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GB2060078A - Flight Stabilization of Rocket Propelled Missiles - Google Patents

Flight Stabilization of Rocket Propelled Missiles Download PDF

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Publication number
GB2060078A
GB2060078A GB7935085A GB7935085A GB2060078A GB 2060078 A GB2060078 A GB 2060078A GB 7935085 A GB7935085 A GB 7935085A GB 7935085 A GB7935085 A GB 7935085A GB 2060078 A GB2060078 A GB 2060078A
Authority
GB
United Kingdom
Prior art keywords
rocket
missiles
fins
section
exhaust nozzle
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Withdrawn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
GB7935085A
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.)
FRANCE E
Original Assignee
FRANCE E
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 FRANCE E filed Critical FRANCE E
Priority to GB7935085A priority Critical patent/GB2060078A/en
Publication of GB2060078A publication Critical patent/GB2060078A/en
Withdrawn legal-status Critical Current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
    • F42B10/02—Stabilising arrangements
    • F42B10/26—Stabilising arrangements using spin
    • F42B10/28—Stabilising arrangements using spin induced by gas action
    • F42B10/30—Stabilising arrangements using spin induced by gas action using rocket motor nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/97—Rocket nozzles

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

To maintain flight stability of a rocket powered missile the gas passing through the exhaust nozzle is caused to flow spirally by means of internal fins or rifling or by forming the nozzle with a non-circular internal cross-section twisted helically.

Description

SPECIFICATION Flight Stabilization of Rocket Propelled Missiles The object of this invention is to stabilize the flight of rocket propelled missiles. The invention applies to missiles which have no control systems. It is common practice to provide missiles of this type with external stabilizing fins. The present invention dispenses with the use of external fins. Flight stability is attained by spinning missiles in a manner similar to the spinning of projectiles shot from rifled gun barrels.
Kinetic energy of gases flowing from rocket thrust chambers is used to provide forces to cause spinning. Gases flowing through rocket exhaust nozzles, or flowing aft of rocket exhaust nozzles, are deviated toward a spiral course, inducing torque reaction. Means by which gas flow is deviated are described in the following examples.
A rocket propelled missile has an exhaust nozzle provided with fins situated either, internally, or aft of the gas exit. The fins have proportions and profiles suitable to the gas velocities produced from the rocket motor. The fins are set at angles of incidence needed to deviate the gases to flow spirally.
A rocket propelled missile has an exhaust nozzle which is rifled, with grooves of suitable proportions to deviate the gases to flow spirally.
A rocket propelled missile wherein a portion of the length of the exhaust nozzle has a bore of non-circular cross section. (As an example the cross section may be elliptical.) The non-circular portion of the bore is twisted around the centroid of the cross section, maintaining constant alignment with the thrust centre-line of the rocket motor. Gases passing through the twisted portion of the exhaust nozzle are deviated to flow spirally.
Claims
1. A rocket motor exhaust nozzle of non circuiar internal cross-section, twisted helically.
The centroid of the cross-section coincides with the centre line of thrust of the rocket.
Amendments to Claims filed on 19th December 1980.
Amended Claims: Claims 2 and 3 deleted.
**WARNING** end of DESC field may overlap start of CLMS **.

Claims (1)

  1. **WARNING** start of CLMS field may overlap end of DESC **.
    SPECIFICATION Flight Stabilization of Rocket Propelled Missiles The object of this invention is to stabilize the flight of rocket propelled missiles. The invention applies to missiles which have no control systems. It is common practice to provide missiles of this type with external stabilizing fins. The present invention dispenses with the use of external fins. Flight stability is attained by spinning missiles in a manner similar to the spinning of projectiles shot from rifled gun barrels.
    Kinetic energy of gases flowing from rocket thrust chambers is used to provide forces to cause spinning. Gases flowing through rocket exhaust nozzles, or flowing aft of rocket exhaust nozzles, are deviated toward a spiral course, inducing torque reaction. Means by which gas flow is deviated are described in the following examples.
    A rocket propelled missile has an exhaust nozzle provided with fins situated either, internally, or aft of the gas exit. The fins have proportions and profiles suitable to the gas velocities produced from the rocket motor. The fins are set at angles of incidence needed to deviate the gases to flow spirally.
    A rocket propelled missile has an exhaust nozzle which is rifled, with grooves of suitable proportions to deviate the gases to flow spirally.
    A rocket propelled missile wherein a portion of the length of the exhaust nozzle has a bore of non-circular cross section. (As an example the cross section may be elliptical.) The non-circular portion of the bore is twisted around the centroid of the cross section, maintaining constant alignment with the thrust centre-line of the rocket motor. Gases passing through the twisted portion of the exhaust nozzle are deviated to flow spirally.
    Claims
    1. A rocket motor exhaust nozzle of non circuiar internal cross-section, twisted helically.
    The centroid of the cross-section coincides with the centre line of thrust of the rocket.
    Amendments to Claims filed on 19th December 1980.
    Amended Claims: Claims 2 and 3 deleted.
GB7935085A 1979-10-10 1979-10-10 Flight Stabilization of Rocket Propelled Missiles Withdrawn GB2060078A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB7935085A GB2060078A (en) 1979-10-10 1979-10-10 Flight Stabilization of Rocket Propelled Missiles

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB7935085A GB2060078A (en) 1979-10-10 1979-10-10 Flight Stabilization of Rocket Propelled Missiles

Publications (1)

Publication Number Publication Date
GB2060078A true GB2060078A (en) 1981-04-29

Family

ID=10508400

Family Applications (1)

Application Number Title Priority Date Filing Date
GB7935085A Withdrawn GB2060078A (en) 1979-10-10 1979-10-10 Flight Stabilization of Rocket Propelled Missiles

Country Status (1)

Country Link
GB (1) GB2060078A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1999046499A1 (en) * 1998-03-10 1999-09-16 Tsai, Artur Rifled jet nozzle
US6450443B1 (en) * 2000-08-17 2002-09-17 The United States Of America As Represented By The Secretary Of The Navy High torque 2.75-inch rocket nozzle
US7229029B2 (en) 2002-10-29 2007-06-12 Phisser Technologies, Inc. Propulsion system

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1999046499A1 (en) * 1998-03-10 1999-09-16 Tsai, Artur Rifled jet nozzle
US6450443B1 (en) * 2000-08-17 2002-09-17 The United States Of America As Represented By The Secretary Of The Navy High torque 2.75-inch rocket nozzle
US7229029B2 (en) 2002-10-29 2007-06-12 Phisser Technologies, Inc. Propulsion system

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Legal Events

Date Code Title Description
WAP Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1)