EP0062563B1 - Verfahren zum Steuern der Seitwärtsbeschleunigung eines Flugkörpers und entsprechendes Waffensystem - Google Patents

Verfahren zum Steuern der Seitwärtsbeschleunigung eines Flugkörpers und entsprechendes Waffensystem Download PDF

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Publication number
EP0062563B1
EP0062563B1 EP82400527A EP82400527A EP0062563B1 EP 0062563 B1 EP0062563 B1 EP 0062563B1 EP 82400527 A EP82400527 A EP 82400527A EP 82400527 A EP82400527 A EP 82400527A EP 0062563 B1 EP0062563 B1 EP 0062563B1
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EP
European Patent Office
Prior art keywords
pif
paf
missile
control
aerodynamic
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EP82400527A
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English (en)
French (fr)
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EP0062563A1 (de
Inventor
Gérard Selince
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Airbus Group SAS
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Airbus Group SAS
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Priority to AT82400527T priority Critical patent/ATE15266T1/de
Publication of EP0062563A1 publication Critical patent/EP0062563A1/de
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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
    • F42B10/661—Steering by varying intensity or direction of thrust using several transversally acting rocket motors, each motor containing an individual propellant charge, e.g. solid charge
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • 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
    • F42B10/663—Steering by varying intensity or direction of thrust using a plurality of transversally acting auxiliary nozzles, which are opened or closed by valves

