JPH0463799A - Airplane having flap - Google Patents

Airplane having flap

Info

Publication number
JPH0463799A
JPH0463799A JP17537590A JP17537590A JPH0463799A JP H0463799 A JPH0463799 A JP H0463799A JP 17537590 A JP17537590 A JP 17537590A JP 17537590 A JP17537590 A JP 17537590A JP H0463799 A JPH0463799 A JP H0463799A
Authority
JP
Japan
Prior art keywords
airplane
flap
speed
flap angle
maximum
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.)
Pending
Application number
JP17537590A
Other languages
Japanese (ja)
Inventor
Katsumasa Sugiyama
Original Assignee
Mitsubishi Heavy Ind 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 Mitsubishi Heavy Ind Ltd filed Critical Mitsubishi Heavy Ind Ltd
Priority to JP17537590A priority Critical patent/JPH0463799A/en
Publication of JPH0463799A publication Critical patent/JPH0463799A/en
Pending legal-status Critical Current

Links

Abstract

PURPOSE: To exhibit the performance of an airplane at maximum and use it safely and efficiently by controlling the flap angle based on the speed of airplane, and maintaining the flap angle at optimum value at take-off running and the like of the airplane.
CONSTITUTION: A speed signal of an airplane detected by a speed system 14 and a flap angle signal detected with a flap angle potentiometer 21 are respectively input to a computer 16 to compute and process. Meanwhile, the control signal to obtain an optimum flap angle for the speed of an airplane is transmitted from the computer 16, and input to a hydraulic device 18 to actuate it. An actuator 20 is actuated to perform change of flap angle 3. Hereby, optimum flap angles against the speed of the airplane at take-off, landing, and the like are instituted, respectively adjusted so as to be maximum increase of lift by flap and minimum increase of resistance by flap, and performance of the airplane is exhibited at maximum.
COPYRIGHT: (C)1992,JPO&Japio
JP17537590A 1990-07-04 1990-07-04 Airplane having flap Pending JPH0463799A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP17537590A JPH0463799A (en) 1990-07-04 1990-07-04 Airplane having flap

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP17537590A JPH0463799A (en) 1990-07-04 1990-07-04 Airplane having flap

Publications (1)

Publication Number Publication Date
JPH0463799A true JPH0463799A (en) 1992-02-28

Family

ID=15995005

Family Applications (1)

Application Number Title Priority Date Filing Date
JP17537590A Pending JPH0463799A (en) 1990-07-04 1990-07-04 Airplane having flap

Country Status (1)

Country Link
JP (1) JPH0463799A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6970773B2 (en) 2004-03-10 2005-11-29 Utah State University Apparatus and method for reducing induced drag on aircraft and other vehicles
US7883060B2 (en) 2006-12-14 2011-02-08 Utah State University Apparatus and method for twisting a wing to increase lift on aircraft and other vehicles
CN108536175A (en) * 2017-03-06 2018-09-14 陕西飞机工业(集团)有限公司 A kind of flap configuration output mechanism angular adjustment apparatus

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6970773B2 (en) 2004-03-10 2005-11-29 Utah State University Apparatus and method for reducing induced drag on aircraft and other vehicles
US7883060B2 (en) 2006-12-14 2011-02-08 Utah State University Apparatus and method for twisting a wing to increase lift on aircraft and other vehicles
CN108536175A (en) * 2017-03-06 2018-09-14 陕西飞机工业(集团)有限公司 A kind of flap configuration output mechanism angular adjustment apparatus
CN108536175B (en) * 2017-03-06 2019-11-15 陕西飞机工业(集团)有限公司 A kind of flap configuration output mechanism angular adjustment apparatus

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