GB998766A - Improvements in flight control of aircraft - Google Patents
Improvements in flight control of aircraftInfo
- Publication number
- GB998766A GB998766A GB10282/62A GB1028262A GB998766A GB 998766 A GB998766 A GB 998766A GB 10282/62 A GB10282/62 A GB 10282/62A GB 1028262 A GB1028262 A GB 1028262A GB 998766 A GB998766 A GB 998766A
- Authority
- GB
- United Kingdom
- Prior art keywords
- signal
- nozzle
- measured
- amplifier
- acceleration
- 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
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 title 1
- 230000001133 acceleration Effects 0.000 abstract 15
- 230000000087 stabilizing effect Effects 0.000 abstract 5
- 238000007599 discharging Methods 0.000 abstract 3
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
- G05D1/0653—Rate of change of altitude or depth specially adapted for aircraft during a phase of take-off or landing
- G05D1/0661—Rate of change of altitude or depth specially adapted for aircraft during a phase of take-off or landing specially adapted for take-off
- G05D1/0669—Rate of change of altitude or depth specially adapted for aircraft during a phase of take-off or landing specially adapted for take-off specially adapted for vertical take-off
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0041—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors
- B64C29/0066—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors with horizontal jet and jet deflector
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 Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
- Navigation (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
998,766. Controlling jet-propelled aircraft. BRISTOL AIRCRAFT Ltd. March 11, 1963 [March 16, 1962], No. 10282/62. Heading B7G. An aircraft having a jet-propulsion engine with a rotatable nozzle, includes means receiving vertical and horizontal acceleration demands and applying each of these partly to the engine throttle control and partly to the nozzle angle control, in proportions determined by the instantaneous nozzle angle, so that during hovering with jet lift, horizontal acceleration is produced predominantly by altering the nozzle angle, and vertical acceleration by throttle adjustment, and during cruise, the opposite obtains. The Figures show the control system of a pilotless aircraft, which receives information from a terrain following radar system 50, a programming and inertial guidance system 54 receiving commands by an aerial 56, an inertial guidance table having gyroscopes and accelerometers, and from a radio altimeter 58. Signal gain and limiting devices are indicated by G and LIM. An altitude demand signal from programmer 54 is compared with the measured altitude from altimeter 58 in summing amplifier 60, which also adds a stabilizing signal equivalent to rate of climb. The result is taken as a vertical acceleration demand signal, and provides one input to an " or " gate 62. The other input is a vertical acceleration demand signal from the terain following radar 50. The gate 62 selects the input which demands the greater upward acceleration, and this signal is fed over line 64 to a summing amplifier 66, which compares the demand with the signal from a vertical accelerometer 69, and deducts a constant " one g " signal. The resulting vertical acceleration error signal is fed to proportioning devices 70, 72, which multiply their inputs by factors U<2>/Uc<2> and 1-U<2>/Uc<2> respectively, where U is the airspeed measured by a pitot-static head 74, and Uc is the cruise speed. At cruise speed therefore, the output of device 72 is low, and vertical acceleration is controlled by device 70, which energizes equally the port and starboard elevon servos 132, 134, a pitch rate stabilizing signal from gyro 126 being added by summing amplifier 130. At low speeds, the output of device 70 is low and the vertical acceleration error signal is passed on line 96 to a resolver 80 driven by the nozzle angle servo 82 (gamma being the nozzle angle measured from the position of vertical discharge). The error signal is multiplied by cos gamma and passed to the throttle servo 92, and is multiplied by sin gamma and passed to the nozzle servo 82, so that vertical acceleration is adjusted by the throttle when the nozzle is discharging downwardly, and by the nozzle angle setting when the nozzle discharges rearwarely. A pitch demand signal from programmer 54 is fed on line 128 to summing amplifier 122 which deducts the pitch angle measured by gyro 124, and adds a pitch rate stabilizing signal from gyro 126. The resultant controls pitch altitude controlling jets 120 to provide pitch control at low speeds when the elevons are ineffective. An airspeed demand signal on line 84 from programmer 54 is compared with the measured airspeed in summing amplifier 86, the error signal being taken as the horizontal acceleration demand signal. This is compared with the horizontal acceleration measured by accelerometer 90 in amplifier 88, and the error signal is fed to resolver 80, so that it is multiplied by sin gamma and passed to the throttle servo, and by cos y and passed to the nozzle angle servo, whereby horizontal acceleration is controlled by the throttle when the nozzle is discharging horizontally, and by the nozzle angle when the nozzle is discharging vertically. To give vertical acceleration demands precedence over horizontal acceleration demands when the combined demands require a thrust that the engine cannot supply, the throttle servo total input is fed through limiter 98 and multiplied by sin gamma in resolver 80, to provide a suitable negative feedback signal to amplifier 88 when the total demand is excessive. A yaw demand signal from programmer 54 is fed over line 106 and is compared with the yaw measured by gyro 110 in amplifier 104, which also adds a stabilizing yaw rate signal from gyro 112. The resultant yaw error signal operates yaw control jets 100, which are effective only at low speeds. At high speeds, the rudder is effective, and is used solely to reduce sideslip as measured by a lateral accelerometer 114, to the output of which a yaw rate signal is added in amplifier 116, the resultant controlling the rudder servo 102. A roll demand signal from programmer 54 on line 136 is compared with the roll measured by gyro 140 in amplifier 138, and a stabilizing roll rate signal from gyro 144 is added to the roll error signal by amplifier 142. The resultant signal operates roll jet controlling vanes 146 and also operates the elevon servos 132, 134, differentially.
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB10282/62A GB998766A (en) | 1962-03-16 | 1962-03-16 | Improvements in flight control of aircraft |
DE19631406364 DE1406364A1 (en) | 1962-03-16 | 1963-03-15 | Control device for a missile with rotatable nozzles |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB10282/62A GB998766A (en) | 1962-03-16 | 1962-03-16 | Improvements in flight control of aircraft |
Publications (1)
Publication Number | Publication Date |
---|---|
GB998766A true GB998766A (en) | 1965-07-21 |
Family
ID=9964985
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB10282/62A Expired GB998766A (en) | 1962-03-16 | 1962-03-16 | Improvements in flight control of aircraft |
Country Status (2)
Country | Link |
---|---|
DE (1) | DE1406364A1 (en) |
GB (1) | GB998766A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN112558625A (en) * | 2020-12-17 | 2021-03-26 | 北京北航天宇长鹰无人机科技有限公司 | Control method for cruising of aviation aircraft and aviation aircraft |
CN113138577A (en) * | 2021-05-14 | 2021-07-20 | 北京理工大学 | Overload feedback control method for vertical channel of quad-rotor unmanned aerial vehicle |
-
1962
- 1962-03-16 GB GB10282/62A patent/GB998766A/en not_active Expired
-
1963
- 1963-03-15 DE DE19631406364 patent/DE1406364A1/en active Pending
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN112558625A (en) * | 2020-12-17 | 2021-03-26 | 北京北航天宇长鹰无人机科技有限公司 | Control method for cruising of aviation aircraft and aviation aircraft |
CN113138577A (en) * | 2021-05-14 | 2021-07-20 | 北京理工大学 | Overload feedback control method for vertical channel of quad-rotor unmanned aerial vehicle |
CN113138577B (en) * | 2021-05-14 | 2022-05-20 | 北京理工大学 | Overload feedback control method for vertical channel of quad-rotor unmanned aerial vehicle |
Also Published As
Publication number | Publication date |
---|---|
DE1406364A1 (en) | 1970-01-22 |
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