GB666540A - Improvements in and relating to control apparatus for automatic pilots for aircraft - Google Patents
Improvements in and relating to control apparatus for automatic pilots for aircraftInfo
- Publication number
- GB666540A GB666540A GB27750/49A GB2775049A GB666540A GB 666540 A GB666540 A GB 666540A GB 27750/49 A GB27750/49 A GB 27750/49A GB 2775049 A GB2775049 A GB 2775049A GB 666540 A GB666540 A GB 666540A
- Authority
- GB
- United Kingdom
- Prior art keywords
- transformer
- signal
- lift
- voltage
- aircraft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
- 238000004804 winding Methods 0.000 abstract 7
- 230000006835 compression Effects 0.000 abstract 1
- 238000007906 compression Methods 0.000 abstract 1
- 239000004020 conductor Substances 0.000 abstract 1
- 230000008878 coupling Effects 0.000 abstract 1
- 238000010168 coupling process Methods 0.000 abstract 1
- 238000005859 coupling reaction Methods 0.000 abstract 1
- 230000001419 dependent effect Effects 0.000 abstract 1
- 230000000694 effects Effects 0.000 abstract 1
- 239000007787 solid Substances 0.000 abstract 1
Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/04—Control of altitude or depth
- G05D1/06—Rate of change of altitude or depth
- G05D1/0607—Rate of change of altitude or depth specially adapted for aircraft
- G05D1/0615—Rate of change of altitude or depth specially adapted for aircraft to counteract a perturbation, e.g. gust of wind
- G05D1/063—Rate of change of altitude or depth specially adapted for aircraft to counteract a perturbation, e.g. gust of wind by acting on the motors
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Automation & Control Theory (AREA)
- Control Of Multiple Motors (AREA)
Abstract
666,540. Automatic control systems for aircraft. SPERRY CORPORATION. Jan. 31, 1946 [Jan, 31, 1945], No. 27750/49. Divided out of 666,471. Class 38 (iv). An automatic control system for aircraft, arranged to effect an adjustment of a control surface, e.g. elevator, to maintain a predetermined magnitude of lift despite disturbances such as changes of bank, load, or relative air speed, comprises means, namely strain gauges, for defining a measure of the desired lift of the aircraft and arranged to produce signals dependent on the deviation of the vertical component of instantaneous lift from the desired lift, these signals being applied automatically to adjust the control surface to counteract the deviations and restore the lift to the desired value. Four strain gauges 50 ... 53 are provided, respectively at the upper and lower surfaces of each wing, adjacent to the body of the aircraft, so that when the wings are loaded the upper gauges 50, 51 are in compression and the lower gauges 52, 53 in tension. The strain gauges are preferably of the type comprising a continuous solid filament of electrical conducting material bonded throughout its effective length to the surface of the strained member, so that its length and electrical resistance vary with the strain. The four gauges are connected in a Wheatatone bridge circuit fed from an A.C. source 55, and the resultant signal, which is proportional to the total lift, is fed through an amplifier 62 to the primary winding of a transformer 64 the secondary of which is rotatable with the fore- and-aft gimbal axis 68-68. The signal transformer 64 is arranged so that its output voltage V3 is equal to the input voltage V2 multiplied to the input voltage V2 multiplied by the cosine of the bank angle as given by the vertical gyro, and is thus proportional to the vertical component of the lift. The voltage V3 is applied to one winding of the threewinding transformer 65 of a follow-up system, the other two windings being connected respectively to a velocity follow-up amplifier 67 and the divided secondary winding of a transformer 66. The amplifier 67 is phase sensitive and connected to feed a two-phase motor 78 driving a generator 77 which is connected to provide a high negative feed-back signal proportional to the motor speed, and the outer ends of the shafts of the motor and generator are associated with couplings controlled by a manually-operated link 9 whereby the system angularly displaces alternatively, either the primary winding of transformer 66 or the primary winding of a pitch signal transformer 86 of the Selsyn type. To produce a datum signal corresponding to the weight of the aircraft the latter is first set on normal level flight and the linkage 9 operated to engage the clutch connecting the rotary winding of transformer 66 to the coupled shafts of motor 78 and generator 77, with the result that motor 78 turns in one direction or the other until the voltage V4 is made equal to voltage V3. Automatic control is then introduced by operating the clutch linkage 9 to disengage the signal transformer 66, which is now held by a friction brake 11, and engage the rotor of pitch signal Selsyn 86 which, through three lines 87, is connected to a receiver Selsyn 88 with rotor mounted on the pitch axis 79 of the vertical gyroscope 69. The output signal from Selsyn 88 is fed through an amplifier 28 to a servo-motor 16 for deflecting the elevation or pitch control of the aircraft. If, through banking or downward pitching, the vertical component of the lift should fall, the voltage V3, which is a measure of the said vertical component, becomes smaller than the pre-set voltage V4, with the result that motor 78 operates the rotor of Selsyn 88 to change its signal output from its normal zero value, so that the amplified signal fed to the servomotor 16 causes operation of the elevator 29 to correct the angle of attack until the voltage V3 is again equal to V4. Specification 666,471 is referred to.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US666540XA | 1945-01-31 | 1945-01-31 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB666540A true GB666540A (en) | 1952-02-13 |
Family
ID=22070847
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB27750/49A Expired GB666540A (en) | 1945-01-31 | 1946-01-31 | Improvements in and relating to control apparatus for automatic pilots for aircraft |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB666540A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7658113B2 (en) | 2007-02-16 | 2010-02-09 | Rolls-Royce Plc | Lift measurement |
-
1946
- 1946-01-31 GB GB27750/49A patent/GB666540A/en not_active Expired
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7658113B2 (en) | 2007-02-16 | 2010-02-09 | Rolls-Royce Plc | Lift measurement |
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