EP1767894A1 - Im Innern eines Flugkörpers angebrachte, mittels Niederspannungen Plasmaentladungen erzeugende Vorrichtung zur Steuerung eines supersonischen oder hypersonischen Flugkörpers - Google Patents

Im Innern eines Flugkörpers angebrachte, mittels Niederspannungen Plasmaentladungen erzeugende Vorrichtung zur Steuerung eines supersonischen oder hypersonischen Flugkörpers Download PDF

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Publication number
EP1767894A1
EP1767894A1 EP06291486A EP06291486A EP1767894A1 EP 1767894 A1 EP1767894 A1 EP 1767894A1 EP 06291486 A EP06291486 A EP 06291486A EP 06291486 A EP06291486 A EP 06291486A EP 1767894 A1 EP1767894 A1 EP 1767894A1
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Prior art keywords
plasma
voltage
electrodes
projectile
generating
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EP06291486A
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English (en)
French (fr)
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EP1767894B1 (de
Inventor
Patrick Gnemmi
Christian Rey
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Institut Franco Allemand de Recherches de Saint Louis ISL
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Institut Franco Allemand de Recherches de Saint Louis ISL
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    • 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
    • F42B10/668—Injection of a fluid, e.g. a propellant, into the gas shear in a nozzle or in the boundary layer at the outer surface of a missile, e.g. to create a shock wave in a supersonic flow

