FR2639123A1 - Apparatus and method of inspection for a weapon interface system on an aircraft - Google Patents

Abstract

The inspection apparatus 83 is designed to interface with a standard avionics unit for a weapon/ejector system, which communicates with the computer on the aircraft or on another vehicle via a data bus conforming to a military standard. The inspection apparatus comprises an operator interface panel 84 with control buttons 86, 88, 90 and indicator lights 92, 94 and an adaptor test cable 98 for connection to an interface unit 22 and a power supply unit 46. The monitoring apparatus is supplied with power by a ground power unit 102. The apparatus allows easy operation on forward military bases under extreme conditions of temperature and bad weather.

Description

 Until now, most of the current weapon systems include equipment made up of boxes containing aeroelectronic equipment or avionics boxes and cables, which constitute the interface between a weapon or a projectile and an ejector on the one hand and the shooting computer and the power supply system of the airplane or of another aircraft on the other hand your avionics boxes and their cables are often mounted on a mount or other weapon supports, such as a beam mounted under the wing or a device for launching and supporting bombs, which is stored separately from the aircraft. Before loading the lookout or other weapon supports on the aircraft, the operation of the assembly is usually carried out. To control such a system, it has always been necessary to use control equipment or separate verification. Conventional equipment of this type is bulky equipment requiring a computer to control it. However, the computers of these devices often have limits of use imposed by the environment, in the sense that they can only operate in a building or an enclosure where the temperature is regulated. These limitations imposed by the environment mean that the control equipment cannot be easily implemented or is unusable in advanced operational bases where the equipment and support materials are minimal.

 Previous attempts to build control equipment have focused in particular on devices which can be moved in a container isolated from the environment. These type of devices take their operating environment with them, because an oven or an air conditioner avoiding extreme temperatures are housed in a transportable enclosure which prevents dust, ie wind, rain and so on from coming. in contact with the equipment. Other control equipment is not mobile and is installed in a building, which makes it necessary to bring the mountings or other weapon supports to the fixed control equipment. Although the equipment described above is suitable for controlling weapon systems, it has the drawback that it cannot be easily implemented on advanced military bases.

 U.S. patents 3609 312, 3 619 792, 3 710 350, 3 803 974, 3 889 109, 3 920 973, 4 155 116, 4 246 472, 4 370 706 and 4 494 438 describe different types of computer-controlled systems for weapons launched at from an aircraft and for control units of airplanes or other aircraft, as well as self-diagnosis control systems used on household appliances.

None of these control systems have the unique features and benefits of the weapon interface system tester described here.

 The verification apparatus according to the invention eliminates the need for complex assistance equipment and makes it possible to carry out the checks, inside or outside, over a wide range of temperatures. In addition, the Verification apparatus according to the invention can be easily implemented on advanced military bases.

 The device uses the unique characteristics of a weapon system avionics box, which communicates with the computer of a vehicle for transporting or controlling a weapon via a data bus according to the American military standard MIL STD 1553.

 The apparatus according to the invention comprises an interface table for the operator-verifier, with a display device of which a lamp control device, a self-control device and a control trigger device, as well as "good" and "defective" indicator lights, which are connected to a weapon system interface unit. The tester is used with a park power supply group and a control cable designed to be plugged into the weapon / ejector power switch unit.

The advantages and the aims of the invention will emerge more clearly from the detailed description which follows, as well as from the appended drawings, showing preferred but in no way limiting embodiments of the invention and in which:
- Figure 1 shows the configuration of a weapon system of the prior art;
- Figure 2 shows a control apparatus of the prior art, connected to a weapon mount;
- Figure 3 is a simplified representation of a weapon system interface unit and a power switching unit; and
- Figure 4 shows a verification device according to the invention for a weapon interface system on an aircraft, device which is connected to the interface unit and the power unit.

 Figure 1 shows a weapon system avionics box, according to the American military standard MIL-STD-1760, for communication with an airplane or any other vehicle for transporting or controlling one or more weapons. The aircraft is generally designated by the reference 10. In FIG. 1, the aircraft 10 is equipped with a shooting or pointing / command computer 12, connected to a data bus according to the aforementioned standard 1553 and comprising lines 14 and 16 terminating on data bus connectors 18 and 20.

