Aircraft firing line test cartridge, test assembly and test method

Abstract

Aircraft firing line test cartridge, test assembly and test method An aircraft firing line test cartridge 20 configured for insertion into a pyrotechnic cartridge housing formed in an aircraft conveying and dropping device, comprising a body having a rearward front surface 24, a front front surface 22 and a side surface having a rear portion 28 and a front portion 26; at least one indicator light 34 supported by the body spaced from the rearward front surface 24; a voltage test setting switch 38 supported by the body;two external electrical contacts and an electronic voltage detection circuit connected to the two electrical contacts, arranged in the body and configured to detect at least one energy threshold received by the test cartridge and configured to, depending on the position of the adjustment switch, control said at least one light indicator, the electronic circuit comprising an electrical energy storage, electrical energy stored in the electrical energy storage making it possible to activate said at least one light indicator.;

Description

Title of invention: Aircraft firing line test cartridge, test assembly and test method

[0001] The invention relates to the field of aeronautics, more particularly to aeronautical conveying and dropping devices, in particular ejectors, and in particular pyrotechnic ones. Ejectors are conveying and dropping devices for aircraft which can alternately retain and release on command a device, also known as a load. The ejectors are intended to be mounted on fixed or rotary wing aircraft, typically armed aircraft, helicopters or drones.

[0002] An ejector is typically installed in the lower part of an aircraft, for example under a fuselage or under a wing. The ejector receives a device which it retains in flight. The ejector also houses two pyrotechnic cartridges housed in a chamber. Upon receiving a separation command, the ejector activates, or fires, the pyrotechnic cartridge. The ejector then releases the device, then pushes the device away from the aircraft, generally vertically. An ejector is described in FR3106812.

[0003] The cartridge must be changed after a mission. After a flight, a ground operator checks for the presence of an unfired cartridge for each chamber. To do this, the operator must follow a strict procedure for handling type I pyrotechnic devices, then opens the ejector chamber to check the condition of the cartridge. If the cartridge is unfired, the operator removes the cartridge and places the cartridge in a container dedicated to the storage of unactivated cartridges. FR3114078 describes an indicator device and a method for verifying the presence or absence of a cartridge, drastically reducing the risks.

[0004] The Applicant sought to improve the reliability of the operation of the ejection function in the aircraft, including the ejector. The firing line means the circuit, generally electrical, extending from the separation control button present in the cockpit of the aircraft to the pyrotechnic cartridge. Before a mission, including between two missions, it is desirable to ensure the proper operation of the firing line in order to avoid a separation failure resulting in a failure of the mission, often by endangering the aircraft, and by a risk on return from the mission.

[0005] The invention improves the situation.

[0006] The invention aims to facilitate the tasks of ground operators, to make them faster and less prone to error in mission preparation and return.

[0007] For these purposes, the invention provides an aircraft firing line test cartridge configured for insertion into a pyrotechnic cartridge housing, said housing being formed in an aeronautical conveying and dropping device, said test cartridge comprising a body having a rear front surface, a front front surface and a side surface provided with a rear portion and a front portion; at least one indicator light supported by the body at a distance from the rear front surface; a voltage test setting switch supported by the body;two external electrical contacts and an electronic voltage detection circuit connected to the two electrical contacts, arranged in the body and configured to detect at least one energy threshold received by the test cartridge and configured to, depending on the position of the adjustment switch, control said at least one light indicator, the electronic circuit comprising an electrical energy storage, electrical energy stored in the electrical energy storage making it possible to activate said at least one light indicator. The invention makes it possible to carry out a rapid test, in particular on the runway, of the operation of the aircraft firing line. Such a test is absent from maintenance manuals. The immobilization of the aircraft is reduced. The probability of mission failure is reduced. ;

[0008] In one embodiment, the cartridge comprises a color selection switch mounted in the body and accessible from the front end surface, and configured to control the color of said at least one indicator light. Simultaneous testing by two aircraft firing line test cartridges arranged in two housings of the same aeronautical conveying and dropping device is possible by clearly distinguishing the two housings.

