EP2767795A2 - Procédé de fonctionnement d'une missile stationaire - Google Patents

Procédé de fonctionnement d'une missile stationaire Download PDF

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Publication number
EP2767795A2
EP2767795A2 EP14000284.1A EP14000284A EP2767795A2 EP 2767795 A2 EP2767795 A2 EP 2767795A2 EP 14000284 A EP14000284 A EP 14000284A EP 2767795 A2 EP2767795 A2 EP 2767795A2
Authority
EP
European Patent Office
Prior art keywords
missile
control unit
unit
data
transmitting
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.)
Withdrawn
Application number
EP14000284.1A
Other languages
German (de)
English (en)
Other versions
EP2767795A3 (fr
Inventor
Stephan Truckenbrodt
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.)
Diehl Defence GmbH and Co KG
Original Assignee
Diehl BGT Defence GmbH and Co KG
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 Diehl BGT Defence GmbH and Co KG filed Critical Diehl BGT Defence GmbH and Co KG
Publication of EP2767795A2 publication Critical patent/EP2767795A2/fr
Publication of EP2767795A3 publication Critical patent/EP2767795A3/fr
Withdrawn legal-status Critical Current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
    • F42B35/00—Testing or checking of ammunition
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/06—Rocket or torpedo launchers for rockets from aircraft
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/01—Arrangements thereon for guidance or control
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/055—Umbilical connecting means

