EP0368738A1 - Verfahren und Vorrichtung zur Programmierung einer äusseren oder integrierten Ladung mittels einer drahtlosen Verbindung in einem sie tragenden Fahrzeug - Google Patents

Verfahren und Vorrichtung zur Programmierung einer äusseren oder integrierten Ladung mittels einer drahtlosen Verbindung in einem sie tragenden Fahrzeug Download PDF

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Publication number
EP0368738A1
EP0368738A1 EP89403048A EP89403048A EP0368738A1 EP 0368738 A1 EP0368738 A1 EP 0368738A1 EP 89403048 A EP89403048 A EP 89403048A EP 89403048 A EP89403048 A EP 89403048A EP 0368738 A1 EP0368738 A1 EP 0368738A1
Authority
EP
European Patent Office
Prior art keywords
load
data
programming
vehicle
source
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
EP89403048A
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English (en)
French (fr)
Other versions
EP0368738B1 (de
Inventor
André Moreau
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.)
MATRA DEFENSE
Original Assignee
MATRA DEFENSE
Societe des Telephones Ericsson 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 MATRA DEFENSE, Societe des Telephones Ericsson SA filed Critical MATRA DEFENSE
Publication of EP0368738A1 publication Critical patent/EP0368738A1/de
Application granted granted Critical
Publication of EP0368738B1 publication Critical patent/EP0368738B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C17/00—Fuze-setting apparatus
    • F42C17/04—Fuze-setting apparatus for electric fuzes

