EP0385878A1 - Steuerungssystem mit im Dauerbetrieb arbeitenden Gasstrahlen für einen Flugkörper - Google Patents

Steuerungssystem mit im Dauerbetrieb arbeitenden Gasstrahlen für einen Flugkörper Download PDF

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Publication number
EP0385878A1
EP0385878A1 EP90400587A EP90400587A EP0385878A1 EP 0385878 A1 EP0385878 A1 EP 0385878A1 EP 90400587 A EP90400587 A EP 90400587A EP 90400587 A EP90400587 A EP 90400587A EP 0385878 A1 EP0385878 A1 EP 0385878A1
Authority
EP
European Patent Office
Prior art keywords
nozzles
axis
vector
nozzle
thrust
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Withdrawn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
EP90400587A
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English (en)
French (fr)
Inventor
Marc Bernard
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.)
Thomson Brandt Armements SA
Original Assignee
Thomson Brandt Armements SA
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 Thomson Brandt Armements SA filed Critical Thomson Brandt Armements SA
Publication of EP0385878A1 publication Critical patent/EP0385878A1/de
Withdrawn legal-status Critical Current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
    • F42B10/66—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 subject of the present invention is a system for guiding a vector using orientable nozzles, supplied continuously by a gas generator.
  • vector is understood here to mean any guided flying machine, whether powered or not.
  • Guidance is also understood to mean, by extension, both guidance of the vector's center of gravity and its steering around its center of gravity.
  • Aerodynamic systems have different limitations due in particular to their complexity, their response time and their variability as a function of the speed of the vector.
  • the first system (impellers) consists of having a set of impellers, each capable of delivering a pulse of pre-established intensity and the duration of which is either continuous or also predefined. This implies that the vector is constantly in rotation around its roll axis or else controlled by a complementary roll system; an alternative solution consists in controlling the block of impellers itself in roll; this need is of course a drawback. In addition, whatever the arrangement and the number of impellers, the number of possible corrections is limited.
  • the switching of jets is in principle discontinuous; the average value of the guiding force is obtained by time modulation, which implies high switching speeds relative to the response time of the vector; these switching speeds are difficult to achieve mechanically.
  • a switch is always a source of mechanical excitations of the structure of the vector.
  • the minimum number of nozzles which allows pitch, yaw and roll to be obtained simultaneously is six, which is high and involves complexity and weight.
  • the last system which consists in orienting the jet of the main propellant of the vector, uses either one or more control surfaces in the flow of hot gas at the level of the diverging part of the nozzle, or means for turning the nozzle (s) themselves.
  • the main limitation of this system is that it requires the presence of a main motor in operation for the duration of the guided phase.
  • the subject of the present invention is a guidance system which makes it possible to avoid the above drawbacks and limitations by the use of a reduced number (three) of continuous gas jets and orientable around an axis substantially parallel to that of the vector. , in one embodiment, and the travel of which can be limited to ⁇ 60 °.
  • the subject of the invention is a system for guiding a vector as defined by claim 1.
  • Figure 1 is therefore an explanatory diagram of the guidance system according to the invention.
  • the outer envelope V of the vector is shown, seen in radial, or transverse section (that is to say section made perpendicular to the longitudinal axis of the vector), and for example in the form of a circle, the trace of the longitudinal axis of the vector being the center O of the circle.
  • the vector is guided by three and only three orientable nozzles, arranged substantially at 120 ° in the same transverse plane (that of the figure), at the periphery of the vector.
  • nozzles are orientable around an axis substantially parallel to the longitudinal axis of the vector, that is to say that, supplied by a gas generator, they are capable of providing a continuous jet of gas substantially in the plane of the figure, in any direction within predefined limits forming the deflection angle of the nozzle.
  • the thrust of each of the nozzles results in forces applied to the vector, marked F1, F2 and F3; the points of application of these forces on the envelope of the vector are marked T1, T2, T3.
  • the force (F1-F3) produced by each of the nozzles makes with the radii OT1, OT2 and OT3 an angle ⁇ 1, ⁇ 2 and ⁇ 3, respectively, which is a function of the orientation of the nozzles.
  • These three forces have a resultant R F which forms an angle ⁇ with a reference radius OX.
  • the value of the maximum roll torque is ⁇ 3 FR for a deflection of ⁇ 90 °.
  • the maximum value of the guide maneuvering force is close to 2.7 F for an angle ⁇ equal to: 1 ⁇ 3 + for an angular displacement of the nozzles of ⁇ 90 °.
  • this force is close to 2F for an angular deflection of the nozzles limited to ⁇ 60 ° and for an angle ⁇ equal to: 1 ⁇ 3 +
  • FIG. 2 schematically represents an embodiment of a steerable nozzle capable of being used in the system according to the invention.
  • a nozzle block 1 terminated by the diverging part 2 of the nozzle; the assembly is capable of a rotational movement about its longitudinal axis ZZ relative to a fixed part 52 using a motor 3, for example electric, via an axis 4; the assembly is held between bearings 50 and 51.
  • the axis of rotation ZZ is preferably arranged as close as possible to the center of thrust, so as to minimize the parasitic torque resulting from a distance between center of thrust and axis of rotation.
  • the gases pass through the nozzle block longitudinally (arrow 10) and are ejected by the divergent (arrow 11), thus giving rise to the thrust F directed along the axis YY of the divergent, that is to say, on the figure, normally at the ZZ axis.
  • each nozzle is not necessarily parallel to the longitudinal axis of the vector. It can make an angle with the latter, from a few degrees up to 45 ° for example, so that the nozzles provide a constant thrust component on the axis of the vector; this allows, for example, to compensate for the aerodynamic drag of the vector or the terrestrial attraction.
  • the axis YY may not be normal to the axis ZZ or the nozzle may not be movable in rotation around its axis ZZ but around a second axis, making an angle with the previous one.
  • the nozzles then provide, in addition to the components useful for guiding in a transverse plane described above, a constant thrust component in the axis of the vector.
  • this system of three nozzles can be arranged in a plane containing or not the center of gravity.
  • the guldage system according to the invention can also be used for a vector in autorotation (roll).
  • all three nozzles are mounted on a more or less free part in rotation relative to the vector, allowing the control of the coupling in roll of the system with the vector.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
EP90400587A 1989-03-03 1990-03-02 Steuerungssystem mit im Dauerbetrieb arbeitenden Gasstrahlen für einen Flugkörper Withdrawn EP0385878A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8902785A FR2643981B1 (fr) 1989-03-03 1989-03-03 Systeme de guidage d'un vecteur par jets de gaz continus
FR8902785 1989-03-03