Definitions

  • the invention relates to a method for operating a stationary missile, in which an operating device is signal-technically connected to a control unit arranged in the stationary missile, which is prepared for controlling operating functions, and data is exchanged between the operating unit and the control unit.
  • a field test instrument providing the necessary infrastructure is connected to it via the operational interface of the missile missile.
  • the field test device sends corresponding control data to a control unit in the rocket missile, so that it performs, for example, a so-called build-in test (BIT). Resulting result data from the test are transmitted to the field device for evaluation. In this way, an update to the control unit of the missile missile can be installed or other software changes are made to the control unit.
  • BIT build-in test
  • control unit is connected via a line to a transmitting and receiving unit and the data between the control unit and the operating unit are transmitted wirelessly by the transmitting unit.
  • a dormant missile in the present case is not only stored for example in a (weapons) depot or stored in a manufacturing facility missile understood, but also on a movable or immovable platform directly or indirectly -. B. via a launcher - mounted missile.
  • the invention is based on the consideration that a test of a missile is sensible or necessary in addition to the depot before its use, in which the missile is already connected to a starting device, for example a launcher on an aircraft.
  • the operating interface of the missile is occupied by the connection to the launcher.
  • the interface on the missile is not freely accessible at a state attached to the launcher.
  • the missile must be released from the launcher, placed in a suitable location, and connected to the tester. This procedure is expensive.
  • By providing the wireless interface can be dispensed with the connection of the field tester to the operational interface of the missile.
  • a data exchange can take place directly between the control unit and the operating device wirelessly while the missile is attached to the starting device and connected via its operative interface with the starting device.
  • the missile is expediently a rocket-propelled missile and in particular a combat missile, such as a ground-to-air missile or an air-to-air missile.
  • the operation of the missile may be a maintenance operation, performed in the maintenance of the missile and the missile is activated accordingly, for example, maintenance data is exchanged between the missile and the control unit.
  • the operation may be a data exchange operation for exchanging data between the HMI device and the control unit.
  • a test operation and / or an operational operation of the missile are also possible.
  • the transmitting and receiving unit is prepared to enable bidirectional data exchange.
  • the transmitting and receiving unit can be arranged in the stationary missile, so that the line between the control unit and transmitting and receiving unit is completely arranged in the missile.
  • the missile usually stores in a storage container or canister in which the missile is mounted.
  • the operational interface with a corresponding interface of the container, canister or other suitable storage container, hereinafter referred to collectively referred to as a container be connected.
  • the transmit and Receiving unit to be part of the container so that it can be dispensed with the provision of a transmitting and receiving unit in the missile.
  • the line between the control unit and the transmitting and receiving unit can in this case comprise a data cable between the missile and a container in which the missile is mounted.
  • the line is conveniently a data line, e.g. a wiring, wherein instead of a wire and other materials are possible, such as glass fiber o. ⁇ ., And fall under the concept of a wiring or a connection via wire.
  • the operating device is advantageously a mobile operating device or an operating device that includes at least one mobile device.
  • the mobile operating device or the mobile device is a small computer for carrying in the hand. Suitable is a tablet computer or smartphone, whereby the use of consumer electronics is favorable. Due to the high availability of consumer electronics and their high volume, it is cheap in procurement, maintenance, repair and maintenance costs. Conveniently, the weight of the mobile control device is limited to two kilograms, in particular to only 500 g.
  • the operating device is designed in several parts and at least part of the operating device is mobile.
  • the parts of the operating device are connected by signal technology, z. B. via a wire or wirelessly.
  • the one or more non-mobile parts of the operating device can be conveniently mounted in or on the platform by, for example, inserted into a drawer or fixed or integrated into existing facilities. If the platform is, for example, an aircraft and the operator is a pilot, then it can be provided that the operating device comprises as a part a device for switching on / off and firing the missile, which z. B.
  • the data exchange with the missile can be done via the device, the helmet and / or another part of the HMI device.
  • the control unit of the missile serves to control the operating functions of the missile.
  • a preparation can be provided by a corresponding control program or a plurality of control programs of the control unit, whose or their sequence - for example in conjunction with suitable input signals, such as sensor signals - causes such a control.
  • the control unit expediently comprises electronic elements, such as a processor and data memory, which are necessary for running the control program or the control programs.
  • the transmitting and receiving unit is a short-range transmitting and receiving unit.
  • Modern guided missiles are equipped with radio transmitters that transmit operation data, for example reconnaissance data or flight condition data, to a ground station over long distances. From the ground station corresponding control signals for controlling the flight operation of the missile are sent to this and received by the missile.
  • Such transmitter in missiles are operated by the internal power supply of the missile, which is naturally limited in their life, especially because of the high power of the transmitter.
  • Such a transmitter is therefore activated only after the start of the missile and is fundamentally unsuitable for the transmission of, for example, maintenance data. Not only does this limit the life of the missile's power supply and thus the functionality of the missile, but also because the transmit power is designed to bridge distances over many kilometers.