Definitions

  • the present invention relates in particular to the field of arrangements for guiding or piloting self-propelled or non-propelled projectiles or missiles, and relates to a method, as well as an associated device, for controlling a projectile, such as, for example, that a shell, bullet or missile, commonly known as a craft.
  • the piloting of a flying machine in the thermosphere can be done with a plasma accelerator (plasma thruster) as described in the patent US3151259 .
  • Steering a flying craft in the atmosphere, that is to say in the troposphere can be performed, for example, by the deployment of airfoils or by the operation of a pyrotechnic device.
  • FR0212906 which describes a method for deflecting a hypervelocity projectile in a Y direction, such as, for example, a shell, bullet or missile, having a generally cone-shaped nose having a more or less pointed end, characterized in that that it consists in performing a plasma discharge on a limited sector of the external surface of the nose and on the side of the direction Y.
  • This patent application also describes a device for implementing this method comprising a triggered spark gap, two electrodes and a high voltage generator.
  • FIG 1 shows the breakdown voltage Vd between two planar electrodes 1 cm apart (d) placed in a chamber containing nitrogen, depending on the pressure p.
  • the breakdown voltage is the minimum voltage whose application causes a disruption between the electrodes; at the end of the disruption, an arc is formed which becomes a conductive medium joining the electrodes.
  • Vd obeys Paschen's law, it is only a function of the product of pressure p of the middle by the inter-electrode distance d.
  • the curve deviates from this law. Indeed, the voltages are high enough for the electric field on the surface of the electrodes to tear electrons.
  • Part I corresponds to the vacuum in which the plasma thrusters work; in this part, Vd is practically independent of the product pd
  • the aim of the invention is to solve these drawbacks by proposing a method of piloting a hypervelocity projectile, that is to say one whose speed is greater than the speed of sound, having no moving part, which can be implemented as many times as necessary and making it possible to generate a plasma for a sufficient duration without requiring an oversizing of the voltage generator.
  • the solution provided is a method of deflecting in a Y direction a hypervelocity projectile evolving in a gas, such as, for example, a shell, bullet or missile, having a nose, generally cone-shaped having a longer end or less pointed, characterized in that it consists in generating a first high voltage discharge capable of producing a plasma on a first limited sector of the surface of the projectile and on the Y direction side and then maintaining this plasma and generating another low voltage discharge capable of supplying said plasma with energy on a second limited sector of the surface of the projectile and on the Y direction side, these sectors being different and possibly or not having a common part.
  • a gas such as, for example, a shell, bullet or missile
  • the maintenance or the increase of the plasma ionization on the second sector will be called plasma energy supply in the following.
  • the supply of the energy plasma to the second sector is carried out for at least one millisecond.
  • the first step consists in carrying out at least a first voltage discharge T1 between at least a first and a second electrode (A; B) delimiting the first limited sector of the surface of the projectile and on the directional side. Y, this discharge being able to break the dielectric barrier between the two electrodes (A; B), then to apply a voltage T3 between the same two electrodes (A; B) capable of generating a plasma, and to apply a voltage T2 between at least two electrodes (B; C) delimiting the second limited sector of the outer surface of the projectile and the Y direction side, this voltage being able to supply said plasma with energy.
  • said at least one voltage discharge T2 applied between said at least two electrodes (B; C) delimiting the second sector and able to supply the plasma with energy is generated on a sector, at least in part, farther from the end of the nose than the first sector.
  • said first voltage discharge T1 consists of a discharge of a high voltage level and low energy, ie less than the deciJoule.
  • the low energy plasma generated on the first sector serves as a contactor on the second sector where a high energy plasma is obtained.
  • a method according to the invention comprises an additional step consisting, after having generated said plasma on the first sector, to maintain this plasma on this first sector, preferably with at least one low voltage voltage discharge T3.
  • said at least one second voltage discharge T2 consists of a discharge of a low voltage level and medium energy, namely greater than Joule.
  • the first step consists in generating at least a first high-voltage discharge of at least 5kV capable of breaking the dielectric barrier present between said at least first and second electrodes (Paschen's law) to generate a plasma and the second step in at least a second low voltage discharge of less than 1000V able to supply said plasma with energy.
  • a method according to the invention consists of a single first high voltage discharge and several successive discharges of low voltage.
  • a method according to the invention consists in generating a plasma on a first limited sector of the nose of the projectile and in supplying this plasma with energy on a second limited sector of the nose of the projectile.
  • the invention also relates to a device for controlling a hypervelocity projectile, such as, for example, a shell, a bullet or a missile, having a nose, generally cone-shaped, having a more or less pointed end and characterized in that it comprises at least one group of at least three electrodes disposed at the outer surface of the projectile and, preferably, of which at least a first and a second electrode delimit between them a first sector and are connected to first means capable of generating a plasma between them and at least one third electrode being, with a fourth or with one of the first and second electrodes, connected to second means able to supply said plasma with energy, and defining between them a second sector which has, relative to the first sector, at least a portion located at a greater distance from said end.
