EP0535330B1 - Einrichtung zur Freigabe der Kühlmittelzufuhr in einem Flugkörper - Google Patents

Einrichtung zur Freigabe der Kühlmittelzufuhr in einem Flugkörper Download PDF

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Publication number
EP0535330B1
EP0535330B1 EP92113386A EP92113386A EP0535330B1 EP 0535330 B1 EP0535330 B1 EP 0535330B1 EP 92113386 A EP92113386 A EP 92113386A EP 92113386 A EP92113386 A EP 92113386A EP 0535330 B1 EP0535330 B1 EP 0535330B1
Authority
EP
European Patent Office
Prior art keywords
missile
control line
cooler
detector
line
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.)
Expired - Lifetime
Application number
EP92113386A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0535330A1 (de
Inventor
Horst Radscheidt
Hubert Peter Lehr
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.)
Bodenseewerk Geratetechnik GmbH
Original Assignee
Bodenseewerk Geratetechnik GmbH
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 Bodenseewerk Geratetechnik GmbH filed Critical Bodenseewerk Geratetechnik GmbH
Publication of EP0535330A1 publication Critical patent/EP0535330A1/de
Application granted granted Critical
Publication of EP0535330B1 publication Critical patent/EP0535330B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/007—Preparatory measures taken before the launching of the guided missiles

Definitions

  • the invention relates to a device for releasing the supply of coolant to a cooler for the detector of an optical viewfinder in a missile, which is arranged in a starting device attached to an aircraft.
  • captive means for capturing the movable viewfinder optics of the finder are provided, which can be unlocked via a control line led from the cockpit of the aircraft to the launching device for target tracking before the missile is deployed.
  • Target-seeking missiles are known. Such missiles contain an optical viewfinder that detects targets and provides control signals through which the missile is guided to the target.
  • the optical viewfinder generally sits on a gyro rotor and is thus decoupled from the movements of the missile.
  • the gyro rotor is gimbal-mounted and so far movable relative to the cell of the missile, so that it can be aimed at a goal.
  • An example of such an optical viewfinder is shown in DE-C-3 623 343.
  • the missiles are usually held in a launcher.
  • the starter is located on an aircraft, usually under the wings.
  • the viewfinder contains a detector which responds to infrared radiation.
  • the sensitivity of such detectors strongly depends on their temperature. It is known to cool detectors for optical viewfinders to increase sensitivity and reduce noise.
  • the invention has for its object to provide a device for releasing the coolant supply to a cooler for the detector of an optical viewfinder in a missile, which is arranged in a starting device on an aircraft, so that an additional control line for this release can be omitted.
  • the invention is based on the object of making older starting devices which do not contain a separate control line for cooling the detector suitable for use with missiles in which the detector is cooled by means of a Joule-Thomson cooler.
  • the invention is based on the knowledge that the finder must be tied down for the target acquisition and tracking only when the detector is sufficiently cooled. Before that, the detector is too insensitive anyway. As a result, the coolant supply is definitely released before releasing the restraint.
  • the control line for the bondage can therefore be used to transmit a short signal to release the coolant supply.
  • This short signal sets the bistable circuit. This opens the valve. This condition is not changed by further signals on the control line.
  • 10 denotes a cockpit of an aircraft 12.
  • a starting device 14 is attached to the aircraft.
  • the launch device 14 contains a missile 16.
  • the missile 16 is provided with a viewfinder 18.
  • the viewfinder 18 includes a detector 20.
  • the detector is cooled by a cooler 22 in the form of a Joule-Thomson cooler.
  • the cooler 22 receives a coolant from a coolant tank 24 via a controllable valve 26 and a line 28.
  • a control line 30 emerges from the cockpit 10 of the aircraft 12, through which the missile can be launched.
  • a control line 32 goes from an actuator 34 arranged in the cockpit 10 to the starting device 14.
  • a relay 36 is arranged in the starting device 14.
  • the relay 36 has a normally closed contact 38.
  • Two lines 40 and 42 are connected to one another via this normally closed contact 38.
  • the lines 40 and 42 form part of a captive circuit with a current source 44 and captive means 46.
  • the normally closed contact 38 is closed, the two leads 40 and 42 are at the same potential at a terminal of the current source 44.
  • the captive circuit is then closed and the captive means 46 keep the viewfinder optics in a fixed position.
  • the relay 36 is excited by a signal on the control line 32. Contact 38 opens. This releases the viewfinder optics.
  • the potential of the line 42 changes.
  • the line 42 is now connected to the other terminal of the current source via the restraining means 46 and is separated from the line 40.
  • the line 42 is connected to a plug 48 which establishes a connection to the seeker head 18 of the missile 16.
  • the plug 48 contains a bistable circuit 50. This circuit 50 is shown in detail in FIG.
  • the circuit 50 is a flip-flop with two N-channel MOSFET transistors 52 and 54.
  • the drain of the N-channel MOSFET transistor 52 is connected via a resistor 56 to a supply voltage of 25 volts, which is supplied via a line 58.
  • the source of the N-channel MOSFET transistor 52 is connected to the line 42 via a diode 60.
  • the drain of the N-channel MOSFET transistor 54 is connected in series via two resistors 62 and 64 to line 58 and thus to the supply voltage.
  • the source of the N-channel MOSFET transistor 54 is grounded.
  • the drain of the N-channel MOSFET transistor 52 is also connected via a resistor 66 to the gate of the N-channel MOSFET transistor 54.
  • the gate of the N-channel MOSFET transistor 54 is connected to ground via a resistor 68 and a capacitor 70 connected in parallel therewith.
  • the drain of the N-channel MOSFET transistor 54 is connected to the gate of the N-channel MOSFET transistor 52 via a resistor 72.
  • the gate of the N-channel MOSFET transistor 52 is also connected to ground via a zener diode 74.
  • connection point between resistors 62 and 64 is connected to the gate of a P-channel MOSFET transistor 76.
  • the source of the P-channel MOSFET transistor 76 is connected to line 58 and is thus connected to the supply voltage.
  • the drain of the N-channel MOSFET transistor 76 is connected to ground via a diode 78.
  • the drain of the N-channel MOSFET transistor 76 is connected to a control line 82 via a diode 80.
  • control line 82 is led to the valve 26 designed as a solenoid valve.
  • the bistable circuit is in a first switching state in which the P-channel MOSFET transistor 76 is blocked. No signal then appears on the control line 82. The valve 26 is closed.
  • the relay 36 is briefly energized by actuating the actuator 34 via the control line 32.
  • the normally closed contact 38 opens.
  • the potential of the line 42 changes accordingly briefly.
  • the bistable circuit 50 is set to its other switching state.
  • the P-channel MOSFET transistor 76 becomes conductive. This connects control line 82 to line 58 and sets it to 25 volts.
  • the valve 26 is opened via the control line 82. Coolant, typically compressed air, flows to the cooler 22. The cooler cools the detector 20 to the required low temperature. This reduces the noise and increases the sensitivity of the detector. The pilot recognizes this by the decreasing noise in the "Missile Audio" signal.
  • the relay 36 can be continuously excited by continuous actuation of the actuator 34.
  • the normally closed contact 38 also constantly opens and releases Restraining the viewfinder optics by turning off the restraining means 46.
  • this changeover no longer has any influence on the switching state of the bistable circuit 50. Accordingly, the valve 26 also remains open for the coolant.
  • a single control line 32 is thus used for two circuits, namely the release of the coolant supply to the cooler 22 and the switching on and off of the restraint means 46 for the viewfinder optics.
  • missiles with Joule-Thomson cooling of the detector can also be used with launch devices that do not have a separate control line for releasing the coolant.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP92113386A 1991-09-21 1992-08-06 Einrichtung zur Freigabe der Kühlmittelzufuhr in einem Flugkörper Expired - Lifetime EP0535330B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4131529 1991-09-21
DE4131529A DE4131529C2 (de) 1991-09-21 1991-09-21 Einrichtung zur Freigabe der Kühlmittelzufuhr in einem Flugkörper

