GB812748A - Improvements in computers for determining the optimum cruising altitude of an aircraft - Google Patents
Improvements in computers for determining the optimum cruising altitude of an aircraftInfo
- Publication number
- GB812748A GB812748A GB1675/57A GB167557A GB812748A GB 812748 A GB812748 A GB 812748A GB 1675/57 A GB1675/57 A GB 1675/57A GB 167557 A GB167557 A GB 167557A GB 812748 A GB812748 A GB 812748A
- Authority
- GB
- United Kingdom
- Prior art keywords
- aircraft
- altitude
- signal
- motor
- rotor
- 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 2
- 238000001816 cooling Methods 0.000 abstract 1
- 238000006073 displacement reaction Methods 0.000 abstract 1
- 239000000446 fuel Substances 0.000 abstract 1
- 238000010438 heat treatment Methods 0.000 abstract 1
- 238000012886 linear function Methods 0.000 abstract 1
- 238000005259 measurement Methods 0.000 abstract 1
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06G—ANALOGUE COMPUTERS
- G06G7/00—Devices in which the computing operation is performed by varying electric or magnetic quantities
- G06G7/48—Analogue computers for specific processes, systems or devices, e.g. simulators
- G06G7/70—Analogue computers for specific processes, systems or devices, e.g. simulators for vehicles, e.g. to determine permissible loading of ships, centre of gravity, necessary fuel
-
- 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
- G05D1/0005—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots with arrangements to save energy
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Computer Hardware Design (AREA)
- Theoretical Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Automation & Control Theory (AREA)
- Mathematical Physics (AREA)
- Control Of Vehicle Engines Or Engines For Specific Uses (AREA)
- Indication And Recording Devices For Special Purposes And Tariff Metering Devices (AREA)
Abstract
812,748. Controlling aircraft ; aircraft indicators. BENDIX AVIATION CORPORATION. Jan. 16, 1957 [Jan. 23, 1956], No. 1675/57. Class 4. [Also in Groups XXXVI and XXXVIII] The optimum cruising altitude of an aircraft is calculated by obtaining signals representative of the instantaneous altitude, ambient temperature and gross weight, and detecting deviations of the combination of these signals from the value which corresponds with optimum conditions. In Fig. 1 the units 10, 11 and 13 produce signals corresponding to altitude, temperature and weight respectively. The aneroid barometer 20 displaces the rotor 22 relative to the stator 2 4 and develops in the latter a signal indicative of the magnitude and direction of displacement. This signal is applied via potentiometer 25 (see below) and amplifier 26 to a motor 27 which drives the stator 24 to a new null position and at the same time displaces the rotor 30 relative to the stator 32. The temperature-sensitive element 41 is mounted outside the aircraft in a position such that air is driven by a vane to create a vortex around, the element; the cooling effect of the vortex then compensates for the dynamic heating and the reading is correct for ambient temperature. When the latter changes, the bridge 40 is unbalanced and the voltage so generated energises the motor 45 to drive the slider 47 until the bridge output is zero: At the same time the rotor of the differential transformer 49 is displaced relative to the stator. The instantaneous weight is calculated from a setting of the initial gross weight and measurement of the rate of consumption of fuel. The latter flows past two pivoted vanes 54 and displaces them against the action of springs. The rotors 60, 64 are thus turned relative to their stators and the voltages so produced are summed, amplified and passed to the motor 72. This turns the rate generator 73 to supply negative feedback to the source, and also displaces the rotor 80. The initial gross weight of the aircraft is set up by the knob 83 as the angular position of the stator 82. A voltage is supplied to rotor 30 and passed on through windings 32, 49, 82 and 80, and if values of temperature and weight are correct for the particular altitude no voltage is developed at the rotor 80. If one of the three parameters changes, a signal is obtained at 80 indicating by phase sense and amplitude the direction and amount of the change. This signal is applied via the transformer 89 to a motor 105 in conjunction with the signal from a vertical gyro 100, and the difference between the two displaces the elevator surface 107 until the followup device 111 brings the difference to zero. The aircraft then climbs or descends until the changing signal from the altitude sensor 10 restores the output 80 to zero, when the motor 105 brings the elevator back to the level position. By a similar circuit the transformer 89 also controls the throttle via the motor 122, and a third winding operates the indicator 130 to show when the aircraft deviates from the correct altitude. The adjustment of elevator and throttle may be carried out manually instead of automatically. For correct compensation it is necessary that the signals from the circuits 10 and 11 be non-linear functions of the altitude and temeperature respectively. This is achieved by causing the motor 27 to operate a potentiometer 25 which injects a further signal into the circuit, of amplitude depending on the output signal. A further potentiometer 152 driven by the same motor varies the input to the temperature bridge in accordance with variations in the altitude signal.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US812748XA | 1956-01-23 | 1956-01-23 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB812748A true GB812748A (en) | 1959-04-29 |
Family
ID=22163159
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1675/57A Expired GB812748A (en) | 1956-01-23 | 1957-01-16 | Improvements in computers for determining the optimum cruising altitude of an aircraft |
Country Status (2)
Country | Link |
---|---|
DE (1) | DE1096762B (en) |
GB (1) | GB812748A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN111221350A (en) * | 2019-12-30 | 2020-06-02 | 湖北航天技术研究院总体设计所 | Method and system for designing trajectory of air-breathing hypersonic aircraft cruise missile |
-
1957
- 1957-01-16 GB GB1675/57A patent/GB812748A/en not_active Expired
- 1957-01-22 DE DEB43217A patent/DE1096762B/en active Pending
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN111221350A (en) * | 2019-12-30 | 2020-06-02 | 湖北航天技术研究院总体设计所 | Method and system for designing trajectory of air-breathing hypersonic aircraft cruise missile |
Also Published As
Publication number | Publication date |
---|---|
DE1096762B (en) | 1961-01-05 |
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