[0009] In one embodiment, the cartridge includes an audible indicator mounted in the body and an audible selection switch mounted in the body and accessible from the front end surface or front portion, and having an on position and a off position for said audible indicator. The test cartridge is suitable for various environments.

[0010] In one embodiment, the electrical energy storage comprises at least one capacitor with a capacity of at least 0.5 mF, preferably at least 1 mF, more preferably at least 1.5 mF.

[0011] In one embodiment, an impedance between the side electrical contact and the end electrical contact is between 0.8 and 1.2 ohms. The capacitor provides power to the electronic circuit. The presence of a battery is not necessary. Advantageously, the cartridge is without a battery or cell.

[0012] In one embodiment, the body is made of conductive metal, in particular stainless steel, aluminum alloy, zinc alloy, the lateral electrical contact being provided by the body, or the body is made of plastic, the lateral electrical contact being provided by a separate conductive part, for example a ring; the lateral electrical contact forming the electrical ground of the test cartridge; and the test cartridge comprising an output connected to the electronic voltage detection circuit and configured to be connected to an external control device. The metal body or a contact, for example a metal ring, provides the electrical connection. The metal ring may be threaded.

[0013] In one embodiment, at least one front indicator light supported by the body on the front surface; and at least one side indicator light supported by the body on the side surface. The indicator lights are visible over a wide angular range.

[0014] In one embodiment, at least two front indicator lights are supported by the body on the front surface; and at least two side indicator lights are supported by the body on the side surface. The presence of two indicator lights makes it possible to assign a color to each test cartridge of a pair implemented to carry out a test in a two-housing pyrotechnic cartridge ejector.

[0015] In one embodiment, a test assembly comprising a test cartridge as above, and a verification housing provided with a housing for receiving said test cartridge, the housing being configured to cooperate with the two electrical contacts of said test cartridge, the verification housing being provided with a firing signal input and configured to transmit a firing signal coming from the firing signal input to said test cartridge in the position plugged into the housing. The test assembly makes it possible to place the test cartridge in the actual test conditions in order to verify the state of the test cartridge: in test condition or out of service. The verification housing may be devoid of active electronic circuitry.

[0016] The invention provides a method for testing an aircraft firing line by an aircraft firing line test cartridge as above, comprising at least the steps: 1) Positioning the voltage test adjustment switch in the position adapted to the supply voltage of the aircraft firing line to be tested. 2) Inserting the test cartridge into a pyrotechnic cartridge housing of an aeronautical conveying and dropping device of the aircraft to be tested, the electrical contact closing a first electrical circuit of the aeronautical conveying and dropping device and the electrical contact closing a second electrical circuit of the aeronautical conveying and dropping device. 3) Triggering a dry firing on the firing line activating the indicators in the event of a satisfactory supply. The correct operation of the firing line is thus verified in a simple manner and by means of light and compact equipment.

[0017] In one embodiment, triggering the dry firing on the firing line causes a firing signal to be sent on the firing line generating a voltage between the electrical contact and the electrical contact, said voltage being received by the electronic circuit, and electrical energy corresponding to said voltage being stored in said storage, then consumed by the electronic circuit to activate the indicators in the event of a satisfactory power supply, the firing signal having a voltage of at least 18 volts and a duration of at least 20 ms. The firing signal serves both as a signal and as a power supplier to power the electronic circuit.

[0018] In one embodiment, steps 1) and 3) are repeated in the event of a detected faulty power supply. A possible error in the execution of the test procedure can thus be corrected.

[0019] In one embodiment, the operation of the test cartridge is verified by plugging it into a receiving housing of a verification box, cooperating with the electrical contact for grounding, the base being supplied with electrical energy and supplying the test cartridge in the position plugged into the base by an electrical signal equivalent to a firing signal, and, in the event of a malfunction of the test cartridge, the test cartridge is declared out of service. The test cartridge is verified to deduce a state of operation or out of service.

[0020] In one embodiment, the housing is provided for a cartridge according to STANAG 3556, in particular type 1. This standard provides for a current of 5 A for 15 ms.

