Controller-throttle engages spoiler/dive brake system when throttle setting is below a fixed power setting and gradually increases effect of spoiler/dive brake as throttle is moved toward idle position; since action is automatically reversible, a sudden application of power abruptly terminates aerodynamic effects of spoiler/dive brake system

Ellis, D. R.

Olcott, J. W.

Seckel, E.

English

NASA Technical Reports Server

May 1972	 B72-10213 
NASA TECH BRIEF 
Ames Research Center 	 -4r 
NASA Tech Briefs announce new technology derived from the U.S. space program. They are issued to encourage 
commercial application. Tech Briefs are available on a subscription basis from the National Technical Information 
Service, Springfield, Virginia 22151. Requests for individual copies or questions relating to the Tech Brief program may 
be directed to the Technology Utilization Office, NASA, Code KT, Washington, D.C. 20546. 
Integrated Flight Controller For Light Aircraft 
The problem: 
Over half of all accidents involving small fixed-
wing aircraft occur during approach and landing 
maneuvers. Because safe landings require the utmost 
in skill and unswerving attention on the part of the 
pilot, NASA is investigating the use of devices or 
aids which simplify the pilot's tasks. Research has 
been conducted on the application of spoiler/dive 
brakes to small fixed-wing general aviation aircraft 
so as to improve performance and handling qualities 
during the typical landing maneuvers of approach, 
flare, touchdown, and rollout as well as during go-
around phases of operation. It was found that spoiler/ 
dive brakes offer significant improvements in the 
performance and handling qualities of small aircraft, 
but a suitable means of safely controlling the per-
formance of these aerodynamic surfaces must be 
provided, for the aircraft is incapable of climbing 
satisfactorily at any time when the spoiler/dive 
brakes are fully deployed, even at full power. 
The solution: 
An integrated controller-throttle which engages the 
spoiler/dive brake system when the throttle setting 
is below a fixed power setting and gradually increases 
the effect of the spoiler/dive brake as the throttle is 
moved toward the idle position; since action is auto-
matically reversible, a sudden application of power 
(as in an aborted landing maneuver) abruptly ter-
minates the aerodynamic effects of the spoiler/dive 
brake system. 
How it's done: 
1. The required aerodynamic modifications for con-
trol of lift-to-drag ratio (L/D control) are added to
the basic design of the aircraft. 
2. The throttle lever is redesigned to accommodate 
connections to the added surfaces. This is the inte-
grated flight controller. 
8. Controls are rigged and adjusted to coordinate 
the functions as desired. The normal functions of the 
throttle are maintained for power settings greater 
than the specific setting called the L/D engage point. 
As power is reduced below this point, control of the 
L/D devices is blended with throttle control, in-
creasing L/D alteration to optimize approach and 
landing performance. Blending continues to the point 
of engine idle. Movement of the integrated controller 
beyond the normal idle stop is possible to command 
additional L/D alteration while engine power re-
mains at idle. 
For many years, spoilers and dive brakes have 
been used successfully on sail planes for landing 
operation. Preliminary test results indicate that an 
integrated controller significantly improves the po-
tential of applying spoilers and dive brakes to small 
aircraft. Spoilers coupled by the integrated flight 
controller improve handling qualities of small aircraft 
to the point where the level of skill required for 
landing is considerably reduced; as a result, landing 
accidents may be reduced. 
Notes: 
1. Research to date on integrated controllers has been 
limited to application for spoiler/dive brakes. 
Potential exists for adoption with other L/D alter-
ation devices, such as boundary layer control sys-
tems, flaps, spoilers alone, dive brakes alone and/ 
or negative thrust on propellers.
(continued overleaf) 
This document was prepared under the sponsorship of the National
	 Government assumes any liability resulting from the use of the 
Aeronautics and Space Administration. Neither the United States 	 information contained in this document, or warrants that such use 
Government nor any person acting on behalf of the United States
	 will be free from privately owned rights.
https://ntrs.nasa.gov/search.jsp?R=19720000213 2020-03-17T03:33:34+00:00Z
2. Requests for further information may be di-
rected to: 
Technology Utilization Officer 
Ames Research Center 
Moffett Field, California 94035 
Reference: TSP72-10213
Patent status: 
No patent action is contemplated by NASA. 
Source: John W. Olcott David R. Ellis, and

Edward Seckel of
Aeronautical Research Associates of Princeton, Inc.

under contract to

Ames Research Center 
(ARC-10456) 
B72-10218	 Category 06


Integrated flight controller for light aircraft

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