Control Surface historical question.

[Arends]

I have just discovered a patent GB524,865 filed by my grandfather in 1941. He was killed in action less than 12 months later and the details of his patent remained undiscovered until now. I am trying to ascertain if the control surface design was ever incorporated and which aircraft utilised this system.

In his arrangement the ailerons and orthodox type of rudder and fin are dispensed with, directional and lateral control being obtained by means of "flap tips" which are built into the elevators. They are hinged on double hinge lines at an angle to one another and can be turned simultaneously or independently about the lines converging towards and diverging away from the axis of the aeroplane. The flap tips are turned about the different hinge lines to give in one instance an aileron effect and in the other, a rudder effect. In flight the aircraft would be turned by moving one flap upwards so that it would act as a rudder while simultaneously, the other flap would be turned down. The tailplane should have a pronounced dihedral.

The object of the invention was to improve the lift over drag ratio by eliminating the vertical fin and rudder.

If anyone would like to view diagrams of this 1941 patent please access the European patent site at

http://www.espacenet.com,

then choose the: Access to esp@cenet, then click the red highlighted EPO. Finally place the patent number GB524865 in the "view a patent application window.

Alternatively please request diagrams directly from me, darren@tobethebest.fsnet.co.uk

Any observations would be gratefully received.

Many Thanks
Darren

 

[chasbo]

I've never heard of any aircraft using this, and I've been a pilot and active EAAer for over 30 years. Rutan started the VariEZE with the canard having independent control of the elevators on the canard, to try and use them as elevons to avoid having to put ailerons on the main wing. He didn't have enough roll control, and so had to add ailerons to the VariEZE. I would expect the same problem with the aircraft as described, plus it would not have any static stability, since the pilot would have to make control inputs to get the plane to make yaw corrections.

 

[matt00000]

The configuration of the tailplane is not totally unique. several aircraft have dihedral configuration elevators and no vertical fin.

I only had a quick look at the diagrams and it occurs to me that it would be difficult to mount actuators as to move the control surfaces. I think it may be difficult to provide enough strength to overcome flutter also.

I think that the idea has been superceeded by all moving tailerons.

He obviously thought about the problem a great deal though and he was obviously knowledgeable in this area.