  • a hypervelocity projectile such as, for example, a shell, a bullet or a missile, having a nose, generally cone-shaped, having a more or less pointed end and characterized in that it comprises at least one group of at least three electrode
  • these at least three electrodes are aligned longitudinally, preferably in the direction M parallel to the rectilinear movement of the projectile.
  • the first and second means each comprise a low-voltage generator and at least one low-voltage capacitor.
  • said first means are capable of generating, between said first and second electrodes, at least one high voltage T1 discharge and then, preferably, low voltage T3, these first means being preferentially able to store a low quantity of energy, know lower than the deciJoule for high voltage and the order of Joule for low voltage.
  • said second means are capable of generating a low voltage discharge T2, these second means preferably being able to store a high quantity of energy, namely at least equal to 5 Joule.
  • the invention also relates to a projectile using a device according to the invention.
  • a shock wave occurs upstream of its nose.
  • the pressures distributed over its surface are balanced and the shock wave has symmetries depending on the shape of the vehicle.
  • the wave is attached to the tip of the cone and is conical in shape.
  • FIG. 2 presents the result of a numerical simulation of a machine of longitudinal axis X flying at a supersonic speed in direction Z of the arrow. It shows integrally a machine 1 and half of two other surfaces 2 and 3.
  • the machine comprises a front portion 4 conical and a rear portion 5 cylindrical. Said surfaces 2 and 3 characterize a constant pressure in the flow.
  • the surface 2 attached to the tip of the machine represents the surface of the conical shock wave while the surface 3 attached to the discontinuity of the surface of the machine (cone-cylinder junction) characterizes a relaxation wave.
  • the invention applied to such a projectile consists in unbalancing the flow around the nose of the machine by producing a plasma discharge, for example towards the end 29 of the nose as close as possible to the point, in order to realize an incidence of the machine.
  • This plasma discharge carried out on a limited angular sector modifies the boundary layer which surrounds the surface of the machine.
  • the objective is therefore to produce a discharge such that the imbalance of the thermodynamic quantities is large enough to cause the deviation of the machine relative to a straight path.
  • FIG. 3 shows the result of a numerical simulation of the same machine operating under the same supersonic flight conditions as before. a plasma discharge is applied near the tip. Each of the two surfaces 7 and 3 shown therein features a constant pressure in the flow.
  • Figure 4 shows the dissymmetry of the density distribution of the surrounding air over half of the projectile surface and in the plane of symmetry of the flow for the chosen example.
  • This density is substantially constant and equal to 1 kg / m 3 between the points A and B situated opposite the plasma discharge 6 and downstream, with respect to the Z direction of the projectile, from the plasma discharge (zone C ), while it is very low (of the order of 2.7 • 10 -2 kg / m 3 ) at the level of the skin E of the projectile upstream of the plasma discharge 6.
  • it is maximal, of the order of 3kg / m 3 at point D at the plasma discharge 6.
  • Figure 5 shows a diagram of a part of a device according to one embodiment of the invention.
  • This part has a cone-shaped nose 4 of a hypervelocity projectile. Near the end 29 of the nose is shown a plasma discharge 6.
  • a plasma discharge 6 is carried out in a first step on a limited sector 8 of the external surface of the nose and on the side of the direction Y and a second step of supplying this plasma with energy is then carried out.
  • FIG. 6 shows an exemplary embodiment of a device for generating a plasma according to the invention comprising two pairs of electrodes, namely A and B and B and C and first means 10 for generating a high voltage. T1 and a low voltage T3 between the electrodes A and B, and second means 20 for generating a low voltage T2 between the electrodes B and C.
  • the voltage T1 generated by the first means 10 is able to break the barrier of the dielectric between the electrodes A and B or, in other words to ionize the gas present between these electrodes, then the voltage T3 is able to maintain this ionization between the said same two electrodes, while the voltage T2 is suitable to increase the ionization of said gas between the electrodes B and C.
  • the first means generate a voltage T1 consisting of a level of 10kV with a low stored energy of the order of 3mJ followed by a voltage level T3 of 0.55kV with a stored energy of 12J, while that the second means 20 generate a voltage T2 of 0.55 kV with a high stored energy of the order of 50J by the use of a capacity of 330 ⁇ F.
  • the plasma is generated by high voltage discharge (s). This (these) discharge (s) is (are) triggered (s) from a low level electrical or optical signal external to the present device (these) discharge (s) delivers (s) sufficient energy to the priming the plasma.
  • the design optimizes the stored electrical energy prior to tripping and the voltage pulse appropriate to the conditions of the plasma discharge.
  • FIG. 6 shows the application of the device for generating a plasma to a hypervelike projectile of which only the front part, in this case the nose, is represented.
  • This projectile is supposed to move in direction M with a speed V.
  • the device comprises three electrodes, one of which is common to the first and second means for generating a voltage. These three electrodes C, B and A are aligned along said direction M.
  • the projectile is supposed to move in the air at a high speed in the direction M perpendicular to the Y direction.