Definitions

  • the present invention relates to guided missiles intended for the neutralization of air attackers more particularly those animated by a very high speed on trajectory, having a great capacity of maneuver, with approach of final attack possible either in gliding flight, or in very strong dive.
  • a target is more particularly characterized by its displacement: speed, direction, maneuverability, trajectory.
  • the target can be hit by a guided missile according to a law of guidance (alignment guidance, proportional guidance, etc.), which brings the missile closer to the target as the latter moves slowly and regular.
  • alignment guidance proportional guidance, etc.
  • An end-of-travel error must be compensated by a final maneuver of piloting the missile towards the target.
  • the load factors in particular in the vicinity of the interception, must be all the more important and the response times all the shorter, the greater the maneuverability-escape performance of the target.
  • a typical offensive target representing a threat that is particularly difficult to neutralize
  • a supersonic missile which is extremely maneuverable and makes a final approach in sharp dive or in leveling.
  • the late discovery of the hostile missile requires neutralization as soon as possible in order to ensure the security of the site to be protected.
  • control surfaces causing this incidence are either of the aerodynamic type, or with control surfaces in the jet of the main propellant, or else by lateral auxiliary jets supplied from the main propellant or from independent elements.
  • a response time of a few hundredths of a second can be obtained by the use of forces passing practically through the center of gravity, these forces being able to be acquired aerodynamically or by lateral jets. In this case, there is little or no aerodynamic incidence taken but direct displacement of the center of gravity.
  • PAF force piloting
  • the invention relates essentially to a combination of aerodynamic steering "PAF", providing in particular a high load factor with steering "PIF which on the one hand provides a great speed of response and which also makes it possible to significantly raise the total maneuverability of the missile.
  • PAF aerodynamic steering
  • This invention makes it possible, in combination with numerous known devices, to define various new weapon systems, capable in particular of ensuring the destruction of a supersonic aerodyne with very high maneuverability performing an approach in low-angle flight or at a very high angle. of dive.
  • a first weapon system consists in vertically ejecting a missile with its accelerator off, tilting it in the direction of the target using the "PIF” piloting system, and switching on the accelerator to carry the missile at very high speed then, at the end of combustion of said accelerator, the center of gravity of the missile now remaining fixed, to be able to use “PIF-PAF” piloting.
  • a second weapon system consists of dropping the missile from an aerodyne and using its specific devices to carry out a rapid rally towards the objective.
  • the missile according to FIGS. 1 and 2 comprises, in the usual manner, a three-axis autopilot.
  • the detection of the target is carried out on the site (for example: a surveillance radar 11A on a surface building 11 which gives the situation of the target on site, deposit and distance) and the elements treated are communicated to said missile.
  • the invention proposes to associate with a missile comprising an aerodynamic piloting means with a high load factor called "PAF”, a force piloting mode called “PIF”, said piloting mode comprising means producing forces passing near the center of gravity as suggested by the examination of Figure 1.
  • references 1 and 2 respectively designate the missile and its releasable accelerator.
  • the missile 1 comprises: a seeker 3; piloting and guiding equipment 4; a force piloting mode “PIF itself comprising a device for deflecting jets 5 producing forces passing near the center of gravity C G and the propellant devices 6A and 6 B arranged in the vicinity of the deflection device 5 so that the known displacement of the center of gravity C G is very low during propellant of the propellant; a set of wing and aerodynamic control surfaces “PAF” bearing the general reference 7.
  • the reference 8 designates the deployable stabilizer in this case the releasable accelerator 2.
  • FIGS. 2 and 3 This is illustrated in FIGS. 2 and 3 where we see respectively a high performance objective 10, attacked during phase IV (FIG. 2) or even less effective but more distant objectives such as helicopter 13 or attacked plane 12 during phase V ( Figure 3).
  • objectives 12 or 13 could, a fortiori, be neutralized during phase IV.
  • the composite 1 + 2 missile and accelerator assembly extinguished is ejected from a site 11 at a speed of the order of a few tens of meters / second, for example using a gas generator associated with the launch tube 11 B.
  • phase I the first “PIF” force piloting regime is initiated, making it possible to achieve, in phase II, the tilting of said assembly in a few tenths of a second.
  • phase III the accelerator is on, causing the missile to accelerate to around 1,000 m / s.
  • the seeker begins its search for target 10 and, in the event of a catch before the end of acceleration phase III, a first correction of orientation of the missile is then carried out by means of the "PIF" .
  • the trajectory in the vertical plane is carried out in a slight dive in order to avoid certain possible effects such as the “image on the sea” effect for example.
  • yaw and pitch control is ensured by the first operating level of the "PIF", that is to say with action of said “PIF” device, offset from the center of gravity.
  • the yaw / pitch autopilot is a load factor control with high dynamic performance. It comprises a conventional aerodynamic pilot, of the “PAF” type, with a time constant of the order of a few tenths of a second, associated, in accordance with the invention, with force control, of the “PIF” type, at the center of gravity, this practically fixed time, whose response time is then very short, of the order of a hundredth of a second.
  • pilot's response time is slightly lower than that of each of its components while remaining fairly close to that of the fastest.
  • the third mode which corresponds to piloting in free flight, after stopping the “PIF” device, becomes of the classic aerodynamic type.
  • the “PIF” device can be reactivated later.
  • the actual guidance includes pre-steering and autoguiding.
  • the pre-guidance is inertial, carried out from information from the center, possibly readjusted in flight every second, and data from a “strap-down” type central unit for example.
  • It comprises two stages, one of tilting during which a attitude control is carried out controlled by the “PIF” device., The other of acceleration during which the missile always controlled by the “PIF” device, the other d acceleration during which the missile still controlled by the “PIF” device is directed towards an intermediate point between the current and the future goal.
  • Autoguiding begins immediately after the release of the accelerator, which requires approximately 0.1 seconds.
  • the guidance law is pure proportional navigation with a coefficient of around 4 with correction of the deceleration of the missile in the undisturbed flight phase.
  • the increased guidance order from the output of the model 15 serves as input to the aerodynamic pilot.
  • the aerodynamic pilot's servo error serves as input to both the device 16 for controlling the "PIF" and to its operating simulator 15.
  • the “PIF” works as a vernier on the error of the “PAF” which makes it possible to obtain an overall device whose operating capacity is the sum of the operating capacity of the partial devices and whose response time is close to the response time of the fastest partial device.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Claims (3)