  • Short-range transmitting and receiving unit is understood to mean a transmitting and receiving unit with a maximum transmitting power of 500 mW, in particular a maximum of 125 mW. This data transmission in a close range of a maximum of 300 m in the open area and good helical antenna, in particular only 100 m in free space with a conventional antenna and commercial receiver is possible.
  • the transmitting and receiving unit transmits on a frequency that is provided for the short-range data transmission and in particular allowed.
  • a frequency may be an approved WiFi frequency, a WLAN frequency, a Blue-Tooth frequency or a frequency in the infrared spectral range.
  • Other transmitting and receiving units are not disturbed and the retrievability of the test data is limited to a small circumference.
  • the wirelessly transmitted data is sent in a short-range protocol, that is to say in a transmission protocol, which is usually used for the transmission of short-range data. This can be a WiFi protocol, a WLAN protocol, a Blue-Tooth protocol or a protocol used for infrared interfaces.
  • the operation is a maintenance operation.
  • An operator who expediently resides in the field of vision of the missile, can activate a maintenance mode of the control unit via the operating device.
  • a test eg.
  • the operator may send corresponding data for initiating a test, for example a build-in test, with his operating units to the transmitting and receiving unit, so that the control unit carries out the corresponding test.
  • data relating to a test carried out by the control unit of components of the missile can be sent to the operating unit via the transmitting and receiving unit.
  • Test routines may be performed or a status of the missile or a component of the missile may be read.
  • an error memory can be read out and, for example, overwritten, log files or test data can be read.
  • the implementation of a reconfiguration or even reprogramming for example by updating the control unit or its software.
  • the transmitting and receiving unit is supplied with operating energy from outside the missile.
  • the missile or container - depending on where the transmitting and receiving unit is arranged expediently a connection for the transmission of operating energy.
  • the control unit expediently also for the supply of the control unit with operating energy.
  • the missile is arranged, for example, in a container, such as a storage container, the power supply of the transmitting and receiving unit and / or the control unit of the missile expediently takes place via a power connection of the container. Power supply and data transmission to the missile carried by the wireless data transmission thus expediently via different interfaces.
  • an operator activates a power supply from the outside to the transmitting and receiving unit and expediently also to the control unit.
  • a cable can be placed on the missile or the container and a power supply can be turned on.
  • an operation is started by the transmitting and receiving unit and control unit and the data exchange is started.
  • additional supply lines can be attached to the container or directly to the missile. If, for example, a cooling test is to be carried out, cooling by cooling gas, it is expedient to apply a gas connection to the container or directly to the missile.
  • the method according to the invention is particularly advantageously applicable in the evaluation of flight tests.
  • the missile is attached to an aircraft, such as a launcher, and undertakes a training flight with the aircraft.
  • a warhead of the missile is replaced by a test unit or recorder unit, which is prepared for recording flight data.
  • the data stored in the test unit can be read out wirelessly via the transmitting and receiving unit and the operating device.
  • the missile can remain attached to the aircraft while the data is transmitted wirelessly.
  • the operator is standing next to the aircraft, holding the HMI device, and entering the appropriate commands to read the data into it.
  • the power supply for the transmitting and receiving unit takes place expediently via the aircraft.
  • the flight or test data may be flight data of the aircraft and are conveniently data transferred via a data bus of the aircraft, for example to the recorder unit. Also data to the new Configuration or reprogramming may be communicated in this state to the transmitting and receiving unit, which transmits this data to a unit of the missile or aircraft.
  • the flight data for example via a training flight
  • the flight data are stored in a unit of the aircraft and sent from this unit via the transmitting and receiving unit to the operating unit.
  • the transmitting and receiving unit can in this case be arranged in the aircraft, in the launcher or in the missile.
  • the transmitting and receiving unit in the missile for example, in the recorder unit
  • the arrangement in a wing or other component of the aircraft is advantageous, for example at an information distribution unit of the aircraft, for example connected to a weapon bus, e.g. the so-called MILBUS, is connected.
  • MILBUS weapon bus
  • the transmitting and receiving unit is arranged, for example, in a wired data connection between the control unit and a unit of the starting device or a carrier such as the aircraft.
  • a platform is possible, for. B. a floating or land based platform.
  • the platform is designed in particular as a vehicle, for example as a ship or as an underwater vehicle or as a land vehicle, for example in the form of a truck.
  • a land-based platform it may, for. B. also act as a ground-based, fixed installation - like a container located on a substrate.
  • the operational operation may be a combat operation or a practice operation for practicing a combat operation. Under such a training operation may also be a simulation operation for simulating a combat operation or practice operation fall.
  • the control unit is transmitted by the operating unit via the transmitting and receiving unit operation data for operational operation of the missile.
  • the operating unit transmits simulation data to the control unit.
  • the control unit can be simulated, for example, a starting device.
  • An operational operation for example a start or the preparation of a take-off, can be simulated and the missile can be tested in its behavior, for example.