The connectors are in turn connected to a weapon system interface unit 22. The aircraft 10 also comprises a power supply source for a weapon mount, designated by the reference 23 and providing electrical energy to a current distribution box 24 for a weapon mount, via a line 26 for transporting alternating current and / or direct current. The interface unit 22 and the distribution box 24 are part of a mount or other weapon support generally designated by the reference 30 and separated from the aircraft 10 by an aircraft / vehicle interface represented by a line 31. The interface unit 22 and the distribution box 24 are connected together by a supply line 32 and a line 34 for controlling a slave switching unit. The interface unit 22 further comprises additional data buses, 36 and 38, also according to the aforementioned standard 1553, with connectors 40 and 42 which are connected to a weapon connector 44 at the end of a weapon umbilical cable 45 (see FIG. 4) serving when connecting to a weapon. The interface unit 22 is connected by a command and control line 48 to a command and control unit 46 for switching the supply of the weapon / ejector. The power unit 46 is also connected to the distribution box 24, by a line 50, for its supply of alternating current and / or direct current. In addition, the unit 46 is connected to a connector of ejector 52 by a line 53 for the control of the ejector and the transmission of signals of discrete components, as well as to the weapon connector 44 by a line 54 used for the power supply of the weapon and for the transmission of signals discrete components. The ejector has an ejector umbilical cable 55 (see Figure 4).

 FIG. 2 shows a conventional apparatus 60 for controlling the mount or other weapon support 30. The latter is shown separated from the control apparatus 60 by an interface line 31.

 The apparatus 60 uses a bus control 62 according to the aforementioned standard 1553. This controls the avionics box or, in this case, the weapon mount 30 with the standard interface unit. 22.

The control apparatus 60 also comprises a remote terminal 64, also according to the aforementioned standard 1553, intended to be connected to the weapon connector 44. The terminal 64 responds to the interface unit 22 in the manner of a missile. The apparatus 60 also includes a device 66 for monitoring the weapon and the ejector, used to check the discrete components used to emit signals and to receive signals from the weapon (projectile) and from its ejector. This system simulates a weapon computer.

The apparatus additionally comprises an operator terminal 61, a computer 63, a computer bus 65 and a power source 67.

A device 68 forms an intermediate element for supplying alternating current and / or direct current to the distribution box 24 from the power source 67. Together with the bus control 62, this device simulates a computer plane
When we now refer to FIG. 3, it should be noted that a standard interface 22 includes, as one of its components, a remote terminal card (R / T) 70, according to the aforementioned standard 1553, for communication with the airplane 10. In addition, it includes a bus control (B / C) 72, also according to the aforementioned standard 1553, as well as a central unit with memory (CPU) 74, all connected to a motherboard 76. The latter is also combined with a power supply circuit 78, a power supply unit interface 80 and a card 82 for a panel with discrete components.

 FIG. 4 represents the verification apparatus according to the invention, generally designated by the reference 83 and comprising a table 84 of operator interface with a button 86 for controlling lamps, a button 88 for self-checking of unit d interface and a control trigger button 90, as well as a "good" indicator light 92 and a "faulty" indicator light 94. The panel 84 is connected to the interface unit 22 by a line 96. A control adapter cable 98 is used for connection to the weapon umbilical cable 45, to the ejector umbilical cable 55 and to a connection line 100 for discrete components. The control adapter cable 98 is compatible with a standard bus according to the military standard MIL-STD-1553 mentioned above, comprising lines 14 and 16, as shown in FIGS. 1, 2 and 3.

The verification device 83 according to the invention further comprises an electric power source such as the park group 102, comprising a line 104 for supplying alternating current / direct current, with an adapter cable 106 for the connection to a current distribution box 108, itself connected to the supply unit 46 by a line 110 and to the interface unit 22 by a line 112.

 For a check, the fleet group is started.

and the system is powered. The operator-checker presses the lamp control button 86 in table 84 to check the indicators 92 and 94. After this check, the self-control button 88 of the interface unit is turned: if the "good" indicator 92 s On, the interface unit 22 has successfully passed the contract. If the "defective" indicator 94 lights up, the interface unit 22 is replaced.

Then, the adapter cable 98 is connected to the cables 45 and 55 of the weapon and of the ejector. The control button 90 is rotated in your on position and the interface unit 22 is used to control the system according to the aforementioned standard 1553 and the discrete components of the weapon and the ejector. If the check is satisfactory, the indicator 92 will light up. If it is the light 94 which lights up, there is a control problem. At this point, check the wiring connections and the connector pins and repeat the test.

If the "faulty" light comes on again, the power unit 46 must be replaced. If, after this replacement, the "defective" indicator lights up again, a fault has occurred in the interface unit 22, which must then be replaced.

it should be noted that the verification device 83 lets the central unit 94 control the B / C bus control 72, that it transmits signals through the system wiring and the bus connectors, with feedback of signals in the interface unit 22, and that it gives instructions to the remote terminal card
R / T 70. Thus, the central unit 74 delivers an instruction according to the aforementioned standard 1553 to the bus control B / C 72, the message goes around and arrives on the R / T 70 for evaluation. This looping concept allows the central unit 74 to receive by a device the message that it sent via another device. If a message error occurs, it means that there is a fault in a circuit or a break in a cable or connector.A visual inspection of the connector (s) or cables concerned, on the presence of interruptions or other damage, may cause the operator of the testing device 83 to replace the suspect component and retest. A similar defect after a cable and / or connector replacement would result in the replacement of the suspect avionics box. This would then be removed and sent to the maintenance depot. The only remaining signals requiring verification are those of the discrete components of the weapon and the ejector. This control can be achieved by adding circuits in the supply unit 46 to allow the central unit 74 of the interface system 22 to reintroduce the output signals of the discrete components of the weapon and of the ejector into the power unit 46, using a loop-through control cable. The control cable 98 ensures the looping of the signals on the connectors 102, 104 of the umbilical cables of the weapon and the ejector, to pass them back through the connection 100 of the interface unit 46 to to a card 101 for discrete components.

