Patent US-1916-1326946
This invention is about a method of control of an aeroplane's stability in a "proper, normal or predetermined attitude of flight." Some aeroplane stabilizers operate by adjusting the controlling surfaces of the aeroplane to deflect the aeroplane from its predetermined course. An objection to all such devices has been that they "over-control" -- the stabilizing mechanisms maintain the controlling means in an adjusted position until the aeroplane reaches its normal flying position, and then momentum from the aeroplane's return to such position from a deflected position carries the aeroplane over and beyond its normal position.
My method of control obviates such occurrences, and the method of control is slightly different for different degrees of deflection or deviation of the aeroplane or other vehicle upon which the apparatus may be connected, from its predetermined attitude and course, so that the restoring effect imposed upon the aeroplane may be applied with different degrees of effectiveness according to the intensity and degree of deflection of the aeroplane from its normal attitude.
Objectives of the invention:
- to provide a method of control for an apparatus on an aeroplane to be connected with the actuating means for the controls of the aeroplane whereby the same may be automatically operated to maintain the <> plane on an even keel or at a bank, and which acts to restore the same to normal flying attitude when deflected therefrom for any causes whatsoever.
- to provide a method of aeroplane control whereby the controls of the aeroplane are actuated to correct deflections or tilting of the aeroplane from a predetermined attitude of flight, restoring the same to normal without the objectionable feature of over-control, moving the same beyond its normal flying position by the restoration effect thereon.
- to control an aeroplane or other vehicle control by using gravity acting levers or plumbs and electrical circuits for energizing electrical driving devices whereby the aeroplane controls are actuated, and with the mechanisms which close and open the electric circuit so constructed that a different series of operations is passed through for different degrees and intensity of deflection of a vehicle from its predetermined . . .
- Tech classifications: CPC B64C17/00 Aircraft stabilisation not otherwise provided for
- Assignee Macy Engineering Company of Franklin, PA, a corporation of Maine
- Application filed by Macy Engineering Company
- Inventor location: Chicago, Cook county, IL (FIPSloc=17031, imputed from HistPat
- Witnesses (as shown on the final text page): Charles W. Hills, Jr. and Earl M. Hardine
Sources
- Patent 1326946 document and bibliographic info on espacenet
- Patent 1326946 at google patents
| Year filed | 1916 |
|---|---|
| Year granted | 1920 |
| Office | US |
| Patent number | 1326946 |
| Inventors | Alfred John Macy |
| Inventor country | US |
| Applicant person | Alfred John Macy |
| Applicant firm | Macy Engineering Company |
| Applicant type | COMPANY + INDIV |
| Applicant is inventor? | No |
| Original title | Method of automatic control for vehicles |
| English title | Method of automatic control for vehicles |
| Tech fields | control, stability, automatic stability, pendulum |
| Filing date | 1916/03/25 |
| Full specification filed date | |
| Application number | 86613/16 |
| Grant date | 1920/01/06 |
| Granted? | Yes |
| Publication date | |
| Supplementary to patent | |
| Related to aircraft? | Yes |
| Serial number | 86613 |
| Patent agent | |
| Assigned to | Macy Engineering Company |
| National tech categories | USPC 244/177, USPC 244/80 |
| IPCs | IPC B64C17/00 |
| CPCs | CPC B64C17/00 |
| Family year | 1916 |
| First filing? | Yes |
| Cites these patents | |
| Citations from after 1930 | |
| Application ID | 47057138 |
| INPADOC family ID | 47194235 |
| Number of text pages | 7 |
| Number of diagram pages | 5 |
| Number of figures | 24 |
| Number of claims | 11 |