  • a plasma discharge is generated, which plasma is then supplied with energy. It consists of proceeding, on the side of the direction Y and with the aid of a device according to the invention, to a plasma discharge on a first limited sector 28 of the external surface of the nose, this sector 28 being delimited by the electrodes A and B and then supplying this plasma energy on a second limited sector 27 of the external surface of the nose, this sector 27 being delimited by the electrodes B and C.
  • a high voltage discharge is applied by the first means 10 to the electrodes A and B, producing between them a voltage difference T1.
  • This voltage difference is sufficient to break the dielectric barrier of the air and generate a microplasma. Then a low voltage supply is applied by the first means 10 to the electrodes A and B, producing between them a voltage difference T3 sufficient to ionize the air, thereby generating a plasma on the sector 28. Given its speed, the projectile moves relative to the generated plasma. When the plasma is found on the second sector 27 delimited by the electrodes B and C, successive low voltage discharges are applied by the second means 20 to the electrodes B and C, producing between them a voltage difference T2. These low voltage discharges are sufficient to maintain the plasma, that is to say maintain its existence for a period of several milliseconds, sufficient to allow the deflection of the projectile.
  • three groups of electrodes each comprising three electrodes A, B and C are distributed over the circumference of the nose of the projectile.
  • the three pairs of electrodes A and B are each connected to their own first means 10 while the three pairs of electrodes B and C are each connected to their own second means 20.
  • Such an arrangement makes it possible to deviate, possibly by combining said groups, the projectile in all directions.
  • FIG. 8 shows a diagram of a control circuit for the voltage applied to the electrodes arranged according to the layout of FIG. 7.
  • This circuit comprises a control device 40 controlling the voltage distributing trip devices 41 and 42 which respectively control the first and second means 10 and 20 for generating a voltage.
  • These generators 10 and 20 are each respectively connected to each of the electrodes A and B and the other to each of the electrodes B and C.
  • control device 40 controls via the distributing trip units 41 and 42 and the first and second means 10 and 20 for generating a voltage, on the one hand the generation of the appropriate difference in voltage, namely high voltage and then low voltage for the first means for generating a voltage and low voltage for the second means, and secondly the delivery of these voltages to the group (30, 31, 32) of electrodes corresponding to the desired direction of deviation.
  • the drag of the machine, the force and the moment of piloting can be determined by calculation. Even in the case where efforts are low, this device is interesting because by acting near the tip of the machine, a small dissymmetry of the flow destabilizes the projectile and allows its piloting.
  • the use of the same device, or of another device according to the invention placed at another place on the projectile, can be used to stabilize the projectile again on its trajectory.
  • this device can be associated with means allowing its control, such as, for example, a GPS system, a self-steering type system, a remote control system, or any other system for knowing the roll position of the machine.
  • a plasma discharge whose temperature is about 15000K, is carried out on a surface of 9 mm 2 near the tip of the projectile which requires a momentum corresponding to a mass flow rate of an explosive substance of about 15 ⁇ 10 -4 kg / s corresponding to a power of about 3 kVA.
  • the duration of the discharge being between 2 and 4 ms, the electrical energy is of the order of ten Joules.
  • the intensity of the discharge can be modulated by acting on the thermodynamic parameters such as the temperature in the discharge and the associated momentum.
  • the effect on the aerodynamic effects is interesting.
  • the aerodynamic effects are first evaluated by numerical simulation in the case of the unmanned projectile moving on a straight trajectory at zero incidence.
  • the aerodynamic coefficients are calculated only for the front body of the projectile, the wake is therefore not taken into account:
  • the coefficient of lift Cz and the moment coefficient Cm calculated at the tip of the projectile are obviously zero.
  • the shape of the nose can be any and not necessarily revolution.
  • the invention can also be applied to sectors not located on the nose of the machine, and may be on the cylindrical surface, on empennages or bearing surfaces of the machine.
  • several electrodes, preferably arranged in parallel can be used to generate a plasma and / or several electrodes, preferably arranged in parallel can be used to maintain one or more generated plasmas.
  • many provisions of said first second, third and fourth electrodes are possible.
  • the first and second electrodes may be aligned longitudinally or be arranged perpendicularly or even take an intermediate position between these two positions. It is the same for the third and fourth electrodes.
  • At least a portion of the sector delimited by the third and fourth electrodes is further away from the end of the nose of the projectile than that delimited by the first and second electrodes.
  • the angle formed by the longitudinal axis and these electrodes can reach ⁇ Rd if these electrodes are positioned at the nose of the projectile.
  • each group of electrodes may be positioned at any other location of the projectile to be determined for each particular application depending on the mission assigned to it.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Plasma Technology (AREA)
EP06291486A 2005-09-27 2006-09-21 Im Innern eines Flugkörpers angebrachte Plasmaentladungen erzeugende Vorrichtung zur Steuerung eines supersonischen oder hypersonischen Flugkörpers Active EP1767894B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0509831A FR2891359B1 (fr) 2005-09-27 2005-09-27 Nouveau dispositif embarque de generation de decharge(s) plasma pour le pilotage d'un engin supersonique ou hypersonique.