Definitions

  • the present invention relates to the transmission of programming data from a carrier vehicle, and in particular from an aircraft, to an external or integrated load.
  • the present invention aims in particular to provide a method of transmitting data which meets the requirements of practice better than those known in the past, in particular in that it uses only moderate price means and of small footprint, allows verifications ( tests) once the load is placed under the pylon and allows the load to be implemented at any time without any programming delay being required.
  • the invention provides a method of transmitting programming data according to the whole of claim 1.
  • the separation can be ordered at any time.
  • the invention finds a particularly important, although not exclusive, application in the transmission of data between an aircraft and an external military load to which programming update data is repeatedly addressed.
  • the programming data to be transmitted have a low dynamic range and can therefore be represented by a short data word, so that a high data refresh rate remains compatible with the limits on the bit rate imposed by a simple and inexpensive optical source, for example a light-emitting diode (LED). It is however possible, when a high refresh rate is required and / or complex data (high dynamic range required) to be transmitted, to use a laser diode as the emission source.
  • a simple and inexpensive optical source for example a light-emitting diode (LED).
  • Programming data can be trans put in the form of messages whose structure and format are compatible with those of messages transmitted by existing buses in carrier vehicles. This compatibility can be achieved by means of an appropriate coding-decoding means.
  • One can in particular transmit the data in the form of messages all having the same duration, comprising a header, a data word, and error control bits.
  • the transmitted data can correspond to several types of charges insofar as each message includes an identification address specific to a type of charge and the latter comprises means making it possible to select the information data intended for it.
  • the method can be implemented unidirectionally; it can also operate in duplex, provided that a transmitter with a source on the load and a receiver with a sensor on the carrier vehicle are also provided.
  • the load transmitter can in particular repeat the programming data received, for verification by comparison in the carrier vehicle.
  • the transmitter carried by the load can also be programmed so as to cause the source to transmit to the carrier vehicle, a specific identification word of the load allowing a computer mounted in said vehicle to take into account the characteristics of the in charge of developing the programming data supplied to the latter.
  • the invention also provides a device for programming a load making it possible to implement the method defined above, according to claim 7.
  • the method according to the invention is used to transmit, from an aircraft 10 to an external load 12 constituted by a braked bomb (FIG. 1), programming data representing the time interval between the separation of the load, caused by the pilot, and the command to deploy a parachute.
  • the load 12 is mounted under a pylon 14 comprising an ejector 16 to which the load is attached.
  • Figure 2 shows a possible mounting of the transmitting source 32 carried by the aircraft and the sensor 34 of the receiver carried by the load.
  • the source 32 constituted for example by a current type light-emitting diode, is mounted in the pylon 14 behind a window 36 flush with the underside of the pylon.
  • the sensor 34 which will generally be a photodiode having a sensitivity range adapted to the wavelength of the source 32, is similarly mounted on the load, possibly behind a filter adapted to the emission wavelength of the source 32.
  • a flexible sleeve 38 can be fixed to the pylon 14 in order to delimit a protected space around the path of transmission. If this transmission is by diffusion, and not in the form of a directed beam, it is not necessary that the source 32 and the sensor 34 are perfectly aligned. In this case, this makes it possible in particular to mount, on a given pylon 14, loads having different constitutions and on which the position of the sensor can vary, from one load to another, relative to a given reference (position of the transmitter on the pylon).
  • a precision of 1 / 100th of a second on the value to be transmitted of the time interval between the release of the load and the opening of the parachute is largely sufficient.
  • a data word of twelve useful bits, the least significant bit of which represents 10 ms, makes it possible to represent a delay of up to forty seconds, greater than all the values currently necessary in practice.
  • the messages transmitted can comprise thirty-two bits so as to be directly compatible with the words provided for by existing aeronautical standards and have the format shown in Figure 3.
  • the message has a header 20 of eight bits, a useful area 22 of twenty-one bits, composed of a word 24 of information of sixteen bits and a reserved part of five bits, two bits 28 of validity check and one bit of parity 30.
  • a modulation frequency of 6.4 kHz for example which can be obtained without difficulty with low-cost infrared sources, such as light-emitting diodes or LEDs, is sufficient to transmit the thirty-two bits of the message. in 5 ms. However, it would be possible to use a source and a sensor that could operate at much higher frequencies if the data rate to be transmitted exceeded the possibilities offered by an LED.
  • the load 12 is also provided with an emission source 60 and the pylon is then provided with a sensor 64, which makes it possible to transmit information from the load to the aircraft and thereby achieve a dialogue between the load and the carrier vehicle.
  • the sources and the sensors will be identical, which requires working in alternation. But this condition is not in practice a problem for most applications: in the case, mentioned above, of thirty-two bit messages having a duration of 5 ms, it is possible to adopt a refresh rate of 50 Hz, reserving an interval of 5 ms between each transmission for the return transmission which follows it.
  • the source and the sensor carried by the pylon 14 can be placed side by side, with an interval corresponding to that of the sensor and the source carried by the load.
  • Flexible sleeves can be provided to isolate each path from the other.
  • the transmission device comprises a transceiver mounted in the pylon and connected to a computer 40 placed in the carrier vehicle, generally by means of a modem (not shown in the Figure 4).
  • the transceiver comprises a pilot oscillator 42 constituting a time base, at 6.4 kHz for example in the case considered above, and a generator of frame 44 intended to supply, in response to an order received from a control logic 46, a message whose frame is that shown in FIG. 3.
  • the generator 44 includes a header memory intended to indicate the type of load to which the transmitted parameters apply.
  • the generator can also be provided to generate the control bits and the parity bit.