[0021] Other characteristics and advantages of the invention will be explained in detail in the following description, given with reference to the attached drawings.

[0022] [Fig-1] is a perspective view of an ejector with the cartridge in place.

[0023] [Fig.2] is a right elevational view of the ejector of [Fig. 1].

[0024] [Fig.3] is a perspective view of the interior of the ejector of [Fig.l].

[0025] [Fig.4] is a perspective view of an ejector with the test cartridge in place.

[0026] [Fig.5] is a cross-sectional view of the ejector of [Fig.4].

[0027] [Fig.6] is a sectional view of a test cartridge.

[0028] [Fig.7] is a cross-sectional view of a test assembly, test cartridge in place.

[0029] [Fig.8] is a perspective view of a test cartridge.

[0030] [Fig.9] is a perspective view of the interior of a test cartridge.

[0031] [Fig. 10] is a cross-sectional view of an ejector.

[0032] [Fig. 11] is a perspective view of a test assembly mounted with the cartridge of test.

[0033] [Fig. 12] is an electrical diagram of the test cartridge.

[0034] The attached drawings contain, for the most part, elements of a certain character. They may therefore not only serve to better understand the present invention, but also contribute to its definition, where appropriate.

[0035] Here, the term "test" is understood to mean a rapid operation to verify whether or not it is working properly using portable tools that can be used outdoors, on the track, allowing rapid binary decision-making.

[0036] Figures 1 to 3 show an ejector 1. The ejector 1 is intended to be attached to an aircraft, for example a fighter plane or a drone, and to receive a device (not shown) to be released, also called a load. The ejector 1 receives the device during ground loading and separates from said device, either during a drop or an in-flight ejection, or on return from a mission for a replacement of the load.

[0037] The device has on one of its walls a pair of retaining projections, for example in the form of a ring or a T. The ejector 1 engages with said retaining projections when loading the ejector 1. The ejector 1 then retains the device. Upon release, the ejector 1 releases the retaining projections from the device, then pushes the device in a thrust direction Z. The device is ejected. The ejection energy is provided by at least one pyrotechnic cartridge 2 installed in the ejector 1 in a replaceable manner.

[0038] The ejector 1 extends along a direction X perpendicular to the thrust direction Z, from a front support 40 to a rear support 42. The ejector 1 is generally symmetrical with respect to a first plane (Y, Z) orthogonal to the direction X in the sense that the retaining projections are retained in the front support 40 and in the rear support 42.

[0039] In the embodiment shown, the ejector 1 has an elongated shape along the direction X. Here, the ejector 1 is generally symmetrical with respect to a second plane (X, Z) parallel to the directions X and Z.

[0040] The ejector 1 has a first lateral face and a second lateral face 48 parallel, opposite in a direction Y orthogonal to the plane (X, Z). In Figures 1-3, the direction Z is oriented downwards. Here, the ejector 1 has a generally flat appearance relative to the direction Y. The ejector 1 has a lower face 52, perpendicular to the direction Z. The device received by the ejector 1 is opposite the lower face 52. The projections for retaining the device are spaced apart in the direction X.

[0041] The ejector 1 comprises a frame 4. The frame 4 comprises two longitudinal members 400, also called housings. The longitudinal members 400 are parallel and arranged at a distance from each other in the Y direction. A first of the two longitudinal members 400 forms the first lateral face. A second of the two longitudinal members 400 forms the second lateral face 48. The frame 4 comprises a plurality of tabs 402, here four in number. The tabs 402 are arranged in the lower part of the frame 4, on the side of the lower face 52. Here, a first pair of legs 402 is arranged near the front end 40 and another pair of legs 402 is arranged near the rear support 42. The legs 402 are intended to come into abutment against the machine, when the machine 2 is received by the ejector 1. The legs 402 improve the stability of the machine by providing supports distant from each other.

[0042] The side members 400 define between them the interior of the frame 4. The ejector 1 comprises, received in the interior of the frame 4, a pyrotechnic assembly 6, a hook assembly 8 and a locking assembly 10, cf [Fig.3].