  • the operating unit transmits simulation data to the control unit with which operating conditions are simulated to the control unit, for example a flying state of the missile. In this way, the missile or its functions can be tested.
  • the operating unit transmits data to the control unit for carrying out a functional test and the control unit transmits result data of the functional test to the operating unit.
  • a functional test for example, the startup of a computer of the missile, the mobility of rudders and / or control surfaces of the missile or the functions of a seeker head unit of the missile can be tested.
  • control unit controlling, for example initiating, setting up or modifying this weapon function.
  • the missile can indeed be attached to the aircraft and carried and launched by this, a data transmission to the pilot of the aircraft or another crew member of the aircraft is not possible in any desired manner, as appropriate Data connections or protocols are not established.
  • This problem can be solved by operating the operating device from the aircraft on which the missile is arranged.
  • operation data for the deployment of the missile can be sent by the crew member via the operating device to the control unit of the missile before the operation.
  • state data of the missile can be read out.
  • the invention can be modified so that the method instead of the operation of a dormant missile operation of an aircraft mitbewegten missile is carried out, the missile is thus attached to the aircraft.
  • the control unit is arranged in accordance with entrained missile.
  • the method then refers to an operation of a missile carried on a platform, which platform may conveniently be a vehicle, such as an aircraft, a land vehicle, or a maritime vehicle.
  • the operating device is operated from an aircraft on which the missile is arranged, and sensor data generated by the missile is sent from the control unit to the operating device.
  • an image generated by an optical unit of the missile can be given to a display means of a crew member of the aircraft, which is expediently integrated on the operating device. If there is an interface between the operating device and a display device of the aircraft, then the image or the sensor data generally generated by the missile or data derived therefrom can be displayed on the display device of the aircraft.
  • the invention is directed to a missile system having a missile comprising a control unit for controlling operating functions of the missile, a holding unit, on which the missile is held, and a transmitting and receiving unit, which is connected via a line to the control unit.
  • the line is an objective line, z. B. a signal line.
  • the transmitting and receiving unit comprises a short-range transmitter for wireless transmission of signals.
  • the transmitting and receiving unit and advantageously also the control unit are advantageously prepared for transmission in a local area protocol and / or in a local area frequency, such as WiFi, WLAN, blue-tooth or infrared.
  • the transmitting and receiving unit is prepared to transmit with a health-compatible transmission energy, expediently with a maximum transmission power of 500 mW, in particular a maximum of 125 mW.
  • the missile system expediently comprises a mobile operating device designed as a handheld device, which is prepared for data exchange with the transmitting and receiving unit. Maintenance and operation functions can be performed and checked very easily.
  • the transmitting and receiving unit is arranged in an objective data connection between an interface, which is prepared for connection to a control means of a missile carrier, and the control unit of the missile.
  • a data traffic between the control means, such as an aircraft, and the control unit of the missile can be tapped and sent at least partially by the transmitting and receiving unit to the operating unit.
  • Fig. 1 shows a missile system 2a with a missile 4, which is held in a holding unit 6a in the form of a container for supporting the missile 4 to three bearing elements 8.
  • the missile 4 is a ground-to-air missile comprising a rocket engine, control vanes 10, a seeker head 11, a warhead 12 and a control unit 14 for controlling the operation of the missile 4.
  • Such operation may be a maintenance operation, a trial operation or an operational operation in which the missile 4, which is still attached to a platform, is instructed to be ready to launch and, in particular, already trained for a target.
  • the missile 4 is permanently stored in the holding unit 6a and parked for example in a weapons depot.
  • an external power supply 16 is connected via a power cable 18 to an interface 20 of the holding unit 6a.
  • the interface 20 is a plug connection for plugging in a plug of the power cable 18 from the outside and a cable from the inside, which connects an operational interface 22 of the missile 4 with the container interface 20.
  • the control unit 14 is connected to the operational interface 22 and thus to the external power supply 16.
  • a gas connection may be provided on the holding unit 6a for carrying out a cooling test, by means of which cooling gas can be conducted externally to the missile 4.
  • the control unit 14 is connected via a line 24 to a transmitting and receiving unit 26a, which is presently arranged in the region of the seeker head 11, but also an arrangement in the warhead 12 is possible.
  • the line 24 is both a power line and a data line.
  • the transmitting and receiving unit 26a is supplied with power from the external power supply 16 via the control unit 14.
  • the transmitting and receiving unit 26a is a WLAN router with a transmission power of 80 mW, so that data can be received within a radius of a maximum of 50 m from a commercially available WLAN receiver.
  • the control unit 14 and the transmitting and receiving unit 26a is activated so that a wireless data connection to the WLAN router can be established.
  • This wireless data connection is closed by a control unit 28, which holds an operator in the hand by standing next to the container with the missile 4.
  • the data connection between the Transmitting and receiving unit 26a and the control unit 28 and thus also between the control unit 28 and the control unit 14 made.
  • the operator now activates a maintenance mode of the control unit 14 via the operating unit 28 and initiates a maintenance operation. This may include performing an in-flight build-in test and reading test data.
  • an error memory can be read out, a status of the missile 4 can be recorded and / or log files can be read.
