EP1970664A3 - Control for a miniature aircraft - Google Patents

Control for a miniature aircraft Download PDF

Info

Publication number
EP1970664A3
EP1970664A3 EP08004057A EP08004057A EP1970664A3 EP 1970664 A3 EP1970664 A3 EP 1970664A3 EP 08004057 A EP08004057 A EP 08004057A EP 08004057 A EP08004057 A EP 08004057A EP 1970664 A3 EP1970664 A3 EP 1970664A3
Authority
EP
European Patent Office
Prior art keywords
rudder
small missile
propeller
wings
fins
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
EP08004057A
Other languages
German (de)
French (fr)
Other versions
EP1970664B1 (en
EP1970664A2 (en
Inventor
Michael Alois Surauer
Franz Maier
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.)
MBDA Deutschland GmbH
Original Assignee
LFK Lenkflugkoerpersysteme GmbH
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 LFK Lenkflugkoerpersysteme GmbH filed Critical LFK Lenkflugkoerpersysteme GmbH
Publication of EP1970664A2 publication Critical patent/EP1970664A2/en
Publication of EP1970664A3 publication Critical patent/EP1970664A3/en
Application granted granted Critical
Publication of EP1970664B1 publication Critical patent/EP1970664B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/60—Steering arrangements
    • F42B10/62—Steering by movement of flight surfaces
    • F42B10/64—Steering by movement of flight surfaces of fins
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/60—Steering arrangements
    • F42B10/66—Steering by varying intensity or direction of thrust
    • F42B10/666—Steering by varying intensity or direction of thrust characterised by using a nozzle rotatable about an axis transverse to the axis of the projectile

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Toys (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Abstract

The control device for the production of torques around the longitudinal and transverse axis of a small missile (15) driven over a steering electronics by propellers, comprises wings (11, 12, 13, 14) having aerodynamic flight stabilization rudder-fin (16). The rudder fins are arranged in their number of revolutions over the steering electronics influenceable in their angle of deflection with propeller modules (M1) coupled to the rudder fins. The propeller modules supply the controllable propulsion for the small missile and are directly arranged at the wings. The control device for the production of torques around the longitudinal and transverse axis of a small missile (15) driven over a steering electronics by propellers, comprises wings (11, 12, 13, 14) having aerodynamic flight stabilization rudder-fin (16). The rudder fins are arranged in their number of revolutions over the steering electronics influenceable in their angle of deflection with propeller modules (M1) coupled to the rudder fins. The propeller modules supply the controllable propulsion for the small missile and are directly arranged at the wings. The propeller comprises electric motors fed by the main battery of the small missile. The propeller modules supporting the rudder fins are arranged at a tail or nose of the small missile forming control surfaces (22, 23).
EP08004057A 2007-03-16 2008-03-05 Control for a miniature aircraft Not-in-force EP1970664B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102007012799A DE102007012799B3 (en) 2007-03-16 2007-03-16 Control device for the production of torques around a longitudinal and transverse axis of a small missile driven over a steering electronics by propellers, comprises wings having an aerodynamic flight stabilization rudder-fin

Publications (3)

Publication Number Publication Date
EP1970664A2 EP1970664A2 (en) 2008-09-17
EP1970664A3 true EP1970664A3 (en) 2010-04-14
EP1970664B1 EP1970664B1 (en) 2011-12-28

Family

ID=39244667

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08004057A Not-in-force EP1970664B1 (en) 2007-03-16 2008-03-05 Control for a miniature aircraft

Country Status (3)

Country Link
EP (1) EP1970664B1 (en)
AT (1) ATE539312T1 (en)
DE (1) DE102007012799B3 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102011015780A1 (en) 2011-04-01 2012-10-04 Lfk-Lenkflugkörpersysteme Gmbh Small aircraft
DE102014010109A1 (en) 2014-07-08 2016-01-14 Mbda Deutschland Gmbh missile
CN104699918B (en) * 2015-03-27 2017-08-11 北京润科通用技术有限公司 A kind of method and system for calculating angle of rudder reflection
CN113720216A (en) * 2021-06-10 2021-11-30 北京星途探索科技有限公司 Tail cabin and rudder-controlled transmission mechanism

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5322243A (en) * 1992-06-25 1994-06-21 Northrop Corporation Separately banking maneuvering aerodynamic control surfaces, system and method
DE10322412A1 (en) * 2003-05-16 2004-12-02 Paul Schreiber Tailless aircraft, has no elevator or rudder and thrust path is adjustable relative to fuselage
DE102004061977A1 (en) * 2004-12-23 2006-07-06 Lfk-Lenkflugkörpersysteme Gmbh Small Missile

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10322421A1 (en) 2003-05-16 2004-12-09 Electrolux Home Products Corporation N.V. Method for dispensing products in a dish washing machine from a multi-compartment dispensing unit in the minimum quantities required has a fuzzy logic control system

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5322243A (en) * 1992-06-25 1994-06-21 Northrop Corporation Separately banking maneuvering aerodynamic control surfaces, system and method
DE10322412A1 (en) * 2003-05-16 2004-12-02 Paul Schreiber Tailless aircraft, has no elevator or rudder and thrust path is adjustable relative to fuselage
DE102004061977A1 (en) * 2004-12-23 2006-07-06 Lfk-Lenkflugkörpersysteme Gmbh Small Missile

Also Published As

Publication number Publication date
DE102007012799B3 (en) 2008-04-30
EP1970664B1 (en) 2011-12-28
EP1970664A2 (en) 2008-09-17
ATE539312T1 (en) 2012-01-15

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