[0043] The pyrotechnic assembly 6 comprises a body, at least one cartridge adapter 62, a pair of ejection pistons 64 and a release piston.

[0044] The body is arranged towards the center of the ejector 1. In the body is provided at least one housing, in particular by machining. In each of said at least one housing is installed one of said cartridge adapters 62. Each cartridge adapter 62 is capable of storing a pyrotechnic cartridge 2. Each cartridge adapter 62 can be alternately opened and closed. In the embodiment described here, two housings are provided in the body for two cartridge adapters 62. The cartridge adapters 62 are arranged parallel in the Y direction and juxtaposed.

[0045] Each cartridge adapter 62 is typically of general shape of revolution around an axis in the Y direction. The interior of each cartridge adapter 62 is accessible from the outside when the cartridge adapter 62 is open, so that a pyrotechnic cartridge 2 can be inserted and removed therefrom. Here, access to the housings of the cartridge adapters 62 is from the right side of the frame 4, through an opening 404 opening onto the first lateral face. The opening 404 is formed in the right-hand side member 400.

[0046] The ejection pistons 64 are arranged at the front and rear of the frame 4. The ejection pistons 64 protrude from the lower face 52, on either side of the housings in the direction X. Here, the ejection pistons 64 are arranged near the front 40 and rear 42 supports and the tabs 402, see [Fig.2].

[0047] Each ejection piston 64 is fluidically connected to the cartridge adapters 62. Each pyrotechnic cartridge 2, once ignited, releases a pressurized gas. Then the pressurized gas flows from each cartridge adapter 62 to the ejection pistons 64. Then the ejection pistons 64 deploy downwardly from the frame 4, whereby the ejection pistons 64 eject the device.

[0048] The hook assembly 8 is arranged to alternately retain and release the craft. The hook assembly 8 has a first state in which the hook assembly 8 is closed and retains the craft. The hook assembly 8 has a second state in which the hook assembly 8 is open and releases the craft. The hook assembly 8 is movable between its two states.

[0049] The hook assembly 8 comprises a hook 80 arranged proximate the support 40 and another hook 80 arranged proximate the rear support 42. Each of the hooks 80 is adapted to engage one of the retaining projections of the machine. When the hook assembly 8 is in its first state, each hook 80 is in a closed position in which the hook 80 retains the respective retaining projection of the machine. The hooks 80 are locked. When the hook assembly 8 is in its second state, each hook 80 is in an open position in which the hook 80 releases or can accommodate the respective retaining projection of the machine. The hooks 80 are unlocked.

[0050] The locking assembly 10 is arranged to lock and unlock the hooks 80 of the hook assembly 8. The locking assembly 10 is arranged between the body 60 and the hooks 80. The locking assembly 10 is arranged on either side of the body 60 along the direction X. The locking assembly 10 is actuable by the unlocking piston, whereby the locking assembly 10 unlocks the hooks 80.

[0051] The ejector 1 comprises, near each cartridge adapter 62, a respective visual indicator 12 of the presence of pyrotechnic cartridge 2. The indicator 12 is arranged, at least in part, on one of the side members 400, here the side member 400 to the right of the ejector 1. The indicator 12 is visible and accessible at least in part from outside the frame 4. Reference is made to FR3114078.

[0052] The ejector 1 is controlled by the pilot of the aircraft or by a control unit of the drone via a firing line. The firing line comprises the elements, in particular wires, relays, boxes, between the ejector 1 and the cockpit or the control unit. The firing line is tested before each mission to ensure that the craft will be ejected when the ejection command is initiated.

[0053] For the rapid testing of the firing line, the Applicant has developed an aircraft firing line test cartridge 20. In Figures 4 and 5, the ejector 1 is shown with test cartridges 20 in place of the pyrotechnic cartridges. Each test cartridge 20 is inserted into a housing 63, said housing being formed in an ejector 1, more precisely in place of the cartridge adapter 62.