1. Verfahren zum Steuern der Seitwärtsbeschleunigung eines Flugkörpers, das erlaubt, eine sehr kurze Antwortzeit auf Befehle selbst großer Amplitude zu erhalten, daß die Verbindung eines aerodynamischen Steuersystems der Seitwärtsbeschleunigung mit hoher Leistung (7), genannt « PAF » und eines Schubkraft-Steuersystems (5, 6A, 6B) in der Nähe des Schwerpunktes (CG) mit mäßiger Seitwärtsbeschleunigungs-Leistung aber sehr kurzer Antwortzeit, genannt « PIF », aufweist, dadurch gekennzeichnet, daß diese Beziehung derart ist, daß ihre gemeinsame Antworf auf einen Befehl durch die Gleichung :
Figure imgb0007
gegeben sei, in der bedeutet :
Og Leitbefehl
F(p) Übertragungsfunktion des « PIF
G(p) Übertragungsfunktion des « PAF »
Fex totale, vom Flugkörper ausgeführte Beschleunigung,
Γ2 Beschleunigung des « PAF »
Γ1 Beschleunigung des « PIF »

und daß man die gewöhnliche Antwort des aerodynamischen Autopiloten G(p) Og erkennt, zu der die Antwort des « PIF », F(p)(1-G(p)) Og hinzukommt, die als Feineinstellung über den Fehler (1-G(p)) Og des « PAF derart arbeitet, daß zusätzlich und beim Vorhandensein eines konstanten Befehles und mit einer Verzögerung, die gleich der Antwortzeit des « PAF ist, das « PIF » vollständig bereit ist, um eine neue Aktion zu bewirken.
2. Vorrichtung zur Anwendung des Verfahrens bei einem Waffensystem nach Anspruch 1, dadurch gekennzeichnet, daß sie verwendet :
- ein Mittel zum vertikalen Ausstoß des Flugkörpers (11B)
- ein Mittel zur Inbetriebnahme der Schubsteuerung (5, 6A, 6B) « PIF », die eine Schwenkung durch die Tatsache der veränderten Position des Schwerpunktes (CG) vor der vollständigen Zündung des Triebswerks erlaubt
- ein Mittel zur Beschleunigung (2) des Flugkörpers (1) das während dieser Phase durch die Vorrichtung des « PIF gesteuert wird
- eine Sucheinrichtung (3) für das Zielobjekt (10), die im Fall einer Annäherung vor dem Ende der Beschleunigungsphase eine erste Korrektur der Ausrichtung des Flugkörpers (1) durch das « PIF erzeugt
- ein Mittel zur Steuerung « PIF-PAF », das
eine wieder auf die Bahn bringende Vorhaltung bewirkt, wenn die Selbststeuerung (3) keine Annäherung erreicht hat,
eine Führung (4) in Richtung auf das Zielobjekt (10) bewirkt, die die « PIF-PAF »-Steuerung zumindest in der Nähe des besagten Zielobjektes (10) benutzt
- ein Mittel, das die Verwendung des « PAF nach der Verwendung des « PIF » erlaubt, wenn Veranlassung besteht.
3. Vorrichtung zur Steuerung zur Anwendung des Verfahrens nach Anspruch 1, dadurch gekennzeichnet, daß das aerodynamische Steuerungssystem « PAF und das Schubsteuerungssystem « PIF die folgenden Elemente aufweisen :
- eine klassiche aerodynamische Seitenbeschleunigungssteuerung, die beispielsweise einen Beschleunigungsmesser (20), einen Gyrometer (18) und eine Integrationsvorrichtung (21) umfaßt,
- eine Schubsteuerung (17) mit kurzer Reaktionszeit und seine Steuerungsvorrichtung (16)
- einen Simulator (15) für das Verhalten der Schubsteuerung, der die Informationen der Schub-Steuerungsvorrichtung (16), des Gyrometers (18), des Beschleunigungsmessers (20) und eines Aufnehmers (14) empfangen kann, wobei die Anordnung dieser Elemente derart ist, daß der vom Ausgang des Simulators (15) vergrößerte leitbefehl als Eingabegröße zur aerodynamischen Steuerung dient und der Steuerungsbefehl der aerodynamischen Steuerung zugleich als Eingabegröße der Steuerungsvorrichtung (16) der « PIF »-Vorrichtung und seines Funktionssimulators (15) dient.
EP82400527A 1981-04-01 1982-03-23 Verfahren zum Steuern der Seitwärtsbeschleunigung eines Flugkörpers und entsprechendes Waffensystem Expired EP0062563B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT82400527T ATE15266T1 (de) 1981-04-01 1982-03-23 Verfahren zum steuern der seitwaertsbeschleunigung eines flugkoerpers und entsprechendes waffensystem.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8106541 1981-04-01
FR8106541A FR2503413A1 (fr) 1981-04-01 1981-04-01 Procede de pilotage en facteur de charge d'un missile et systemes d'armes correspondants