Publications (1)

Publication Number Publication Date
EP0385878A1 true EP0385878A1 (de) 1990-09-05

Family

ID=9379329

Family Applications (1)

Application Number Title Priority Date Filing Date
EP90400587A Withdrawn EP0385878A1 (de) 1989-03-03 1990-03-02 Steuerungssystem mit im Dauerbetrieb arbeitenden Gasstrahlen für einen Flugkörper

Country Status (4)

Country Link
US (1) US5004184A (de)
EP (1) EP0385878A1 (de)
CA (1) CA2011352A1 (de)
FR (1) FR2643981B1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5679919A (en) * 1993-03-30 1997-10-21 Bofors Ab Method and apparatus for imparting to an airborne warhead a desired pattern of movement

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5273237A (en) * 1992-11-02 1993-12-28 The United States Of America As Represented By The Secretary Of The Air Force Forebody nozzle for aircraft directional control
JP2004306762A (ja) * 2003-04-07 2004-11-04 Mitsubishi Heavy Ind Ltd 三軸姿勢制御用推進装置及びその装置を備えた飛行物体
US8076623B2 (en) * 2009-03-17 2011-12-13 Raytheon Company Projectile control device
FR2997179B1 (fr) * 2012-10-22 2015-01-16 Roxel France Dispositif combine de pilotage de trajectoire et de reduction de trainee.