  • the control unit 14 can be reconfigured and / or reprogrammed.
  • the holding unit 6a in this case the storage container, includes its own transmitting and receiving unit 26b, which is part of the holding unit 6a.
  • This is suitably connected via a cable 30 to the missile 4, for example via the interface 20 and the cable to the operational interface 22 of the missile 4 and on to the control unit 14.
  • a cable 30 to the missile 4, for example via the interface 20 and the cable to the operational interface 22 of the missile 4 and on to the control unit 14.
  • In is the cable connection between the operative interface 22 of the missile 4 and the Interface 20 of the container, a data line for transmitting data from the control unit 14 to the transmitting and receiving unit 26 b.
  • the transmitting and receiving unit 26b is also connected to the power supply 16 via the interface 20.
  • the maintenance operation can be carried out as described above, with the difference that the data is not transferred from the control unit 14 via the data line 30 to the transmitting and receiving unit 26a but to the transmitting and receiving unit 26b and from there to the operating unit 28.
  • the transmitting and receiving unit 26b can also be designed as a WLAN router.
  • the advantage can be achieved that the transmission shield of the holding unit 6a is bypassed by the transmitting and receiving unit 26a and reliable data connection with the control unit 28 can be constructed.
  • the antenna 32 is also connected via a data line to the transmitting and receiving unit 26a or 26b.
  • FIG. 2 Another embodiment is in Fig. 2 shown.
  • the missile 4 hangs on a holding unit 6b, in this case a starter device indicated only schematically, which can be designed as a launcher in the form of a launch rail of an aircraft.
  • a starter device indicated only schematically, which can be designed as a launcher in the form of a launch rail of an aircraft.
  • the launcher of the missile 4 is firmly connected to the aircraft.
  • another vehicle may be used to support the missile 4.
  • the warhead 12 of the missile 4 is replaced by a recorder unit 36 which includes a transmitting and receiving unit 26a.
  • the transmitting and receiving unit 26 a - as well as the control unit 14 is included by the missile.
  • the recorder unit 36 records flight data, test data or mission data, for example a flight route, flight maneuvers, aerial images taken with a camera, commands issued by a crew member, data traffic within the aircraft or between a unit of the aircraft Aircraft and the missile 4 or other suitable flight data.
  • an operator arrives at the missile 4 and activates the data traffic with the transmitting and receiving unit 26a and thus also with the control unit 14 via the operating unit 28.
  • test data can be read out, ie wirelessly transmitted to the operating unit 28 without the operational interface 22 must be used. This remains connected via a cable to an interface 38 of the starting device and thus to a control unit of the aircraft.
  • the power supply of the missile 4 is carried by the aircraft, or by the starting device, via the operational interface 22nd
  • a transmitting and receiving unit 26c may be present in the holding unit 6b or in the aircraft, which is connected to a control unit 40 of the aircraft.
  • the transmitting and receiving unit 26c is arranged in the data traffic between the control unit 40 and the control unit 14 of the missile 4, so that the exchanged data pass through the transmitting and receiving unit 26c.
  • the transceiver 26c by its arrangement and data connection, is prepared to wirelessly transmit data from data traffic between the control unit 40 and the control unit 14 to the mobile operator unit 28.
  • FIG Fig. 3 An exemplary arrangement of the transmitting and receiving unit 26c is shown in FIG Fig. 3 shown.
  • An external supply unit 42 for the power supply and coolant supply is connected to a distributor unit 44 via a plurality of lines.
  • Such lines may be a power line, a coolant line, a data line or multiple data lines, in Fig. 3 only two lines are shown as examples.
  • the distribution unit 44 is connected via a line and the operative interface 22 with the missile 4, so that power, coolant and data are passed to corresponding units of the missile 4.
  • the data connection from the missile 4 to the distribution unit 44 is a bus system, for example a MILBUS.
  • the transmitting and receiving unit 26c is wirelessly connected to the operating device 28.
  • the transmitting and receiving unit 26c, the control unit 46 and the distributor unit 44 can be part of an interface unit 48, which can be arranged in the launcher, in the aircraft or in the missile 4.
  • a weapon function of the missile 4 is controlled by the control unit 28 by corresponding data are given wirelessly to the control unit 14. This can be, for example, before an operational use of the missile.
  • the recorder unit 36 of the missile is then with a warhead and the control unit 14, such as Fig. 1 described, equipped.
  • simulation operation is also possible, in which the operating unit 28 transmits to the control unit 14 simulation data with which the control unit 14 is simulated a starting device. This is useful if the launcher is not ready, for example, or the missile 4 is not connected to this, for example, before mounting on the launcher. It is also possible to simulate operating conditions and to test the reactions of the missile.
  • control unit 28 in the aircraft is indicated by the dashed control unit 28 in Fig. 2 is indicated.
  • On-board personnel for example a pilot of the aircraft, now use the operating device 28 for inputting operational commands, for example during the flight of the aircraft before the launch of the missile 4 from the aircraft.
  • the display unit can be a display unit on the operating unit 28 or, in the case of a corresponding interface of the operating unit 28, can also be transmitted to a display unit of the aircraft.
  • Such an operating mode is particularly advantageous if data traffic between the missile 4 and the aircraft is not readily possible due to incompatible interfaces or protocols.
  • the recorder unit 36 in the missile 4 and to give flight data to the cockpit staff of the aircraft, for example, to control.
  • the control unit 28 may be integrated in a pilot's helmet.
EP14000284.1A 2013-02-16 2014-01-28 Procédé de fonctionnement d'une missile stationaire Withdrawn EP2767795A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102013002717.9A DE102013002717A1 (de) 2013-02-16 2013-02-16 Verfahren zum Betrieb eines ruhenden Flugkörpers

