EP1813907A1 - Corps volant pour la zone supersonique - Google Patents

Corps volant pour la zone supersonique Download PDF

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Publication number
EP1813907A1
EP1813907A1 EP07001443A EP07001443A EP1813907A1 EP 1813907 A1 EP1813907 A1 EP 1813907A1 EP 07001443 A EP07001443 A EP 07001443A EP 07001443 A EP07001443 A EP 07001443A EP 1813907 A1 EP1813907 A1 EP 1813907A1
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EP
European Patent Office
Prior art keywords
aero
spike
missile
pivotable
spikes
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
EP07001443A
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German (de)
English (en)
Other versions
EP1813907B1 (fr
Inventor
Erich Dr. Schülein
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.)
Deutsches Zentrum fuer Luft und Raumfahrt eV
Original Assignee
Deutsches Zentrum fuer Luft und Raumfahrt eV
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.)
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Publication date
Application filed by Deutsches Zentrum fuer Luft und Raumfahrt eV filed Critical Deutsches Zentrum fuer Luft und Raumfahrt eV
Publication of EP1813907A1 publication Critical patent/EP1813907A1/fr
Application granted granted Critical
Publication of EP1813907B1 publication Critical patent/EP1813907B1/fr
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
    • F42B10/32—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

Definitions

  • the invention relates to a missile for the supersonic range with an aero-spike, which extends upstream from a front end face of the missile.
  • Aero spikes are attached directly to, for example, a semi-spherical nose or a seeker head of the missile and are aligned along a longitudinal axis of the missile.
  • the aero-spike can be significantly reduced by an induced flow separation in the area of the distal end of the aero-spike, which results from the interaction of the bow thrust with the boundary layer at the aero-spike, in [1 ] is estimated at up to 80%.
  • the document proposes not to form the aero-spike as a mandrel with a constant cross-section and with a tip or a plate at the distal end, but rather to provide a spherical, ellipsoidal or teardrop-shaped attachment at the distal end.
  • This has the result that a compression shock occurs in the region of the distal end of the aero-spike, which is immediately attenuated by a dilution fan.
  • Behind the dilution fan occurs at the essay a replacement.
  • the detached flow mixes with the flow behind the dilution fan and occurs both on the windward side and on the leeward side, where it is then pushed off as well.
  • the invention has for its object to provide a missile with an Aero-Spike, in which with alternative or cumulative to the aforementioned measures proposed design features negative effects of flow to the missile at an angle to the longitudinal axis of the missile are at least reduced.
  • the present invention is based on the idea to adapt the missile with the Aero-Spike (exclusively) measures taken by a-priori measures or measures taken before the launch of the missile to different flight conditions. Rather, it is suggested that the Aero-Spike, taking into account the respective flight conditions of the missile is pivotable. In the event that with the pivoting of the aero-spike primarily changed angle of attack in a plane passing through the longitudinal axis of the missile plane is taken into account, this may, for example.
  • the aero-spike be pivotable about an axis perpendicular to the longitudinal axis and the previously mentioned. Alternatively, a spatial pivoting of the aero-spikes can take place about a pivot point arranged in the region of the front end face.
  • an "aero-spike” is understood to mean, in particular, a flow-guiding element which increases the effective degree of slimming of the aircraft by means of a local current reduced in the direction of flight and reduces the nose resistance.
  • the generation of such a local stream at the bow of the missile is carried out, for example, directly by means of so-called “jet spikes” (often referred to as “counterflow-jet”, cf., eg [3]), or directly by a manipulation of the total pressure distribution in the atmosphere, which, in interaction with this bow thrust, leads to the formation of a recirculation bubble.
  • jet spikes of the total pressure distribution in the atmosphere
  • the last type also includes applications with optical, electrical and electromagnetic flow heating by means of "beam-spikes” (also known as “energy deposition control” or the like, see also [3], [4 ]).
  • the variability of the aero spikes can result in a simplified structural design, which is error-resistant even under harsh operating conditions.
  • At least one alignment element is provided. According to an influence of the flow on this alignment element of the Aero-Spike is automatically and passively swiveled.
  • the alignment elements may be rigid elements in accordance with the principle of a wind vane, which are arranged downstream of the bearing point or a bearing axis of the Aero-Spikes and their alignment with the flow, the orientation of the Aero-Spikes pulls.
  • the alignment element may be a flat or curved surface.
  • the alignment element may be formed as a lattice. In this case, the well-known excellent stability behavior of a grating surface wind vane can be used for the invention.
  • the pivoting can also be done by active measures.
  • active is understood to mean a pivoting using an energy supply of the missile and / or a control or regulation unit with a suitable actuator. Such active pivoting may account for anticipated flight and flow conditions or actual or detected flow or flight conditions.
  • the missile has a memory unit in which an a priori defined course of a desired influence of the aero-spikes during a flight phase can be stored.
  • the aero-spike can be actively pivoted taking into account the stored history.
