CA2499956C - Conception d'un mecanisme de deploiement - Google Patents

Conception d'un mecanisme de deploiement Download PDF

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Publication number
CA2499956C
CA2499956C CA002499956A CA2499956A CA2499956C CA 2499956 C CA2499956 C CA 2499956C CA 002499956 A CA002499956 A CA 002499956A CA 2499956 A CA2499956 A CA 2499956A CA 2499956 C CA2499956 C CA 2499956C
Authority
CA
Canada
Prior art keywords
flight surface
rotation
angle
axes
axis
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.)
Expired - Fee Related
Application number
CA002499956A
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English (en)
Other versions
CA2499956A1 (fr
Inventor
Rudolph A. Eisentraut
Edgar R. Melkers
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.)
Raytheon Co
Original Assignee
Raytheon Co
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 Raytheon Co filed Critical Raytheon Co
Publication of CA2499956A1 publication Critical patent/CA2499956A1/fr
Application granted granted Critical
Publication of CA2499956C publication Critical patent/CA2499956C/fr
Anticipated expiration legal-status Critical
Expired - Fee Related 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
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel

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

Abstract

La présente invention concerne un méthode de conception d'un mécanisme de déploiement pour une surface portante sur un corps aéroporté. Cette méthode consiste à déterminer une position d'arrimage de la surface portante ; déterminer une position déployée de la surface portante ; identifier un premier axe de rotation et un premier angle de rotation correspondant, et un second axe de rotation et un angle de rotation correspondant, selon lesquels la surface portante peut pivoter séquentiellement pour passer de la position d'arrimage à la position de déploiement, ou vice versa ; et utiliser les premiers et seconds axes de rotation et angles de rotation pour déterminer une axe et un angle de rotation équivalents uniques autour desquels et selon lesquels la surface portante peut passer par rotation de la position d'arrimage à la position de déploiement, ou vice versa.
CA002499956A 2002-11-18 2002-11-18 Conception d'un mecanisme de deploiement Expired - Fee Related CA2499956C (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2002/036850 WO2004046636A1 (fr) 2002-11-18 2002-11-18 Conception d'un mecanisme de deploiement

Publications (2)

Publication Number Publication Date
CA2499956A1 CA2499956A1 (fr) 2004-06-03
CA2499956C true CA2499956C (fr) 2009-02-03

Family

ID=32323534

Family Applications (1)

Application Number Title Priority Date Filing Date
CA002499956A Expired - Fee Related CA2499956C (fr) 2002-11-18 2002-11-18 Conception d'un mecanisme de deploiement

Country Status (3)

Country Link
AU (1) AU2002346422A1 (fr)
CA (1) CA2499956C (fr)
WO (1) WO2004046636A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2916268B1 (fr) * 2007-05-15 2010-09-10 Saint Louis Inst Projectile et procede de pilotage associe

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3127838A (en) * 1960-10-12 1964-04-07 Bombrini Parodi Delfino Spa Retractable blade tail unit for projectiles
US3327539A (en) * 1963-05-03 1967-06-27 Kollsman Instr Corp Inertial reference platform
US4664339A (en) * 1984-10-11 1987-05-12 The Boeing Company Missile appendage deployment mechanism
FR2623898B1 (fr) * 1987-11-26 1990-03-23 France Etat Armement Dispositif de deploiement d'une ailette de projectile
US5172323A (en) * 1989-06-22 1992-12-15 The United States Of America As Represented By The Secretary Of The Navy Apparatus for determining the attitude of a vehicle
FR2663731B1 (fr) * 1990-06-21 1992-09-11 Stauff Emile Systeme d'asservissement pour projectile en auto-rotation.
US5192037A (en) * 1991-08-23 1993-03-09 Mcdonnell Douglas Corporation Double-pivoting deployment system for aerosurfaces

Also Published As

Publication number Publication date
CA2499956A1 (fr) 2004-06-03
AU2002346422A1 (en) 2004-06-15
WO2004046636A1 (fr) 2004-06-03

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Effective date: 20141118