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3446436A (en) * 1966-11-29 1969-05-27 Thiokol Chemical Corp Rocket thrust nozzle system
US3599899A (en) * 1969-06-20 1971-08-17 Thiokol Chemical Corp Rocket control
FR2501359A1 (fr) * 1981-03-05 1982-09-10 Messerschmitt Boelkow Blohm Missile ou engin guide
DE3108283A1 (de) * 1981-03-05 1982-09-16 Messerschmitt-Bölkow-Blohm GmbH, 8000 München "lenkflugkoerper"
DE3138869A1 (de) * 1981-09-30 1983-04-14 Messerschmitt-Bölkow-Blohm GmbH, 8000 München "lenkflugkoerper"
EP0110774A1 (de) * 1982-11-29 1984-06-13 AEROSPATIALE Société Nationale Industrielle Raketensteuerungsanlage mit seitlichem Gasstrahl
DE3429798C1 (de) * 1984-08-13 1985-12-12 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Vorrichtung zur Korrektur der Flugbahn eines Geschosses
FR2573861A1 (fr) * 1984-11-24 1986-05-30 Messerschmitt Boelkow Blohm Dispositif de guidage de courte duree d'un engin volant au moyen de generateurs de poussee transversale
FR2612289A1 (fr) * 1987-03-14 1988-09-16 Messerschmitt Boelkow Blohm Dispositif pour piloter un engin volant

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3249325A (en) * 1963-03-12 1966-05-03 Oliver C Forehand Missile guidance system
US3573861A (en) * 1969-01-06 1971-04-06 Dawn Donut Co Inc Self-cleaning fryer apparatus
US4017040A (en) * 1976-01-12 1977-04-12 The United States Of America As Represented By The Secretary Of The Navy Steerable extraction rocket
US4384690A (en) * 1981-03-06 1983-05-24 The United States Of America As Represented By The Secretary Of The Navy Thrust vector control for large deflection angles
US4599044A (en) * 1985-01-07 1986-07-08 The United States Of America As Represented By The Secretary Of The Navy Electronic feedback area control system for TVC gas generator
US4913379A (en) * 1988-02-23 1990-04-03 Japan as represented by Director General, Technical Research and Development Institute, Japan Defence Agency Rocket flight direction control system

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3446436A (en) * 1966-11-29 1969-05-27 Thiokol Chemical Corp Rocket thrust nozzle system
US3599899A (en) * 1969-06-20 1971-08-17 Thiokol Chemical Corp Rocket control
FR2501359A1 (fr) * 1981-03-05 1982-09-10 Messerschmitt Boelkow Blohm Missile ou engin guide
DE3108283A1 (de) * 1981-03-05 1982-09-16 Messerschmitt-Bölkow-Blohm GmbH, 8000 München "lenkflugkoerper"
DE3138869A1 (de) * 1981-09-30 1983-04-14 Messerschmitt-Bölkow-Blohm GmbH, 8000 München "lenkflugkoerper"
EP0110774A1 (de) * 1982-11-29 1984-06-13 AEROSPATIALE Société Nationale Industrielle Raketensteuerungsanlage mit seitlichem Gasstrahl
DE3429798C1 (de) * 1984-08-13 1985-12-12 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Vorrichtung zur Korrektur der Flugbahn eines Geschosses
FR2573861A1 (fr) * 1984-11-24 1986-05-30 Messerschmitt Boelkow Blohm Dispositif de guidage de courte duree d'un engin volant au moyen de generateurs de poussee transversale
FR2612289A1 (fr) * 1987-03-14 1988-09-16 Messerschmitt Boelkow Blohm Dispositif pour piloter un engin volant

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5679919A (en) * 1993-03-30 1997-10-21 Bofors Ab Method and apparatus for imparting to an airborne warhead a desired pattern of movement

Also Published As

Publication number Publication date
CA2011352A1 (fr) 1990-09-03
FR2643981A1 (fr) 1990-09-07
FR2643981B1 (fr) 1994-03-11
US5004184A (en) 1991-04-02

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