  • different flight phases such as a climb, a flight phase with cruising altitude and a Zielanflugphase are stored with the associated expected time periods, so that the respective requirements can be taken into account by changing the position of the aero-spikes in the respective phases of flight.
  • any other different flight phases are to be considered a priori in the memory unit.
  • a particularly simple suitable pivoting of the aero-spike can take place in that it depends on a steering action of the missile.
  • an optimal pivoting angle of the aero-spike be stored depending on the steering action of the missile, so that in flight for a request for a suitable steering action optimum pivoting of the aero-spike is known.
  • Such a dependency can be stored in the form of maps or functional dependencies.
  • the pivoting of the aero-spike with a steering element of the missile is electrically, mechanically or hydraulically coupled.
  • the aero-spike is pivotable together with the front end face of the missile.
  • the pivoting enabling grooves, guides, bearings u. ⁇ . Be avoided in the area of the flow conditions of great importance playing face.
  • the front end face is not formed part-spherical in the area of the aero-spike, can continue to be ensured by a joint pivoting of the aero-spike and the front face, that in addition to the adaptation of Aero spikes at the angle of attack also a dependence of the orientation of the front end face against the direction of flow is at least reduced.
  • a homing head is arranged in the missile, which searches a target, for example, with IR or radar wave transmission.
  • a homing dome to cover the homing head may cause u.
  • the aerodynamic requirements may lag behind the desired seeker head functionalities, so the missile may be equipped with a semi-spherical nose which, while capable of high bow drag, improves the seeker head functionality, which is beneficial, for example, for high agile aircraft is.
  • all necessary radar antennas or IR sensors can be optimally positioned.
  • the entire "field of view" of the homing head dome can be made of radiation-transmissive materials. Such a concept allows active and flight direction independent target tracking by a corresponding separate movement of the homing head. Due to the requirement for the target seeker dome to be made of a transmissive material, it may be necessary to use a material which places increased demands on the maximum temperatures and pressures acting in the area of the target seeker dome.
  • the pivotable aero-spike has a thickening at its distal end.
  • a thickening is a disk, a sphere, a cone, a drop shape or an ellipsoid.
  • the missile 1 illustrated in the figures is intended, after covering a trajectory, to hit a moving or stationary target object on land, water or in the air, according to FIG. 1, an opposing missile 3.
  • the missile 1 has in the region of a front end face 4 a homing seeker 5, via which the position of the target object relative to the missile can be detected and influenced via a control device steering elements such that the trajectory 2 of the missile 1 hits the target object.
  • the front end face 4 is formed with a substantially part-spherical Zielsuchkopfdom 6, which is mounted with a pivot axis or a ball joint 7 pivotable about the pivot axis or spatially movable relative to the ball joint relative to the housing of the missile 1.
  • the Zielsuchkopfdom 6 is independent of the pivoting under sealing and under favorable aerodynamic design in a tubular outer surface 8 of the missile 1 over. 1, the flow 9 of the medium in which the missile 1 moves is indicated by an arrow. Opposite a longitudinal axis 10-10 results in an angle of attack 11, which is for the flight state shown in Fig. 1 # 0.
  • an aero-spike 12 carried by the target seeker dome 6 is aligned with the longitudinal axis 10-10 and the flow direction.
  • the aero-spike 12 is designed for the illustrated embodiment as a mandrel with a cylindrical lateral surface whose longitudinal extent is a multiple of the diameter.
  • At the proximal end of the aero-spike 12 is fixedly connected to the Zielsuchkopfdom 6.
  • the distal end 12 has a taper or conical tip for the illustrated embodiment, in which case also out DE 199 53 701 C2 known deviating geometries and essays can be used.
  • the Zielsuchkopfdom 6 is pivoted about the previously described neutral position about an axis oriented vertically to the plane, so that a pivot angle 13 of the Aero-Spikes 12 relative to the longitudinal axis 10-10 results.
  • a pivot angle 13 of the Aero-Spikes 12 relative to the longitudinal axis 10-10 results.
  • the angle of attack 11 corresponds to the pivot angle 13 the angle of attack 11, wherein for another design is also possible that the pivot angle 13 deviates from the angle of attack 11, in particular smaller than this.
  • the attachment point of the Aero-Spikes 12 moves to the Zielsuchkopfdom 6 on a circular path around the pivot axis 7 with the radius of the distance of the attachment point of the pivot axis, so that with increasing pivoting the distance of the attachment point is increased from the longitudinal axis 10-10.
  • the Zielsuchkopfdom 6 carries alignment elements 14.
  • the alignment elements 14 are to be referred to as L-shaped in a first approximation, wherein the free end portion of the short leg of the L is rigidly secured to the Zielsuchkopfdom 6 and the long leg of the L in the neutral position approximately parallel to the longitudinal axis 10-10 and slightly spaced from the lateral surface 8 of the missile 1 extends.
  • the end of the alignment elements facing away from the Zielsuchkopfdom 6 carries surfaces 15 or a Gitterleitmaschine.
  • the surface 15 or the lattice are arranged in the direction of the longitudinal axis 10-10 behind the pivot axis 7 of Aero-Spike 12, Kugelsuchkopfdom 6 and the alignment elements 14 so that forces due to the flow, which act on the surfaces 15 and are greater than on the aero-spike 12 forces exerted by the flow, cause the Aero-Spike 12 aligns exactly to the flow 9.