[0054] As illustrated in Figures 6 and 8, the test cartridge 20 comprises a body having a front end surface 22, a rear end surface 24 and a side surface provided with a front portion 26 and a rear portion 28. The side surface or one of said front and rear portions may have a shape of revolution. The front portion 26 and the rear portion 28 are stepped. The front end surface 22 is radial. The rear end surface 24 is radial. The rear portion 28 may be cylindrical. The front portion 26 and the rear portion 28 are separated by an annular step 30.

[0055] The body may be made of conductive metal, in particular stainless steel, aluminum alloy, zinc alloy. A lateral electrical contact is provided by the body. Alternatively, the body is made of plastic, the lateral electrical contact then being provided by a separate conductive part, for example a ring. The lateral electrical contact forms the electrical ground of the test cartridge 20.

[0056] The test cartridge 20 comprises at least one, here two, front indicator lights 32. The front indicator light 32 is supported by, for example mounted in, the body on the front front surface 22. The front indicator light 32 is a colored LED. The front indicator light 32 is disposed flush with or recessed from the body. The front indicator light 32 may be mounted at a distance from the side surface. The test cartridge 20 comprises at least one, here four, side indicator lights 34. The side indicator light 34 is supported by, for example mounted in, the body on the side surface at a distance from the rear front surface 24. The side indicator light 34 may be mounted in the front portion 26 of the side surface. The side indicator light 34 may be mounted at a distance from the rear portion 28 and at a distance from the front front surface 22. The side indicator light 34 is a colored LED.The side light indicator 34 is disposed flush with or recessed from the body. A light indication on both the front end surface 22 and the side surface reduces the risk of misreading by an operator.

[0057] Alternatively, a light indicator close to the front frontal surface 22 and the side surface may be associated with a light-conducting member to provide light transmission both to an orifice in the front frontal surface 22 and to an orifice in the side surface. The orifices may be common in the form of a notch in the front frontal surface 22 and in the side surface.

[0058] As a variant, the front frontal surface 22 is devoid of a luminous function.

[0059] As a variant, the side surface is devoid of a luminous function.

[0060] The test cartridge 20 includes an audible warning or indicator 36 supported by, for example mounted, in the body. The audible indicator 36 is directed toward the front end surface 22. The audible indicator 36 is disposed flush with or recessed from the body. The audible indicator 36 may have a sound level greater than 90 dB.

[0061] The test cartridge 20 includes an operating energy threshold adjustment switch 38 supported by, for example mounted, in the body. The adjustment switch 38 is accessible from the front portion 26 of the side surface. The adjustment switch 38 is in the form of a two-position button, in particular a slide button.

[0062] In [Fig. 4], two test cartridges 20 are inserted, each in a cartridge adapter housing 63. The rear parts 28 of the test cartridges 20 are arranged in the ejector 1. The front parts 26 of the test cartridges 20 are arranged projecting from the ejector 1. The side 34 and front 32 light indicators are visible from the outside.

[0063] The test cartridge 20 comprises the side electrical contact 54 and an end electrical contact 56 on the front 22 or rear 24 front surface. The side electrical contact 54 and the end electrical contact 56 are configured to establish a closed circuit with corresponding contacts of the ejector 1. The contact corresponding to the side electrical contact 54 is formed on a wall of the cartridge adapter housing 63.

[0064] The test cartridge 20 comprises an electronic voltage detection circuit 66 connected to the lateral electrical contact 54 and to the end electrical contact 56. The test cartridge 20 may comprise an output connected to the electronic voltage detection circuit 66 and configured to be connected to an external control device, for example by the cable 58. The electronic circuit 66 is connected to the lateral electrical contact 54 and to the end electrical contact 56. The electronic circuit 66 is configured to detect the voltage between the lateral electrical contact 54 and the end electrical contact 56. The electronic circuit 66 is configured to, depending on the position of the voltage test setting switch 38, control said at least one lateral light indicator 34, said at least one front light indicator 32 and said audible indicator 36.The electronic circuit 66 receives an electrical signal from the side electrical contact 54 and the end electrical contact 56 and processes it as a source of energy and as a source of information.