 To summarize and briefly re-examine the preceding descriptions of the drawings, it will be understood that different types of avionics boxes for weapon systems are easily adaptable to the verification device 83 according to the invention. In addition, the control devices previously used can now be replaced by the verification device 83 for weapon interface systems, device which only comprises a switch and display panel 84, with the adapter cable 98 and a ground power source, such as the park group 102, as well as a current distribution box 108, provided that the interface unit 22 is programmed, during its design, to contain the firmware necessary for interfacing with the switchboard 84 and for using a self-checking circuit, which is added to the system by the discrete component cards 82 and 101.

 The invention is not limited to the embodiments described and those skilled in the art can make various modifications to it, without going beyond its ambit.

Claims (8)

 1. Verification device (83) for checking the status of a weapon interface system intended to connect an airplane computer (12) to weapons and weapon ejectors, the interface system weapon comprising a weapon system interface unit (22), a power switching unit (46) and a power distribution box (108), the interface unit (22) being connected the power switching unit (46) and the current distribution box (108) and comprising a first data bus (18, 20) connected to the aircraft computer (12) and a second data bus data (36, 38) connected to one of the weapon systems, the power switching unit (46) being connected to the interface unit (22) and to the current distribution box (108) and comprising a line (54) for connection to the weapon and a line (53) for connection to the ejector, and the current distribution box (108) being connected to a current source (102), because operated in that it includes  - an operator interface panel (84) intended to be connected by a line (96) to the interface unit (22) and comprising control members (88, 90) for controlling the interface system weapons,  a control adapter cable (98) intended to connect the power switching unit (46) to the second data bus (36, 38) of the interface unit (22), and,  - a central unit (CPU-74) mounted in the interface system and connected by line (96) to the interface board and to selected parts, circuits or components, of the interface system, in order to produce and send messages or signals in said selected parts, to receive messages or signals in return from said selected parts via said control adapter cable (98), and to control said interface panel (84),  - Said interface table (84) comprising indicator lights (92, 94) sensitive to messages or feedback signals to indicate the state of the selected part.  2. Apparatus according to claim 1, characterized in that the operator interface table (84) comprises at least one control button (88) intended to produce a control message or signal and at least one indicator (92) intended to receive a message or signal in return and to indicate the state of the part chosen according to the message or signal in return.  3. Apparatus according to claim 1, characterized in that the central unit (CPU-74) is included in the interface unit (22).  4. Apparatus according to claim 1, characterized in that the selected part comprises a part of the interface unit (22).  5. Verification method for checking the status of a weapon interface system intended to connect an airplane computer (12) to weapons and weapon ejectors, the weapon interface system comprising a weapon system interface unit (22), a power switching unit (46) and a power distribution box (108), the interface unit (22) being connected to the power switching unit (46) and to the current distribution box (108) and comprising a first data bus (18, 20) connected to the computer (12) and a second data bus (36, 38) connected to one of the weapon systems, the power switching unit (46) being connected to the interface unit (22) and to the current distribution box (108) and comprising a line (54 ) of connection to the weapon system in question, and a line (53) of connection to the corresponding ejector, and the current distribution box (108) being connected to a current source (102), characterized in that it comprises  - the connection of an interface panel (84) by a line (96) to the interface unit (22),  - producing a control signal or message and sending this message or signal to the interface unit (22), using the interface table (84),  - provide a central unit (CPU-74) in the weapon interface system,  - send the control signal or message to a selected part, circuit or component, of the weapon interface system so that this chosen part sends a signal or message in return to the central unit (CPU-74) according to the state of this chosen part,  - transmit the signal or message back to the interface panel, and  - indicate the state of said selected part by means of the interface table (84) as a function of the return signal or message.  6. Method according to claim 5, characterized in that the selected part comprises a part of the weapon system interface unit (22).  7. Method according to claim 5, characterized in that the selected part comprises a part of the power switching unit (46).  8. Method according to claim 5, characterized in that it further comprises  - the connection of the power switching unit (46) to the interface unit (22)  - the choice of the part chosen so that the return signal or message is transmitted to the interface unit (22) via the power switching unit (46).