  • the distance of the alignment elements 14 from the lateral surface 8 of the missile 1 is selected such that the required pivoting about a pivot angle 13 during an expected flight operation is possible.
  • FIG. 3 and 4 show a sketch of the resulting flow structures, on the one hand for a prior art rigid aero-spike 12 and on the other hand for a pivotable aero-spike according to the present invention in an oblique flow. While, according to FIG. 3, the front end face 4 and the homing seeker dome 6 in the region 16 are acted upon by the flow detached from the aero-spike 12, such a stress is the front end face 4 and the Zielsuchkopfdoms 6 for the pivoting of the Aero spikes 12 as shown in FIG. 4 largely avoided.
  • FIG. 5 shows a schematic block diagram for actively influencing the swivel angle 13 of the aero-spike 12 with respect to the longitudinal axis 10-10 of the missile.
  • a measuring element 17 supplies a signal 18 which at least correlates with the angle of attack 11.
  • the signal 18 is fed to a control device 19.
  • the control device 19 determines an application signal 20 for an actuator 21 which, in particular via a force, a moment, a travel or an angle 22, acts on the aero-spike 12 for adjusting the swivel angle 13.
  • the control device 19 may be provided separately for driving the Aero-Spikes 12 or, as indicated in Fig. 5, take over other functions, such as generate steering signals 23 to influence the trajectory 2 of the missile 1 or process signals of the homing 5.
  • the control device 19 is connected via a signal connection 24 in conjunction with a memory device 25 in which, for example, a priori determined gradients for the pivot angle 13 of the Aero-Spikes 12 are stored and / or dependencies of the Beaufschlagungssignals 20 of a signal 18 and / or steering signals 23 in Form of functional parameters or maps are stored.
  • the missile 1 in the front end region has an extension 26 which carries a spherical end portion 27.
  • Fixedly connected to the Zielsuchkopfdom 6 are inwardly extending support 28 which carry a ball sleeve 29.
  • the spherical end portion 27 and the ball sleeve 29 form a joint 30, via which the Zielsuchkopfdom 6 with the attached thereto Aero-spike 12 is spatially, for example in the direction 31 relative to the missile 1 is pivotable.
  • the Zielsuchkopfdom 6 is approximately spherical and received in a ball seat 32 of the missile 1, whereby in this case, the joint 30 is formed. If such a training in the Zielsuchkopfdom 6 to arrange a homing head, so this is to be formed as an independent unit. Alternatively, a transmission of electrical signals between the missile 1 and the Zielsuchkopfdom 6 done, for example by means of sliding contacts, moving wires or a transmission of radio signals.
  • the Aero-Spike 12 has a spherical or cylindrical end portion 33, with which this is pivotally mounted in the spatial direction or pivotally mounted in the plane in a cylindrical or spherical receptacle 34, whereby in this case the joint 30th is formed.
  • the sleeve 36 carries on both sides in the direction of the transverse axis 38-38 oriented bearing pin 39, 40, with respect to which the aero-spike 12 is mounted with the alignment elements 14 in the region of bearing eyes 41, 42 pivotable about the transverse axis 38.
  • the alignment elements 14 are formed in the form of a sheet-like body, which extends approximately circular around the Zielsuchkopfdom 6, here centrally carries the Aero-Spike 12, the side of the Zielsuchkopfdoms 6, the bearing eyes 41, 42nd forms and is rotated in the opposite end of the aero-spike 12 for a suitable flow around the longitudinal axis of the end portions.
  • FIGS. 10 to 12 show a further embodiment for ensuring a pivotability of the aero-spike 12 with the alignment elements 14.
  • aero-spike 12 and alignment elements 14 are fixedly disposed on an outer sleeve 36, the is supported by a slide bearing pivotable about the longitudinal axis 10-10 relative to an outer cylindrical lateral surface of a hollow cylindrical intermediate body 43.
  • the sleeve 36 with the associated attachments such as aero-spike 12 and alignment elements 14 can have a center of gravity which is arranged eccentrically to the longitudinal axis 10-10.
  • the intermediate body 13 is supported by bearing bolts 39, 40 in the direction of the transverse axis 38-38 pivotally about this against an inner body 44 of the missile 1, wherein the bearing pins 39, 40 are fixedly connected to the inner body 44 and in bearing eyes of the intermediate body 43 are pivotable or are fixedly connected to the intermediate body 43 and in bearing eyes of the inner body 44 are pivotable.
  • a blunt nasal shape is typically used, which is necessary to ensure the functionality of the seeker head.
  • this form leads to a very high aerodynamic resistance, which occurs for example at supersonic speeds by forming a strong compression shock at the bow. As it passes through the shock, the entropy of the flow medium increases and at the same time the static pressure drops. This causes the so-called wave resistance on the missile, which increases very much from the intensity of the bow thrust and with the speed.
  • the relative size of the aero spike may vary for different missions, aero spike types, and speed ranges. From the literature, information on the most effective rigid aero spikes for low supersonic speeds (Mach number between 1.8 and 3) known, said z. B. is dull aero spikes with relative thicknesses usually ⁇ 0.2 D and a relative length of about (1-2) D, where D denotes the frontal diameter of the missile.
  • an equilibrium position of the pivot angle 13 may be predetermined, for example via suitable spring elements or detents for a pivoting angle of zero.
EP07001443A 2006-01-26 2007-01-24 Corps volant pour le domaine supersonique Expired - Fee Related EP1813907B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102006003638A DE102006003638B4 (de) 2006-01-26 2006-01-26 Flugkörper für den Überschallbereich