Publications (2)

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EP0062563A1 EP0062563A1 (de) 1982-10-13
EP0062563B1 true EP0062563B1 (de) 1985-08-28

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EP82400527A Expired EP0062563B1 (de) 1981-04-01 1982-03-23 Verfahren zum Steuern der Seitwärtsbeschleunigung eines Flugkörpers und entsprechendes Waffensystem

Country Status (7)

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US (1) US4465249A (de)
EP (1) EP0062563B1 (de)
JP (1) JPS5828998A (de)
AT (1) ATE15266T1 (de)
AU (1) AU544856B2 (de)
DE (1) DE3265731D1 (de)
FR (1) FR2503413A1 (de)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0222571A3 (de) * 1985-10-31 1988-05-04 British Aerospace Public Limited Company Visierlinienlenksystem für Flugkörper
GB2214749B (en) * 1988-01-29 1992-02-19 Marconi Co Ltd Radar seeker transient suppressor
US8173946B1 (en) 2008-08-26 2012-05-08 Raytheon Company Method of intercepting incoming projectile
US8058596B2 (en) * 2009-08-27 2011-11-15 Raytheon Company Method of controlling missile flight using attitude control thrusters
CN116301028B (zh) * 2023-02-09 2023-08-04 大连理工大学 基于吸气式高超声速平台的多约束在线飞行轨迹规划中段导引方法

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3072365A (en) * 1957-09-16 1963-01-08 Missile Corp Pilotless craft guidance method and means
US3695555A (en) * 1970-06-12 1972-10-03 Us Navy Gun-launched glide vehicle with a mid-course and terminal guidance control system
FR2226066A5 (de) * 1970-10-13 1974-11-08 Bodenseewerk Geraetetech
US3735944A (en) * 1971-06-25 1973-05-29 U S A Represented By Secretary Dual mode guidance and control system for a homing missile
GB1467035A (en) * 1973-05-25 1977-03-16 Messerschmitt Boelkow Blohm Attacking flying targets from a submarine
JPS5848840B2 (ja) * 1975-02-21 1983-10-31 株式会社東芝 ヒシヨウタイノ クウチユウロツクオンホウシキ
US4198015A (en) * 1978-05-30 1980-04-15 The United States Of America As Represented By The Secretary Of The Army Ideal trajectory shaping for anti-armor missiles via time optimal controller autopilot
US4277038A (en) * 1979-04-27 1981-07-07 The United States Of America As Represented By The Secretary Of The Army Trajectory shaping of anti-armor missiles via tri-mode guidance

Also Published As

Publication number Publication date
ATE15266T1 (de) 1985-09-15
JPH0457960B2 (de) 1992-09-16
US4465249A (en) 1984-08-14
DE3265731D1 (en) 1985-10-03
AU544856B2 (en) 1985-06-13
EP0062563A1 (de) 1982-10-13
FR2503413A1 (fr) 1982-10-08
FR2503413B1 (de) 1983-07-08
AU8226782A (en) 1982-10-07
JPS5828998A (ja) 1983-02-21

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