[0065] As illustrated in Figures 9, 10 and 12, the electronic circuit 66 includes a capacitor power supply 68 for storing electrical energy from the side electrical contact 54 and the end electrical contact 56. The sum of the capacitances of the at least one capacitor of the power supply amounts to at least 0.5 mF, preferably at least 1 mF, more preferably at least 1.5 mF. In the embodiments shown, four capacitors 68 are mounted inside the body in the vicinity of the rear front surface 24. The capacitors 68 are disposed in the rear portion 28. Four capacitors 68 of 0.470 mF are contemplated. The four capacitors 68 are connected in series or in parallel. The electronic circuit 66 has an impedance between the side electrical contact 54 and the end electrical contact 56 of between 4 and 6 ohms.

[0066] As illustrated in Figures 9 and 12, the electronic circuit 66 comprises a first electronic card 70 arranged in front of the capacitors 68. The first electronic card 70 is arranged in the rear part 28. The first electronic card 70 is connected to the capacitors 68. The first electronic card 70 comprises a diode 701 and a resistance bridge 722 forming a voltage divider connected to the voltage test adjustment switch 38. The diode 701 comprises an anode connected to the end electrical contact 56 and a cathode. In one position, the voltage test adjustment switch 38 shorts a portion of the resistors of the resistor bridge. In the other position, the voltage test adjustment switch 38 is open circuit. The resistor bridge 722 is at the side electrical contact 54 forming the ground opposite the voltage test adjustment switch 38 and connected to the end electrical contact 56 on the side of the voltage test adjustment switch 38. The first electronic card 70 comprises a switch 723 controlled by the middle voltage of the resistor bridge and having a drain connected to the cathode of the diode 701 and a source connected to one terminal of a resistor 724. The resistor 724 has another terminal connected to the capacitors 68.Thus, an electrical firing signal emitted on the firing line of an aircraft being checked makes it possible to power the test cartridge 20, thus making it operational for its test function by charging the capacitors 68. The diode 701 allows the capacitor charging current to pass and blocks the discharge of the capacitors 68. The resistor 724 may have a value located within the required resistance range of a firing cartridge.

[0067] The electronic circuit 66 comprises the second electronic card 72 arranged in the front part 26. The second electronic card 72 is powered by the first electronic card 70. The second electronic card 72 comprises a voltage regulator 702 mounted in parallel with the capacitors 68 to power the audible indicator 36 via a switch 76. The first electronic card 70 allows the capacitors 68 to be charged, the electrical energy to be stored and then a sufficient voltage to be supplied for the operation of the test cartridge 20 and to power the red or green light indicators depending on the position of a switch 74 and to power the audible indicator 36 via the switch 76 by means of a second electronic card 72.

[0068] The second electronic card 72 is electrically connected to the front indicator light 32, the side indicator light 34, and the voltage test setting switch 38. In the embodiment shown, two front indicator lights and four side indicator lights are provided. Three of the front and side indicator lights are red. Three of the front and side indicator lights are green.

[0069] Said electrical energy makes it possible to activate and power said at least one front light indicator 32, said at least one side light indicator 34 and said audible indicator 36. The test cartridge 20 may be without a battery or cell.

[0070] Generally, the number of red front and side indicator lights and the number of red front and side indicator lights green are equal. Each of the front and side indicator lights consists of a light-emitting diode and a resistor in series. The red front and side indicator lights are connected in parallel. The green front and side indicator lights are connected in parallel.

[0071] The electronic circuit 66 includes the color selection switch 74. The color selection switch 74 is supported by, for example mounted, in the body. The color selection switch 74 is accessible from the front end surface 22, in particular flush or projecting. The color selection switch 74 is electrically connected to the front 32 and side 34 indicator lights.The color selection switch 74 has two positions, a first position in which the front 32 and side 34 red indicator lights are electrically connected to the power supply and the front 32 and side 34 green indicator lights are isolated from the power supply, and a second position in which the front 32 and side 34 green indicator lights are electrically connected to the power supply and the front 32 and side 34 red indicator lights are isolated from the power supply. Optionally, a brightness variation is provided. The color selection switch 74 can be mounted on the second electronic card 72.