Publications (2)

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EP1813907A1 true EP1813907A1 (fr) 2007-08-01
EP1813907B1 EP1813907B1 (fr) 2012-02-22

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US (1) US7775480B2 (fr)
EP (1) EP1813907B1 (fr)
DE (1) DE102006003638B4 (fr)

Cited By (1)

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CN107600408A (zh) * 2017-09-21 2018-01-19 吉林大学 一种用于可折叠扑翼微飞行器的磁吸式可折叠翼机构

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DE102006061709B3 (de) * 2006-12-28 2008-05-29 Deutsches Zentrum für Luft- und Raumfahrt e.V. Flugkörper für den Überschallbereich mit einem porösen Stirnkörper
DE102009001953B4 (de) 2009-03-27 2013-11-14 Deutsches Zentrum für Luft- und Raumfahrt e.V. Vorrichtung zur Beeinflussung einer Überschall-Umströmung
US8502126B2 (en) * 2010-05-27 2013-08-06 Raytheon Company System and method for navigating an object
DE102010024252B3 (de) 2010-06-18 2011-12-22 Lkf-Lenkflugkörpersysteme Gmbh Vorrichtung zur passiven Ausrichtung einer Geräteplattform in einem durch ein Medium bewegten Körper
US9228815B2 (en) * 2011-07-04 2016-01-05 Omnitek Partners Llc Very low-power actuation devices
US20160009360A1 (en) * 2014-07-14 2016-01-14 Raytheon Company Optical window system with aero-optical conductive blades
CN112158362B (zh) * 2020-09-30 2021-04-20 中国空气动力研究与发展中心超高速空气动力研究所 一种航天器减阻降热装置及方法
CN112498658A (zh) * 2020-11-30 2021-03-16 南京航空航天大学 一种可调式高超声速飞行器主动热防护系统
CN113551565B (zh) * 2021-09-18 2021-11-30 中国科学院力学研究所 一种级间段气动保形的固体火箭及分离方法
CN114018534B (zh) * 2021-11-10 2024-02-06 西安航天动力试验技术研究所 钝头体超声速自由射流试验装置及试验方法
CN115946842B (zh) * 2023-03-10 2023-05-26 中国空气动力研究与发展中心计算空气动力研究所 一种飞行器的减阻装置及飞行器