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EP1767894A1 true EP1767894A1 (de) 2007-03-28
EP1767894B1 EP1767894B1 (de) 2009-05-13

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US (1) US7645969B2 (de)
EP (1) EP1767894B1 (de)
CA (1) CA2560520C (de)
DE (1) DE602006006767D1 (de)
FR (1) FR2891359B1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7988103B2 (en) 2007-01-19 2011-08-02 John Hopkins University Solid state supersonic flow actuator and method of use

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8119956B2 (en) * 2008-10-02 2012-02-21 Raytheon Company Multi-stage hyper-velocity kinetic energy missile
US8502126B2 (en) * 2010-05-27 2013-08-06 Raytheon Company System and method for navigating an object
US9329007B2 (en) 2013-02-01 2016-05-03 Orbital Atk, Inc. Charged projectiles and related assemblies, systems and methods
US10113844B1 (en) * 2016-11-21 2018-10-30 Lockheed Martin Corporation Missile, chemical plasm steering system, and method
US10914559B1 (en) 2016-11-21 2021-02-09 Lockheed Martin Corporation Missile, slot thrust attitude controller system, and method
CN112937912B (zh) * 2021-01-21 2023-08-15 南京南华航空产业有限公司 一种基于阵列式等离子体的旋成体侧向力控制实验装置

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US3151259A (en) 1959-08-18 1964-09-29 Gen Electric Plasma accelerator system
US3176227A (en) * 1959-09-23 1965-03-30 Bendix Corp Control of ions in ionic media for communication and other purposes
US3325123A (en) * 1961-05-19 1967-06-13 Fay E Null Magnetohydrodynamic control
US6247671B1 (en) * 1998-09-23 2001-06-19 Accurate Automation Corporation Ion doping apparatus and method for aerodynamic flow control
FR2846081A1 (fr) 2002-10-17 2004-04-23 Saint Louis Inst Pilotage d'un projectile par decharge plasma

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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
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Publication number Priority date Publication date Assignee Title
US3151259A (en) 1959-08-18 1964-09-29 Gen Electric Plasma accelerator system
US3176227A (en) * 1959-09-23 1965-03-30 Bendix Corp Control of ions in ionic media for communication and other purposes
US3325123A (en) * 1961-05-19 1967-06-13 Fay E Null Magnetohydrodynamic control
US6247671B1 (en) * 1998-09-23 2001-06-19 Accurate Automation Corporation Ion doping apparatus and method for aerodynamic flow control
FR2846081A1 (fr) 2002-10-17 2004-04-23 Saint Louis Inst Pilotage d'un projectile par decharge plasma

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7988103B2 (en) 2007-01-19 2011-08-02 John Hopkins University Solid state supersonic flow actuator and method of use

Also Published As

Publication number Publication date
US20070200028A1 (en) 2007-08-30
US7645969B2 (en) 2010-01-12
DE602006006767D1 (de) 2009-06-25
CA2560520A1 (fr) 2007-03-27
EP1767894B1 (de) 2009-05-13
FR2891359B1 (fr) 2007-12-14
CA2560520C (fr) 2014-03-25
FR2891359A1 (fr) 2007-03-30

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