  • the message transmitted then has the following constitution: - eight-bit identification header or 'label'; - information data intended to program the load (sixteen bits); - five-bit placeholder: - control (two bits); - parity (one bit).
  • the message described above by way of example is transmitted from the carrier pylon to the load by air using an infrared type connection according to the wavelength specified in the example (0.83 ⁇ m).
  • the receiver carried by the load comprises, from the sensor 34, a decoder 48 programmed so as to check the consistency of the message, in particular by using the control word and the parity bit, to decode it and to transmit the data obtained to a buffer memory 50 whose read access 52 is connected to the electronic circuits 72 for using the information, advantageously by means of an opto-electronic coupler of galvanic isolation 53.
  • the transmitter carried by the load comprises a pilot oscillator 54 which may have the same constitution as the oscillator 42.
  • This oscillator drives a generator 56 of report messages, intended to generate a frame identical to that shown in FIG. 2 and comprising: - an eight-bit header; a message of sixteen bits, constituted by the copying of the decoded information coming from the decoder 48; a five-bit load identification word, stored in the generator 56 or supplied by a separate read only memory 58; - two bits of message validity, and - a parity bit.
  • the message to be transmitted is transmitted by the source 60 on reception of an order supplied by a control logic 62 which maintains the interval of 5 ms required between the end of the reception of a message from the aircraft and the start message log.
  • This report message is transmitted from the load to the carrier pylon by air using an infrared type link.
  • the sensor 64 carried by the pylon is intended to receive the messages coming from the load; it attacks a decoder 66, similar in constitution to that of decoder 48, and provides a load identification word on a first output 68 and a validation word (in the event of coincidence between the information transmitted to the load and the feedback) on exit 70.
  • the transceiver mounted in the pylon can be supplied from the general electrical circuit of the aircraft, generally at 28 Volts DC.
  • a source of electrical power of low power sufficient to operate the data transmission circuits; this source, generally constituted by a low power battery, is implemented before takeoff of the aircraft, for example by removal of a safety pin placed on the load.
  • the much greater energy required for implementation electronic circuits and the priming chain, for example to control the opening of a parachute, is supplied separately by a battery which is only put into Orservice when dropping, for example by a tearing strap or order a contact. Until then the priming chain remains inert.
  • the pylon contains a microprocessor card 74 fulfilling the functions of frame generation and coding-decoding, connected by a modulator 76 to the transmission source 32 and by a demodulator 78 to the receiver 64.
  • the card 74 is connected, by a coupler 77 and a connector 79, to the bus 80 of the carrier vehicle ensuring the connection with the on-board computer.
  • the load for its part, contains a microprocessor card 82 connected respectively to the receiver 34 and to the transmitter 60 by a demodulator 84 and a modulator 86. It fulfills the functions of the members 50, 48, 54 and 62 of FIG. 4 It is connected by an opto-electronic coupler 53 to the electronic circuits 72 for implementing the load.
  • the load includes an autonomous supply.
  • This power supply includes a low power source 88, constituted for example by a lithium battery, which is connected to the circuits carried by the load before the start of the mission, for example by removal of an opening pin of a switch. 90.
  • the power necessary for implementing the electronic circuits 72 and the activation chain is supplied by a high power source 94, brought into service when the load is separated.
  • this battery can be controlled by a switch 92 which opens during the separation.
  • the switch also makes it possible to provide a drop top to the microprocessor card 82 and then to cause, with the possible delay necessary for the source 72 to supply its operating voltage, the transfer of the data.
  • the source 94 can in particular be a thermal battery, supplying a voltage greater than a minimum which is itself lower than the maximum voltage which the source 88 can supply.
  • the microprocessor card 82 receives, controls, validates and stores the data coming from the carrier vehicle, and this almost permanently. Upon receipt of the drop signal, the card 82 transmits to circuits 72 the latest information received and validated, stored in the RAM of the microprocessor.
  • FIG. 6 shows a possible arrangement of the components which have just been described. All of the electronic components carried by the pylon constitute a module 96 connected to the bus by the connector 78. The components carried by the load 12 can be grouped in a second module 98 carrying the receiver 34 and possibly the transmitter 60.
  • the invention is susceptible of numerous variant embodiments.
  • the principle of a unidirectional double link can be adopted.
  • the transceiver mounted in the pylon can be provided to transmit, according to a determined repetition sequence, messages having different headers and each corresponding to a type dump.
  • the load transceiver will include header recognition means, making it possible to take into account only the messages being sent to it. actually intended.
  • the invention is capable of numerous applications and can be used on vehicles of very varied types. In all cases, the invention makes it possible to transmit the information with a space-saving device, capable of being housed in locations provided for the power supply connectors of many adapters; the device is very flexible and makes it possible to transmit very diverse parameters; the device does not require precise alignment of components when mounting the load. Finally, it allows without major difficulties to re-equip existing loads.
  • the invention can be applied, as a priority, by way of nonlimiting examples, to droppable loads with a view to transmitting orders such as: choice of trajectory, opening of parachute (s), cocking of rockets , ejection of submunitions ...
  • the invention can be applied to all types of missiles, on board an aircraft (air-to-air, air-to-ground missiles ...) or not (missiles ground-ground, ground-air, sea-sea etc ...) as well as torpedoes or even shells.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Optical Communication System (AREA)
  • Stored Programmes (AREA)
EP19890403048 1988-11-07 1989-11-06 Verfahren und Vorrichtung zur Programmierung einer äusseren oder integrierten Ladung mittels einer drahtlosen Verbindung in einem sie tragenden Fahrzeug Expired - Lifetime EP0368738B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8814497A FR2638922B1 (fr) 1988-11-07 1988-11-07 Procede et dispositif de programmation, par voie aerienne, d'une charge externe ou integree a partir d'un vehicule porteur
FR8814497 1988-11-07