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US2932945A (en) * 1957-04-16 1960-04-19 Westinghouse Electric Corp Weathercocking supersonic diffuser
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US3416758A (en) * 1967-10-04 1968-12-17 Navy Usa Self-balancing spike control
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DE19953701A1 (de) * 1999-11-08 2001-05-23 Lfk Gmbh Verfahren zur Verminderung von Druck und Temperatur auf der Vorderseite eines Flugkörpers bei Überschallgeschwindigkeit
US6467722B1 (en) * 2002-01-31 2002-10-22 The United States Of America As Represented By The Secretary Of The Army Magnetostrictive missile guidance system
US6527221B1 (en) 2000-05-31 2003-03-04 Kevin Kremeyer Shock wave modification method, apparatus, and system

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Publication number Priority date Publication date Assignee Title
NL88131C (fr) * 1900-01-01
US2776806A (en) * 1954-02-05 1957-01-08 United Aircraft Corp Weathercocking supersonic wedge diffuser for air inlets in aircraft
US2932945A (en) * 1957-04-16 1960-04-19 Westinghouse Electric Corp Weathercocking supersonic diffuser
US3094072A (en) * 1957-12-09 1963-06-18 Arthur R Parilla Aircraft, missiles, missile weapons systems, and space ships
US3195462A (en) * 1961-05-17 1965-07-20 Aerojet General Co Pull rocket shroud
US3416758A (en) * 1967-10-04 1968-12-17 Navy Usa Self-balancing spike control
US3713607A (en) 1968-08-15 1973-01-30 Us Navy Load reducing spike for supersonic missiles
US4399962A (en) * 1981-08-31 1983-08-23 General Dynamics, Pomona Division Wobble nose control for projectiles
DE3503041C1 (de) * 1985-01-30 1986-09-11 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Schnellfliegender Flugkörper mit aerodynamischer Steuerung
DE3612175C1 (de) 1986-04-11 1987-10-08 Messerschmitt Boelkow Blohm Schnellfliegender Flugkoerper
DE3815290C1 (fr) * 1988-05-05 1989-08-17 Messerschmitt-Boelkow-Blohm Gmbh, 8012 Ottobrunn, De
US4998994A (en) * 1989-09-20 1991-03-12 The United States Of America As Represented By The Secretary Of The Army Aerodynamically compliant projectile nose
DE19953701A1 (de) * 1999-11-08 2001-05-23 Lfk Gmbh Verfahren zur Verminderung von Druck und Temperatur auf der Vorderseite eines Flugkörpers bei Überschallgeschwindigkeit
DE19953701C2 (de) 1999-11-08 2002-01-24 Lfk Gmbh Verfahren und Vorrichtungen zur Verminderung von Druck und Temperatur auf der Vorderseite eines Flugkörpers bei Überschallgeschwindigkeit
US6527221B1 (en) 2000-05-31 2003-03-04 Kevin Kremeyer Shock wave modification method, apparatus, and system
US6467722B1 (en) * 2002-01-31 2002-10-22 The United States Of America As Represented By The Secretary Of The Army Magnetostrictive missile guidance system

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107600408A (zh) * 2017-09-21 2018-01-19 吉林大学 一种用于可折叠扑翼微飞行器的磁吸式可折叠翼机构
CN107600408B (zh) * 2017-09-21 2023-07-14 吉林大学 一种用于可折叠扑翼微飞行器的磁吸式可折叠翼机构

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US7775480B2 (en) 2010-08-17
US20070295856A1 (en) 2007-12-27
DE102006003638B4 (de) 2008-01-17
EP1813907B1 (fr) 2012-02-22
DE102006003638A1 (de) 2007-08-09

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