EP3136042A3 - Wing assembly and missile with wing assembly - Google Patents

Wing assembly and missile with wing assembly Download PDF

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Publication number
EP3136042A3
EP3136042A3 EP16001708.3A EP16001708A EP3136042A3 EP 3136042 A3 EP3136042 A3 EP 3136042A3 EP 16001708 A EP16001708 A EP 16001708A EP 3136042 A3 EP3136042 A3 EP 3136042A3
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EP
European Patent Office
Prior art keywords
missile
wing assembly
support surface
actuator
interior
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.)
Withdrawn
Application number
EP16001708.3A
Other languages
German (de)
French (fr)
Other versions
EP3136042A2 (en
Inventor
Peter Gerd Fisch
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.)
Diehl Defence GmbH and Co KG
Original Assignee
Diehl Defence GmbH and Co KG
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
Priority claimed from DE102015014794.3A external-priority patent/DE102015014794A1/en
Application filed by Diehl Defence GmbH and Co KG filed Critical Diehl Defence GmbH and Co KG
Publication of EP3136042A2 publication Critical patent/EP3136042A2/en
Publication of EP3136042A3 publication Critical patent/EP3136042A3/en
Withdrawn legal-status Critical Current

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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

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Transmission Devices (AREA)

Abstract

Die Erfindung betrifft eine Flügelanordnung (12, 12', 12") für einen Flugkörper (2, 2', 2") umfassend eine Tragfläche (14, 14', 14") mit einer daran befestigten Steuerfläche (16), die durch einen Stellantrieb (28, 28', 28", 50) um eine sich mit der Flugkörperlängsachse (20, 20', 20") unter einem Winkel schneidenden oder dazu parallel verlaufenden Achse (18) auslenkbar ist, wobei der Stellantrieb (28, 28', 28", 50) in einem Innenraum (26, 26', 26") der Tragfläche (14, 14', 14") angeordnet ist und mit einem Ansteuerelement (38) verbunden ist, das teilweise im Innenraum (26, 26', 26") der Tragfläche (14, 14', 14") angeordnet ist und mit einem mit der Steuerfläche (16) fest verbundenen Hebelmittel (36) verbunden ist.The invention relates to a wing arrangement (12, 12 ', 12 ") for a missile (2, 2', 2") comprising a support surface (14, 14 ', 14 ") with a control surface (16) attached thereto, which is guided by a Actuator (28, 28 ', 28 ", 50) about a with the missile longitudinal axis (20, 20', 20") at an angle intersecting or parallel to the axis (18) is deflectable, wherein the actuator (28, 28 ' , 28 ", 50) in an interior (26, 26 ', 26") of the support surface (14, 14', 14 ") is arranged and connected to a drive element (38) which partially in the interior (26, 26 ' , 26 ") of the support surface (14, 14 ', 14") is arranged and with a with the control surface (16) fixedly connected to the lever means (36) is connected.

Weiterhin betrifft die Erfindung einen Flugkörper (2, 2', 2") mit zumindest einer solchen Flügelanordnung (12, 12', 12").

Figure imgaf001
Furthermore, the invention relates to a missile (2, 2 ', 2 ") with at least one such wing arrangement (12, 12', 12").
Figure imgaf001
EP16001708.3A 2015-08-25 2016-08-02 Wing assembly and missile with wing assembly Withdrawn EP3136042A3 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102015010881 2015-08-25
DE102015014794.3A DE102015014794A1 (en) 2015-08-25 2015-11-14 Wing arrangement and missile with wing arrangement

Publications (2)

Publication Number Publication Date
EP3136042A2 EP3136042A2 (en) 2017-03-01
EP3136042A3 true EP3136042A3 (en) 2017-04-26

Family

ID=56571103

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16001708.3A Withdrawn EP3136042A3 (en) 2015-08-25 2016-08-02 Wing assembly and missile with wing assembly

Country Status (1)

Country Link
EP (1) EP3136042A3 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115057000B (en) * 2022-08-16 2022-11-01 中国空气动力研究与发展中心空天技术研究所 Zero calibration device and calibration method for hypersonic aircraft air rudder system

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB582840A (en) * 1939-04-19 1946-11-29 Charles Dennistoun Burney Improvements in or relating to marine torpedoes launched from aircraft
US5141175A (en) * 1991-03-22 1992-08-25 Harris Gordon L Air launched munition range extension system and method
US20100282917A1 (en) * 2006-02-16 2010-11-11 O'shea Hank Aerial vehicle with variable aspect ratio deployable wings

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB582840A (en) * 1939-04-19 1946-11-29 Charles Dennistoun Burney Improvements in or relating to marine torpedoes launched from aircraft
US5141175A (en) * 1991-03-22 1992-08-25 Harris Gordon L Air launched munition range extension system and method
US20100282917A1 (en) * 2006-02-16 2010-11-11 O'shea Hank Aerial vehicle with variable aspect ratio deployable wings

Also Published As

Publication number Publication date
EP3136042A2 (en) 2017-03-01

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