with a disk I3 abutting the disk 8.

At the rear end of the fuselage are the usual stabilizer wings I4 to which are articulated the elevators I5. A link I6 extends rearwardly from each vessel 4 and is operatively connected to the corresponding elevator.

In the operation of the device, when the plane commences to nose dive, the weighted vessels 4 roll forwardly and adjust the ailerons 2 through the linkage 'I--I2 to level the plane. Also, the elevators I5 are adjusted through their links I5 for the same purpose.

On the other hand, when the plane is climbing, the weighted vessels roll rearward and become disengaged from the rods I2 so that the normal controls for the ailerons are free. At the same time, the weighted vessels in their rearward position balance the plane more correctly for climbing. When the plane has recovered from the dive the weighted mass does not immediately restore the controls to neutral. The restoration occurs after the interval required for piston 8 to engage the rear end of cylinder 9 and for the cylinder to be pulled against piston I3. The interval allows for a period of climbing before the automatic action sets in. The manual controls may of course also be used.

A pair of flexible metal brake strips I'I are placed in each member 3 beneath the rolling weight therein, as illustrated in Figure 3. From the control stick I8, wires I9 are extended rearwardly, passing over pulleys 20 on the members 3 and attached to the forward ends of the strips Il'. When the pilot wishes the plane to dive, he moves the stick I8 forward in the usual manner for this operation, and the strips are thereby drawn upward, as shown in Figure 4, to arrest the leveling action of the weighted members. Although a specific embodiment of the invention The Vessel 4 contains a heavy has been illustrated and described, it will be understood that various alterations in the details of construction may be made without departing from the scope of the invention as indicated by the appended claims.

What I claim is:

1. In an airplane having a fuselage and ailerons, Weighted means slidable axially in said fuselage, an aileron operating member connected to said ailerons, an actuating member, separate from said operating member, connected to said means and adapted to engage and displace said operating member by movement of said means in one direction, said means being positioned to separate said actuating member from said operating member when moved in the opposite direc tion, whereby said operating member is initially idle on the last named movement of said means.

2. In an airplane having a fuselage, ailerons and elevators, Weighted means slidable axially in said fuselage and linked to said elevators, an operating member connected to said ailerons, an actuating member, separate from said operating member, connected to said means and adapted to engage and displace said operating member by movement of said means in one direction, said means being positioned to separate said actuating member from said operating member when moved in the opposite direction, whereby said operating member is initially idle on the last named movement of said means.

y3. In an airplane having a fuselage and ailer ons, weighted means slidable axially in said fuselage, an aileron operating member connected to said ailerons, an actuating member, separate from said operating member, connected to said meansand adapted to engage and displace said operating member by movement of said means in one direction, said means being positioned to separate said actuating member from said operating member when moved in the opposite direction, whereby said operating member is initially idle on the last named movement of said means, and a manually operated brake functionally engaging said Weighted means for restraining the latter in one direction.

4. In an airplane h'aving a fuselage, ailerons and elevators, Weighted means slidable axially in said fuselage and linked to said elevators, an

operating member connected to said ailerons, an

actuating member, separate from said operating member, connected to said means vand adapted to engage and displace said operating Vmember by movement of said means in one direction, said means being positioned to separate said actuated member operating member is initially idle on the.' last named movement of said means, and a manudirection.

ARMAND Lavora. j

from said operating member whenmoved in the opposite direction, whereby .saidl

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