WO2006076647A3 - Autorotation flight control system - Google Patents

Autorotation flight control system Download PDF

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Publication number
WO2006076647A3
WO2006076647A3 PCT/US2006/001347 US2006001347W WO2006076647A3 WO 2006076647 A3 WO2006076647 A3 WO 2006076647A3 US 2006001347 W US2006001347 W US 2006001347W WO 2006076647 A3 WO2006076647 A3 WO 2006076647A3
Authority
WO
WIPO (PCT)
Prior art keywords
rotorcraft
control
pilot
commands
case
Prior art date
Application number
PCT/US2006/001347
Other languages
French (fr)
Other versions
WO2006076647B1 (en
WO2006076647A2 (en
Inventor
Edward N Bachelder
Dong-Chan Lee
Bimal Aponso
Original Assignee
Systems Technology Inc
Edward N Bachelder
Dong-Chan Lee
Bimal Aponso
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 Systems Technology Inc, Edward N Bachelder, Dong-Chan Lee, Bimal Aponso filed Critical Systems Technology Inc
Publication of WO2006076647A2 publication Critical patent/WO2006076647A2/en
Publication of WO2006076647A3 publication Critical patent/WO2006076647A3/en
Publication of WO2006076647B1 publication Critical patent/WO2006076647B1/en

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
    • G05D1/10—Simultaneous control of position or course in three dimensions
    • G05D1/101—Simultaneous control of position or course in three dimensions specially adapted for aircraft
    • G05D1/105—Simultaneous control of position or course in three dimensions specially adapted for aircraft specially adapted for unpowered flight, e.g. glider, parachuting, forced landing
    • 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

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)
  • Feedback Control In General (AREA)
  • Processing Or Creating Images (AREA)
  • Traffic Control Systems (AREA)

Abstract

The present invention provides computer implemented methodology that permits the safe landing and recovery of rotorcraft following engine failure. With this invention successful autorotations may be performed from well within the unsafe operating area of the height- velocity profile of a helicopter by employing the fast and robust real-time trajectory optimization algorithm that commands control motion through an intuitive pilot display, or directly in the case of autonomous rotorcraft. The algorithm generates optimal trajectories and control commands via the direct-collocation optimization method, solved using a nonlinear programming problem solver. The control inputs computed are collective pitch and aircraft pitch, which are easily tracked and manipulated by the pilot or converted to control actuator commands for automated operation during autorotation in the case of an autonomous rotorcraft. The formulation of the optimal control problem has been carefully tailored so the solutions resemble those of an expert pilot, accounting for the performance limitations of the rotorcraft and safety concerns.
PCT/US2006/001347 2005-01-14 2006-01-13 Autorotation flight control system WO2006076647A2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US64410505P 2005-01-14 2005-01-14
US60/644,105 2005-01-14

Publications (3)

Publication Number Publication Date
WO2006076647A2 WO2006076647A2 (en) 2006-07-20
WO2006076647A3 true WO2006076647A3 (en) 2007-02-08
WO2006076647B1 WO2006076647B1 (en) 2007-08-16

Family

ID=36678247

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2006/001347 WO2006076647A2 (en) 2005-01-14 2006-01-13 Autorotation flight control system

Country Status (1)

Country Link
WO (1) WO2006076647A2 (en)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105676873A (en) * 2016-03-08 2016-06-15 览意科技（上海）有限公司 Automatic landing method and control system of unmanned aerial vehicle
US11194349B2 (en) * 2016-06-27 2021-12-07 Sikorsky Aircraft Corporation Automated autorotation and pilot aiding system
CN107202584B (en) * 2017-07-06 2020-02-14 北京理工大学 Planet accurate landing anti-interference guidance method
CN107957686B (en) * 2017-11-24 2019-09-06 南京航空航天大学 Unmanned helicopter auto landing on deck control system based on prediction control
US11352900B2 (en) 2019-05-14 2022-06-07 Pratt & Whitney Canada Corp. Method and system for operating a rotorcraft engine
CN115047767B (en) * 2022-06-14 2023-06-06 北京中科飞鸿科技股份有限公司 Diving trajectory optimization method considering altimeter use constraint

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6798423B2 (en) * 2001-10-11 2004-09-28 The Boeing Company Precision perspective flight guidance symbology system

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6798423B2 (en) * 2001-10-11 2004-09-28 The Boeing Company Precision perspective flight guidance symbology system

Also Published As

Publication number Publication date
WO2006076647B1 (en) 2007-08-16
WO2006076647A2 (en) 2006-07-20

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