CA2325763A1 - Procedure to reduce the pressure and temperature on the front of a missile at ultrasonic speed - Google Patents

Procedure to reduce the pressure and temperature on the front of a missile at ultrasonic speed Download PDF

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Publication number
CA2325763A1
CA2325763A1 CA002325763A CA2325763A CA2325763A1 CA 2325763 A1 CA2325763 A1 CA 2325763A1 CA 002325763 A CA002325763 A CA 002325763A CA 2325763 A CA2325763 A CA 2325763A CA 2325763 A1 CA2325763 A1 CA 2325763A1
Authority
CA
Canada
Prior art keywords
missile
temperature
pressure
procedure
reduce
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
CA002325763A
Other languages
French (fr)
Other versions
CA2325763C (en
Inventor
Kay Runne
Julio Srulijes
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.)
LFK Lenkflugkoerpersysteme GmbH
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of CA2325763A1 publication Critical patent/CA2325763A1/en
Application granted granted Critical
Publication of CA2325763C publication Critical patent/CA2325763C/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/38—Range-increasing arrangements
    • F42B10/42—Streamlined projectiles
    • F42B10/46—Streamlined nose cones; Windshields; Radomes

Abstract

A procedure is suggested to reduce pressure and temperature on the front of a missile at ultrasonic speed whereby a spike with a spherical, ellipsoidal, or drop-shaped mount is used on the front end. In contrast to conventional shapes, the sensitive nose of the missile is protected from damaging pressure and temperature, even at high angles of incidence. This makes it possible to create missiles that are highly manoeuvrable at high ultrasonic speeds without high pressures and temperatures arising at the front. The resistance and hence the required thrust of such a missile is strongly reduced when the invention is used which correspondingly increases the range and flight duration of such a missile.
CA002325763A 1999-11-08 2000-11-02 Procedure to reduce the pressure and temperature on the front of a missile at ultrasonic speed Expired - Fee Related CA2325763C (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19953701A DE19953701C2 (en) 1999-11-08 1999-11-08 Methods and devices for reducing pressure and temperature on the front of a missile at supersonic speeds
DE19953701.1 1999-11-08

Publications (2)

Publication Number Publication Date
CA2325763A1 true CA2325763A1 (en) 2001-05-08
CA2325763C CA2325763C (en) 2008-08-12

Family

ID=7928307

Family Applications (1)

Application Number Title Priority Date Filing Date
CA002325763A Expired - Fee Related CA2325763C (en) 1999-11-08 2000-11-02 Procedure to reduce the pressure and temperature on the front of a missile at ultrasonic speed

Country Status (4)

Country Link
US (1) US6581870B1 (en)
JP (1) JP2001174200A (en)
CA (1) CA2325763C (en)
DE (1) DE19953701C2 (en)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10305973B3 (en) * 2003-02-13 2004-05-06 Deutsches Zentrum für Luft- und Raumfahrt e.V. Loss reduction device for compression shock includes at least one shock-inducing body spaced out from surface in supersonic flow region
JP4070215B2 (en) * 2005-07-13 2008-04-02 独立行政法人 宇宙航空研究開発機構 Flying object
DE102006003638B4 (en) 2006-01-26 2008-01-17 Deutsches Zentrum für Luft- und Raumfahrt e.V. Missile for the supersonic range
DE102006015952B4 (en) * 2006-04-05 2008-01-17 Deutsches Zentrum für Luft- und Raumfahrt e.V. Missile for the supersonic range
DE102006025270B4 (en) 2006-05-31 2008-04-03 Deutsches Zentrum für Luft- und Raumfahrt e.V. Missile for the supersonic range
CN100423989C (en) * 2006-12-27 2008-10-08 中国科学院力学研究所 Ablation-free self-adaptive heat-resistant and damping system for high supersonic aerocraft
CN100423990C (en) * 2006-12-27 2008-10-08 中国科学院力学研究所 Reverse pulse explosion heat-resistant and damping method for high supersonic aerocraft
DE102006061709B3 (en) * 2006-12-28 2008-05-29 Deutsches Zentrum für Luft- und Raumfahrt e.V. Missile e.g. guided missile, for use with aircraft or combat aircraft, has aero-spike that extends from front face surface, where aero-spike has front body i.e. aero-disk, formed with porous material, whose open pores form flow channels
US8686326B1 (en) * 2008-03-26 2014-04-01 Arete Associates Optical-flow techniques for improved terminal homing and control
DE102009001953B4 (en) * 2009-03-27 2013-11-14 Deutsches Zentrum für Luft- und Raumfahrt e.V. Device for influencing a supersonic flow around
WO2014008549A1 (en) * 2012-07-11 2014-01-16 The University Of Southern Queensland An aerolance system
CN110641727A (en) * 2019-11-06 2020-01-03 北京空间技术研制试验中心 Design method of shock wave rod device mounted on head of supersonic aircraft

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3128964A (en) * 1964-04-14 figures
US2980370A (en) * 1957-07-09 1961-04-18 Takacs Francisco Flying body for supersonic speed
US3424400A (en) * 1965-06-25 1969-01-28 John P Le Bel Sonic boom and shock wave eliminator
US3497163A (en) * 1966-05-24 1970-02-24 George H Wakefield Supersonic aircraft
US3425650A (en) * 1967-10-02 1969-02-04 Joseph Silva Air deflector for supersonic aircraft
US3643901A (en) * 1970-05-27 1972-02-22 Isidor C Patapis Ducted spike diffuser
US4650139A (en) * 1984-07-31 1987-03-17 Taylor Thomas C Aerospike for attachment to space vehicle system
DE3807725A1 (en) * 1988-03-09 1989-09-21 Bodenseewerk Geraetetech END PHASE STEERED BULLET
JPH0560498A (en) * 1991-08-29 1993-03-09 Mitsubishi Heavy Ind Ltd Rain errosion preventing device
JP2973688B2 (en) * 1992-03-11 1999-11-08 日産自動車株式会社 Aerodynamic heating protection device for flying objects
JP3614977B2 (en) * 1996-05-02 2005-01-26 株式会社東芝 Specific part recognition device for flying objects

Also Published As

Publication number Publication date
US6581870B1 (en) 2003-06-24
JP2001174200A (en) 2001-06-29
CA2325763C (en) 2008-08-12
DE19953701A1 (en) 2001-05-23
DE19953701C2 (en) 2002-01-24

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Legal Events

Date Code Title Description
EEER Examination request
MKLA Lapsed

Effective date: 20151102