ES499715A0 - Perfeccionamientos en los sistemas de aumento de estabilidadredundante diferente para aeronaves - Google Patents

Perfeccionamientos en los sistemas de aumento de estabilidadredundante diferente para aeronaves

Info

Publication number
ES499715A0
ES499715A0 ES499715A ES499715A ES499715A0 ES 499715 A0 ES499715 A0 ES 499715A0 ES 499715 A ES499715 A ES 499715A ES 499715 A ES499715 A ES 499715A ES 499715 A0 ES499715 A0 ES 499715A0
Authority
ES
Spain
Prior art keywords
aircraft
different stability
stability increase
increase systems
systems
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.)
Granted
Application number
ES499715A
Other languages
English (en)
Other versions
ES8203756A1 (es
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.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
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 United Technologies Corp filed Critical United Technologies Corp
Publication of ES499715A0 publication Critical patent/ES499715A0/es
Publication of ES8203756A1 publication Critical patent/ES8203756A1/es
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
    • G05D1/08—Control of attitude, i.e. control of roll, pitch, or yaw
    • G05D1/0808—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft
    • G05D1/0858—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft specially adapted for vertical take-off of aircraft
    • 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
    • G05D1/0055—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots with safety arrangements
    • G05D1/0077—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots with safety arrangements using redundant signals or controls

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)
  • Gyroscopes (AREA)
  • Retry When Errors Occur (AREA)
  • Hardware Redundancy (AREA)
  • Safety Devices In Control Systems (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
  • Navigation (AREA)
ES499715A 1980-03-05 1981-02-23 Perfeccionamientos en los sistemas de aumento de estabilidadredundante diferente para aeronaves Expired ES8203756A1 (es)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US06/127,332 US4313201A (en) 1980-03-05 1980-03-05 Tested, dissimilar helicopter stability augmentation

Publications (2)

Publication Number Publication Date
ES499715A0 true ES499715A0 (es) 1982-05-01
ES8203756A1 ES8203756A1 (es) 1982-05-01

Family

ID=22429564

Family Applications (1)

Application Number Title Priority Date Filing Date
ES499715A Expired ES8203756A1 (es) 1980-03-05 1981-02-23 Perfeccionamientos en los sistemas de aumento de estabilidadredundante diferente para aeronaves

Country Status (8)

Country Link
US (1) US4313201A (es)
JP (1) JPS56167597A (es)
AU (1) AU537146B2 (es)
CA (1) CA1153810A (es)
DE (1) DE3106848A1 (es)
ES (1) ES8203756A1 (es)
GB (1) GB2070808B (es)
IT (1) IT1138961B (es)

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4370706A (en) * 1980-09-26 1983-01-25 The Bendix Corporation Controller for a dual servo system
US4443853A (en) * 1981-03-25 1984-04-17 United Technologies Corporation Optical digital servo control system
US4484283A (en) * 1981-03-30 1984-11-20 United Technologies Corporation Aircraft roll-yaw fault protocols
US4545019A (en) * 1982-06-18 1985-10-01 Sundstrand Corporation Aircraft in-flight center of gravity measuring system
US4622667A (en) * 1984-11-27 1986-11-11 Sperry Corporation Digital fail operational automatic flight control system utilizing redundant dissimilar data processing
GB2185951B (en) * 1986-02-04 1989-07-05 Rolls Royce Helicopter rotor and engine control
JPH07122811B2 (ja) * 1986-10-08 1995-12-25 株式会社東芝 シ−ケンス制御装置
GB8807676D0 (en) * 1988-03-31 1988-05-05 Westland Helicopters Helicopter control systems
US5001646A (en) * 1988-12-19 1991-03-19 Mcdonnell Douglas Corporation Automated helicopter flight control system
US5213283A (en) * 1991-08-28 1993-05-25 United Technologies Corporation Low speed turn coordination for rotary wing aircraft
US5238203A (en) * 1991-08-28 1993-08-24 United Technologies Corporation High speed turn coordination for rotary wing aircraft
US8484557B1 (en) * 2008-07-29 2013-07-09 Adobe Systems Incorporated Methods and systems for defining preflight profile rules
GB2541220A (en) * 2015-08-12 2017-02-15 Atlantic Inertial Systems Ltd Inertial sensor
US11161628B2 (en) * 2016-11-01 2021-11-02 Textron Innovations, Inc. Remote aircraft preflight verification
CN109774920A (zh) * 2019-02-22 2019-05-21 西安爱生技术集团公司 一种无人机机载稳定机构
DE102020200056A1 (de) 2020-01-07 2021-07-08 Volkswagen Aktiengesellschaft Kontrolleinheit zur kontinuierlichen Steuersignalüberprüfung bei Multirotorfluggeräten vor und während eines Flugbetriebs

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3688099A (en) * 1971-04-28 1972-08-29 Lear Siegler Inc Automatic control system with a digital computer
US3719336A (en) * 1971-05-20 1973-03-06 United Aircraft Corp Fault detector for helicopter feel augmentation system
US3732501A (en) * 1971-09-27 1973-05-08 United Aircraft Corp Redundant operational amplifier circuit for servo control systems
CA1026850A (en) * 1973-09-24 1978-02-21 Smiths Industries Limited Dual, simultaneously operating control system with fault detection
GB1502184A (en) * 1974-07-05 1978-02-22 Sperry Rand Corp Automatic flight control systems
FR2344063A1 (fr) * 1976-03-10 1977-10-07 Smiths Industries Ltd Circuit numerique de commande a deux voies au moins
US4117317A (en) * 1976-08-09 1978-09-26 Dynage, Incorporated Programmable controller with hardwired backup connecting terminals and related control system using programmable controller and hardwired backup
US4095763A (en) * 1977-02-25 1978-06-20 Textron, Inc. Fail safe augmentation system

Also Published As

Publication number Publication date
AU537146B2 (en) 1984-06-07
IT1138961B (it) 1986-09-17
US4313201A (en) 1982-01-26
JPH0358958B2 (es) 1991-09-09
CA1153810A (en) 1983-09-13
ES8203756A1 (es) 1982-05-01
GB2070808B (en) 1983-11-23
JPS56167597A (en) 1981-12-23
DE3106848C2 (es) 1990-03-29
GB2070808A (en) 1981-09-09
AU6752581A (en) 1981-09-10
DE3106848A1 (de) 1982-02-18
IT8120023A0 (it) 1981-02-27

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Legal Events

Date Code Title Description
FD1A Patent lapsed

Effective date: 20001009