EP1970664A2 - Commande pour un petit avion - Google Patents

Commande pour un petit avion Download PDF

Info

Publication number: EP1970664A2
Authority: EP; European Patent Office
Prior art keywords: rudder; propeller; small missile; small; fins
Prior art date: 2007-03-16
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)

English (en)

Other versions

EP1970664A3 (fr

EP1970664B1 (fr

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.)

2007-03-16

Filing date

2008-03-05

Publication date

2008-09-17

2008-03-05 Application filed by LFK Lenkflugkoerpersysteme GmbH filed Critical LFK Lenkflugkoerpersysteme GmbH

2008-09-17 Publication of EP1970664A2 publication Critical patent/EP1970664A2/fr

2010-04-14 Publication of EP1970664A3 publication Critical patent/EP1970664A3/fr

2011-12-28 Application granted granted Critical

2011-12-28 Publication of EP1970664B1 publication Critical patent/EP1970664B1/fr

Status Not-in-force legal-status Critical Current

2028-03-05 Anticipated expiration legal-status Critical

Links

Images

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

Definitions

the invention relates to a controller for small missiles, as these come as a supplementary armament for infantrymen, for border guards, anti-terrorist units and the like are used.
Such propeller driven a battery powered electric motor as a drive having small missiles are fired from containers or launch tubes and unfold after the start by means of rowing adjustable with the fuselage wing and tail surfaces to generate torques about the steering and transverse axis of the small missile; see. DE 10 2004 061 977 A1 ,
the design of the control device according to the invention allows in the simplest way an additional thrust vector control of the small missile, wherein the controlling thrust vector is generated by the resulting four or two individual delivered by the structurally coupled with the rudder fins in their angular displacement propellers thrusts that either in their Amount equal or can be individually controlled to generate the necessary control moments on the steering electronics for the purpose of thrust change.
the propellers producing the directional change of the small missile generate the propulsion of the small missile and are each coupled with one rowing fin.
the propeller modules bearing rudder fins can also be arranged separately at the stern or nose of the small missile.
the propulsion modules arranged on the aerodynamic wings of the small missile thus separate powered by the on-board battery electric motors are used; but it can also be derived by a single electric motor by means of a controllable branching gear drive the deflectable propeller.
the propellers associated with the steering fins also provide propulsion for the small missile, which simplifies their construction.
a four crosswise on a fuselage structure 10 (see. FIGS. 1 and 2 ) hinged aerodynamic surfaces 11, 12, 13 and 14 having small missile 15 has on the surfaces 11 to 14 hinged rudder fins 16 to 19, of which in FIG. 1 only the rudder fin 16 is shown.
propeller With each rudder fin driven by a battery-powered electric motor, not shown propeller is connected and forms with this in each case a propeller module M1 to M4.
the small missile which has been launched from a starting frame, not shown, is controlled in its cruise phase via a steering electronics along the desired trajectory.
the rudder fins and the associated propeller modules whose speeds and thus their thrust vectors are remotely controlled individually.
the effective thrust vector is generated by the resultant of the four individual thrust vectors of the propeller modules M1 to M4, which are either equal in their amount or can be individually controlled differently.
a rapid and effective change in direction of the small missile is achieved by changing the thrust vector even at low flow velocities of the rudder fins.
the rudder fins instead of the aerodynamic surfaces 11 to 14 as a separate rudder near the tail 20 of the small missile 15 - for example, at 22 - or near the fuselage tip - for example 23 - be arranged.

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)

EP08004057A 2007-03-16 2008-03-05 Commande pour un avion de taille réduite Not-in-force EP1970664B1 (fr)

Applications Claiming Priority (1)

Application Number	Priority Date	Filing Date	Title
DE102007012799A DE102007012799B3 (de)	2007-03-16	2007-03-16	Steuerung für einen Kleinflugkörper

Publications (3)

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

Family

ID=39244667

Family Applications (1)

Application Number	Title	Priority Date	Filing Date
EP08004057A Not-in-force EP1970664B1 (fr)	2007-03-16	2008-03-05	Commande pour un avion de taille réduite

Country Status (3)

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

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
CN104699918A (zh) *	2015-03-27	2015-06-10	北京润科通用技术有限公司	一种计算舵偏角的方法及***
CN113720216A (zh) *	2021-06-10	2021-11-30	北京星途探索科技有限公司	一种尾舱及舵控传动机构

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
DE102011015780A1 (de)	2011-04-01	2012-10-04	Lfk-Lenkflugkörpersysteme Gmbh	Kleinflugkörper
DE102014010109A1 (de)	2014-07-08	2016-01-14	Mbda Deutschland Gmbh	Flugkörper

Citations (2)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
DE10322421A1 (de)	2003-05-16	2004-12-09	Electrolux Home Products Corporation N.V.	Verfahren zum Reinigen von Geschirr in Geschirrspülmaschinen unter Verwendung einer automatischen Dosiervorrichtung mit Mehrfachdosierung und Geschirrspülmaschine zur Durchführung des Verfahrens
DE102004061977A1 (de)	2004-12-23	2006-07-06	Lfk-Lenkflugkörpersysteme Gmbh	Klein-Flugkörper

Family Cites Families (2)

* 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 (de) *	2003-05-16	2004-12-02	Paul Schreiber	Flugzeug

2007
- 2007-03-16 DE DE102007012799A patent/DE102007012799B3/de not_active Expired - Fee Related
2008
- 2008-03-05 EP EP08004057A patent/EP1970664B1/fr not_active Not-in-force
- 2008-03-05 AT AT08004057T patent/ATE539312T1/de active

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
DE10322421A1 (de)	2003-05-16	2004-12-09	Electrolux Home Products Corporation N.V.	Verfahren zum Reinigen von Geschirr in Geschirrspülmaschinen unter Verwendung einer automatischen Dosiervorrichtung mit Mehrfachdosierung und Geschirrspülmaschine zur Durchführung des Verfahrens
DE102004061977A1 (de)	2004-12-23	2006-07-06	Lfk-Lenkflugkörpersysteme Gmbh	Klein-Flugkörper

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
CN104699918A (zh) *	2015-03-27	2015-06-10	北京润科通用技术有限公司	一种计算舵偏角的方法及***
CN104699918B (zh) *	2015-03-27	2017-08-11	北京润科通用技术有限公司	一种计算舵偏角的方法及***
CN113720216A (zh) *	2021-06-10	2021-11-30	北京星途探索科技有限公司	一种尾舱及舵控传动机构

Also Published As

Publication number	Publication date
DE102007012799B3 (de)	2008-04-30
ATE539312T1 (de)	2012-01-15
EP1970664A3 (fr)	2010-04-14
EP1970664B1 (fr)	2011-12-28

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