Publications (2)

Publication Number Publication Date
EP0368738A1 true EP0368738A1 (de) 1990-05-16
EP0368738B1 EP0368738B1 (de) 1993-06-09

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP19890403048 Expired - Lifetime EP0368738B1 (de) 1988-11-07 1989-11-06 Verfahren und Vorrichtung zur Programmierung einer äusseren oder integrierten Ladung mittels einer drahtlosen Verbindung in einem sie tragenden Fahrzeug

Country Status (4)

Country Link
EP (1) EP0368738B1 (de)
DE (1) DE68907022T2 (de)
ES (1) ES2041026T3 (de)
FR (1) FR2638922B1 (de)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0432902A2 (de) * 1989-11-15 1991-06-19 Hughes Aircraft Company Verfahren und Vorrichtung für einen wiederprogrammierbaren Programmspeicher eines Flugkörpers
FR2687260A1 (fr) * 1992-02-12 1993-08-13 Telecommunications Sa Procede de transmission de donnees par faisceau optique entre un vehicule porteur et sa charge et dispositif pour la mise en óoeuvre du procede.
EP0592948A1 (de) * 1992-10-16 1994-04-20 Daimler-Benz Aerospace Aktiengesellschaft Verfahren zur autonomen Lagesteuerung von Lenkflugkörpern
EP1306644A2 (de) * 2001-10-25 2003-05-02 Rheinmetall Landsysteme GmbH Verfahren zur Temperierung einer Munitionseinheit sowie temperierbare Munitionseinheit
US6823767B2 (en) 2001-10-24 2004-11-30 Rheinmetall Landsysteme Gmbh Method for fuze-timing an ammunition unit, and fuze-timable ammunition unit

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5681008A (en) * 1996-09-26 1997-10-28 Boeing North American, Inc. Remote identification, location and signaling response system
US6057949A (en) * 1997-08-07 2000-05-02 The Boeing Company Bi-directional infrared communications system

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3228337A (en) * 1962-12-04 1966-01-11 Rodney E Grantham Radio frequency free communication system
US4091734A (en) * 1977-02-22 1978-05-30 The United States Of America As Represented By The Secretary Of The Navy Aircraft to weapon fuze communication link
WO1984004157A1 (en) * 1983-04-11 1984-10-25 Commw Of Australia Programmable electronic delay fuse
DE3411439C1 (de) * 1984-03-28 1985-09-19 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Absetzverfahren für Lenkflugkörper
US4597345A (en) * 1984-10-29 1986-07-01 The United States Of America As Represented By The Secretary Of The Navy Torpedo cableless umbilical

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3228337A (en) * 1962-12-04 1966-01-11 Rodney E Grantham Radio frequency free communication system
US4091734A (en) * 1977-02-22 1978-05-30 The United States Of America As Represented By The Secretary Of The Navy Aircraft to weapon fuze communication link
WO1984004157A1 (en) * 1983-04-11 1984-10-25 Commw Of Australia Programmable electronic delay fuse
DE3411439C1 (de) * 1984-03-28 1985-09-19 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Absetzverfahren für Lenkflugkörper
US4597345A (en) * 1984-10-29 1986-07-01 The United States Of America As Represented By The Secretary Of The Navy Torpedo cableless umbilical

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0432902A2 (de) * 1989-11-15 1991-06-19 Hughes Aircraft Company Verfahren und Vorrichtung für einen wiederprogrammierbaren Programmspeicher eines Flugkörpers
EP0432902A3 (en) * 1989-11-15 1991-07-31 Hughes Aircraft Company Method and apparatus for a reprogrammable program missile memory
TR25985A (tr) * 1989-11-15 1993-10-07 Hughes Aircraft Co Tekrar programlanabilir programli füze hafizasi icin usul ve cihaz.
FR2687260A1 (fr) * 1992-02-12 1993-08-13 Telecommunications Sa Procede de transmission de donnees par faisceau optique entre un vehicule porteur et sa charge et dispositif pour la mise en óoeuvre du procede.
EP0592948A1 (de) * 1992-10-16 1994-04-20 Daimler-Benz Aerospace Aktiengesellschaft Verfahren zur autonomen Lagesteuerung von Lenkflugkörpern
US6823767B2 (en) 2001-10-24 2004-11-30 Rheinmetall Landsysteme Gmbh Method for fuze-timing an ammunition unit, and fuze-timable ammunition unit
EP1306644A2 (de) * 2001-10-25 2003-05-02 Rheinmetall Landsysteme GmbH Verfahren zur Temperierung einer Munitionseinheit sowie temperierbare Munitionseinheit
EP1306644A3 (de) * 2001-10-25 2003-07-16 Rheinmetall Landsysteme GmbH Verfahren zur Temperierung einer Munitionseinheit sowie temperierbare Munitionseinheit

Also Published As

Publication number Publication date
EP0368738B1 (de) 1993-06-09
DE68907022D1 (de) 1993-07-15
ES2041026T3 (es) 1993-11-01
DE68907022T2 (de) 1993-09-16
FR2638922B1 (fr) 1994-04-29
FR2638922A1 (fr) 1990-05-11

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