[0072] The electronic circuit 66 comprises the sound selection switch 76. The sound selection switch 76 is supported by, for example mounted in, the body. The sound selection switch 76 is accessible from the front end surface 22, in particular flush or projecting. The sound selection switch 76 is electrically connected to the sound indicator 36. The sound selection switch 76 has two positions, a first position in which the sound indicator 36 is electrically connected to the power supply, and a second open circuit position. The sound selection switch 76 controls the sound indicator 36. Optionally, a variation of the sound volume of said sound indicator 36 is provided. The sound selection switch 76 may be powered by the second electronic card 72. The sound selection switch 76 may be mounted on the first electronic card 70.

[0073] As illustrated in [Fig. 7], the test cartridge 20 of [Fig. 6] is inserted into a verification housing 90, thus forming a test assembly. The verification housing 90 is provided with a housing for receiving the test cartridge 20. The verification housing 90 comprises a body 92 made of insulating material. The body 92 comprises a bottom wall, one or more side walls and an open top face. The top face is partially closed by a cover 94. A light is provided in the cover 94. The cover 94 can be screwed onto the body 92. Under the cover 94 and in the body 92, electrical connection members 96 are installed, connected to a first electrical cable 100 passing through the side wall. The test box 90 comprises a socket 99 mounted in the body 92. The socket 99 is made of conductive material. The socket 99 is electrically connected to the electrical connection members 96 by a conductive wire. In the embodiment shown, the socket 99 projects beyond the cover 94 while being retained by the cover 94. A bore is provided in the socket 99. The bore forms a lateral electrical contact 54 for the test cartridge 20. The bore forms said receiving housing.

[0074] The verification housing 90 cooperates with the test cartridge 20 to verify its operation. The socket 99 receives the rear of the test cartridge 20. The test cartridge 20 is inserted into the socket 99 as in an ejector 1.

[0075] The bore of the sleeve 99 is in mechanical and electrical contact with the rear part 28 of the lateral surface of the body of the test cartridge 20. The step of the lateral surface bears on one end of the sleeve 99 projecting relative to the cover 94. Alternatively, the sleeve 99 may be made of insulating material and be crossed by the electrical connection members 96 coming into contact with the rear part 28 of the lateral surface of the body of the test cartridge 20.

[0076] As illustrated in Figures 4, 6 and 7, the test cartridge 20 includes an end electrical contact 56 on the front end surface 22. The end electrical contact 56 is connected to a second electrical cable provided with a male plug and a female plug. An external electrical connection is provided. The first electrical cable and the second electrical cable make it possible to subject the test cartridge 20 to an electrical signal identical to the electrical signal of the firing line of an aircraft.

[0077] The test cartridge 20 illustrated in Figures 8, 9, 10 and 11 includes an end electrical contact 56 on the rear front surface 24. The test cartridge 20 is inserted into a test housing 90, thus forming a test assembly. The test housing 90 is similar to that of the previous embodiment except that the electrical connection members 96 are connected to an electrical cable passing through the side wall. The socket 99 is electrically connected to the electrical connection members 96 by a first conductive wire. A second conductive wire connects the electrical connection members 96 and the end electrical contact 56 of the test cartridge 20 to the bottom of the socket 99 in [Fig. 11]. The end electrical contact 56 is in the form of a rod projecting axially beyond the rear front surface 24 of the body.The first conductive wire and the second conductive wire connected to or from the electrical cable make it possible to subject the test cartridge 20 to an electrical signal identical to the electrical signal of the firing line of an aircraft. A cable 58 can be connected to a terminal on the front surface 22 of the test cartridge 20 for an additional connection, in particular for a measurement of the signal with a measuring device of the oscilloscope type.

[0078] In the ejector 1 of [Fig. 10], the test cartridge 20 is inserted into the cartridge adapter until the rear end surface 24 of the body stops against a bottom of the cartridge adapter. The end electrical contact 56 is in mechanical and electrical contact with a downstream contact of the firing line of the aircraft, for example forming part of the ejector 1. A test shot on the firing line causes the test cartridge 20 to receive an electrical signal of sufficient power to power the test cartridge 20, in particular to charge the capacitor power supply.