Publications (2)

Publication Number Publication Date
EP2767795A2 true EP2767795A2 (fr) 2014-08-20
EP2767795A3 EP2767795A3 (fr) 2017-07-26

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EP14000284.1A Withdrawn EP2767795A3 (fr) 2013-02-16 2014-01-28 Procédé de fonctionnement d'une missile stationaire

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EP (1) EP2767795A3 (fr)
DE (1) DE102013002717A1 (fr)

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CN106855380A (zh) * 2015-12-08 2017-06-16 上海机电工程研究所 一种导弹测试设备供电切换的方法
CN109341440A (zh) * 2018-11-14 2019-02-15 中国空空导弹研究院 一种与导弹电缆整流罩共形的遥测装置
WO2020114359A1 (fr) * 2018-12-03 2020-06-11 中航技进出口有限责任公司 Système de commande aéroporté externe

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CN106855380A (zh) * 2015-12-08 2017-06-16 上海机电工程研究所 一种导弹测试设备供电切换的方法
CN109341440A (zh) * 2018-11-14 2019-02-15 中国空空导弹研究院 一种与导弹电缆整流罩共形的遥测装置
CN109341440B (zh) * 2018-11-14 2023-10-20 中国空空导弹研究院 一种与导弹电缆整流罩共形的遥测装置
WO2020114359A1 (fr) * 2018-12-03 2020-06-11 中航技进出口有限责任公司 Système de commande aéroporté externe

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