Publications (2)

Publication Number Publication Date
EP0535330A1 EP0535330A1 (de) 1993-04-07
EP0535330B1 true EP0535330B1 (de) 1995-10-25

Family

ID=6441201

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92113386A Expired - Lifetime EP0535330B1 (de) 1991-09-21 1992-08-06 Einrichtung zur Freigabe der Kühlmittelzufuhr in einem Flugkörper

Country Status (5)

Country Link
EP (1) EP0535330B1 (xx)
DE (2) DE4131529C2 (xx)
ES (1) ES2081530T3 (xx)
GR (1) GR3018151T3 (xx)
TR (1) TR26282A (xx)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4226024C1 (xx) * 1992-08-06 1993-07-15 Bodenseewerk Geraetetechnik Gmbh, 7770 Ueberlingen, De
US10105437B2 (en) 2004-04-28 2018-10-23 Btg International Limited Epitopes related to coeliac disease

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4429611A (en) * 1982-01-29 1984-02-07 General Dynamics, Pomona Division Airborne missile launcher
DE3327384A1 (de) * 1983-07-29 1985-02-07 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Visiersystem fuer einen lenkflugkoerper
DE3611206A1 (de) * 1986-04-04 1987-10-08 Bodenseewerk Geraetetech Vorrichtung zum kuehlen eines detektors, insbesondere bei einem optischen sucher
DE3623343C1 (de) * 1986-07-11 1989-12-21 Bodenseewerk Geraetetech Optischer Sucher mit Rosettenabtastung
DE3642683A1 (de) * 1986-12-13 1988-06-16 Bodenseewerk Geraetetech Kryostat zur kuehlung eines detektors

Also Published As

Publication number Publication date
DE59204122D1 (de) 1995-11-30
EP0535330A1 (de) 1993-04-07
DE4131529C2 (de) 1994-03-31
GR3018151T3 (en) 1996-02-29
DE4131529A1 (de) 1993-04-01
TR26282A (tr) 1995-02-15
ES2081530T3 (es) 1996-03-16

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