Flight controls with automatic balance

Details Flight controls with automatic balance Flight controls with automatic balance

1998-08-25

2001-04-24

Swiatek, Robert P. (Department: 3644)

Aeronautics and astronautics

Aircraft sustentation

Sustaining airfoils

C244S09000B, C244S089000

Reexamination Certificate

active

06220551

ABSTRACT:

BACKGROUND OF THE INVENTION
1. Field of Invention
This invention relates to a flight control system for use in an aircraft which compensates aerodynamically for the amount of deflection required to provide such a control in response to the variations in airspeed or fluid pressure.
2. Brief Description of the Prior Art
Aircraft flight controls take the form of primary and secondary surfaces which are hinged to the trailing or aft portion of directional, horizontal stabilizer members, and wings on the aircraft. Said members may include ailerons, elevators, rudders, and flaps. The pneumatic or electric system which are operated by the pilot or autopilot, by means of one or two actuators but in most of these systems are used two one piece ailerons or surfaces. One actuator operates always and the other only acts at low speed. Otherwise, the flaps' extension is changed as a function of the airspeed; it is reduced as the airspeed increases. Other like flaps are acted manually by steps or stages. In all cases, the deflection is increased as the airspeed decreases.
SUMMARY OF THE INVENTION
The present invention includes flight controls with automatic balance that control the movement of an aircraft through a fluid system. Said control system comprises ailerons divided into two parts, which at low speed adopt the shape of a conventional aileron and rotate in their entity with the same degree as the opposing-symmetrical partner flap. At high speeds, a part of the flap rotates or extends to a determinated angle by means of the actuator. The other part of the aileron, that is hinged or articulated to the main part of the aileron, rotates with reference to the main part as a function of the air speed pressure. Opposing this rotation are one or more springs.
The mechanical resistance of springs as required are exponential. However, the mechanical resistance may be linear or other desired so that the spring operates throughout the movement, or only in a low or high-speed zone.
The two-pieces ailerons use springs and adopt the form of a variable thickness aerodynamic profile.
The ailerons may be hollow or compacted, of variable cross-section, tapering toward the trailing edge. Both have an aerodynamic profile with hollow ailerons. Hot air can be made to flow through them to heat them. The flaps can include means to allow hot air to emerge through holes in the flaps surface.
When the flap is at high speed, dynamic air pressure causes the flaps to retract completely, so that together with the wing, the flaps form an aerodynamic profile.
The flaps may also be of rigid design. The rigid design contains flaps that are articulated to the wing and turn on a shaft. Springs or strips are used that control the flexibility of the flaps so that, the flaps are extended at low speed, and retracted at high speed.
The flaps size, whether of one or more elements, provides a large surface that allows for greater lift without the need for leading edge flaps.
Using rotating flaps around a tubular shaft, this is joined by means of a cardan to the shaft of the symmetrical flap to avoid asymmetry.
Provided that springs are close to the rotating shaft they provide its safe use.
An addition over-center spring can hold and fix the aileron.
Because this system acts automatically and with the use of only some springs, some devices and controls used to control the secondary or low speed surfaces are avoided.
A goal of the invention is to provide a sure, simple, and economical improvement to existing airplane flaps


REFERENCES:
patent: 3987984 (1976-10-01), Fischer
patent: 3994452 (1976-11-01), Cole
patent: 4053124 (1977-10-01), Cole
patent: 5794893 (1998-08-01), Diller et al.

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