GB990243A - Engine thrust control - Google Patents

Engine thrust control

Info

Publication number
GB990243A
GB990243A GB36235/61A GB3623561A GB990243A GB 990243 A GB990243 A GB 990243A GB 36235/61 A GB36235/61 A GB 36235/61A GB 3623561 A GB3623561 A GB 3623561A GB 990243 A GB990243 A GB 990243A
Authority
GB
United Kingdom
Prior art keywords
thrust
amplifiers
thrusts
engines
amplifier
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
Application number
GB36235/61A
Inventor
Henry Cook
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Allard Way Holdings Ltd
Original Assignee
Elliott Brothers London Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Elliott Brothers London Ltd filed Critical Elliott Brothers London Ltd
Priority to GB36235/61A priority Critical patent/GB990243A/en
Publication of GB990243A publication Critical patent/GB990243A/en
Expired legal-status Critical Current

Links

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

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)
  • Electrical Control Of Air Or Fuel Supplied To Internal-Combustion Engine (AREA)
  • Combined Controls Of Internal Combustion Engines (AREA)

Abstract

990,243. Automatic control of aircraft. ELLIOTT BROS. (LONDON) Ltd. Nov. 14,1962 [Oct. 9,1961], No. 36235/61. Heading G3R. In a system for automatically controlling both the collective and differential thrusts of two engines or groups of engines on an aircraft,the desired thrusts are determined by electrical signals,set manually,which control the engine throttles in an appropriate manner in conjunction with signals dependent on the engine thrusts. In Fig. 1 electrical signals dependent on the thrust of port or forward jet engines 11 on a VTOL or STOL aircraft and electrical signals dependent on the thrust of starboard or after jet engines 12 are derived by meters 14, 15 and automatically corrected by variable gain devices 3 2,31, adjusted in dependence on nozzle angles, to give signals, representative of the vertical components of thrust, which are applied to amplifiers 34,33 respectively. The outputs of amplifiers 34,33 are combined in an amplifier 23 and compared with signals representing desired total thrust set by a manual lever 16 so that any deviation results in an output from amplifier 23 which, through amplifiers 28,24, energizes engine throttle actuators 29, 25 to correct the total vertical thrust. Positional feedback is applied from the throttle actuators to the inputs of amplifiers 28, 24. The signals representing the thrusts of the two sets of engines are also applied in opposite senses to an amplifier 35 which compares their difference with signals representing desired differential thrust set by a manual lever 17,a manual trim device 21,or an automatic trim device 22. The output of amplifier 35 is applied in opposite senses to amplifiers 28, 24 to vary the thrusts differentially and thus control the roll or pitch attitude of the aircraft. The total and differential thrust datums may also be controlled by an autopilot 40.
GB36235/61A 1961-10-09 1961-10-09 Engine thrust control Expired GB990243A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB36235/61A GB990243A (en) 1961-10-09 1961-10-09 Engine thrust control

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB36235/61A GB990243A (en) 1961-10-09 1961-10-09 Engine thrust control

Publications (1)

Publication Number Publication Date
GB990243A true GB990243A (en) 1965-04-28

Family

ID=10386226

Family Applications (1)

Application Number Title Priority Date Filing Date
GB36235/61A Expired GB990243A (en) 1961-10-09 1961-10-09 Engine thrust control

Country Status (1)

Country Link
GB (1) GB990243A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111811824A (en) * 2020-06-18 2020-10-23 上海空间推进研究所 Attitude control engine polarity testing tool and using method thereof
CN112373704A (en) * 2020-11-17 2021-02-19 中国商用飞机有限责任公司 System for realizing emergency control of airplane by controlling engine thrust and airplane

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111811824A (en) * 2020-06-18 2020-10-23 上海空间推进研究所 Attitude control engine polarity testing tool and using method thereof
CN112373704A (en) * 2020-11-17 2021-02-19 中国商用飞机有限责任公司 System for realizing emergency control of airplane by controlling engine thrust and airplane

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