[0079] In both embodiments, the test cartridge 20 can be checked in the check housing 90 of FIGS. 7 and 11 before and / or after its use in the ejector 1 of FIGS. 1 to 5 and 10. Checking the test cartridge 20 comprises plugging the test cartridge 20 into the receiving housing of the check housing 90. A side wall of the housing or bore 99 of the socket 99 cooperates with the lateral electrical contact 54 of the test cartridge 20 for grounding. The check housing 90 is supplied with electrical energy externally. The check housing 90 supplies the test cartridge 20 in the plugged position in the base with an electrical signal equivalent to a firing signal. A firing signal has a voltage of at least 16 volts and a duration of at least 20 ms in the general case. The voltage and duration depend on the aircraft. The shot cartridge can be adapted to other voltages and other durations.

[0080] In the event of a malfunction of the test cartridge 20, the front and side light indicators and the audible indicator 36 remain inactive. The operator is thus informed of a fault in the test cartridge 20. The test cartridge 20 is replaced.

[0081] In both embodiments described above, the aircraft firing line can be tested using the test cartridge 20. The test cartridge 20 is set by positioning the voltage test setting switch 38 in the position adapted to the supply voltage of the aircraft firing line to be tested, generally 18 volts or 28 volts. This can be done before or after inserting the test cartridge 20 into the ejector 1.

[0082] In the case of implementing two test cartridges 20 in the ejector 1, cf [Fig.4], one of the test cartridges 20 is set for a green color display and the other of the test cartridges 20 is set for a red color display by the color selection switch 74 of each test cartridge 20. This can be done before or after the insertion of the test cartridges 20 into the ejector 1.

[0083] The insertion of the test cartridges 20 into the ejector 1 is carried out by a translational movement directed towards the bottom of the cartridge adapters 62. The end electrical contact 56 closes a first electrical circuit of the aeronautical conveying and dropping device and the lateral electrical contact 54 closes a second circuit electrical connection of the aeronautical conveying and dropping device. In other words, the ground of the aeronautical conveying and dropping device and the ground of the test cartridge 20 are made equipotential and the active terminal of the firing line in the aeronautical conveying and dropping device and the active terminal of the test cartridge 20 are electrically connected.

[0084] A dry firing is then carried out. The firing is dry in the sense that the aircraft carrying the ejector 1 is devoid of any device to be ejected. The ejector 1 is therefore empty of payload. The ejector 1 is equipped with test cartridges 20 in place of the pyrotechnic cartridges. The dry firing is controlled from a cockpit of the aircraft or from a suitable maintenance tool. The triggering of the dry firing on the firing line causes the appearance of an electrical voltage in the ejector 1 between the ground formed by the cartridge adapters 62 and a terminal formed by the downstream contact.

[0085] In normal operation, the appearance of said electrical voltage in the ejector 1 results in the ignition of the pyrotechnic cartridges. In test operation, the appearance of said electrical voltage in the ejector 1 causes the capacitor power supply to be charged, the electronic circuit 66 to be activated, and, in a normal situation, the side indicator light 34, the front indicator light 32 and the audible indicator 36 to be activated. More precisely, the electrical energy from the firing line is transferred to the test cartridges 20. The electrical energy is stored in the capacitor power supply of each test cartridge 20, then supplied to the electronic circuit 66 which supplies the side indicator light 34, the front indicator light 32 and the audible indicator 36.

[0086] In the event of a faulty operation, the electrical energy supplied is insufficient. The side indicator light 34 and the front indicator light 32 remain off and the audible indicator 36 remains silent. A fault is detected. In order for this fault to be attributed to the firing line and not to the test cartridges, it is preferable to first check the test cartridges. If this has not been the case, they can be checked after a faulty operation has been established. If the test cartridges are faulty, the firing line test is repeated with new test cartridges.

[0087] After a faulty operation of the firing line has been observed, the test can be repeated with the same test cartridges in order to determine whether the fault lies in the electrical contact between the test cartridges and the ejector. The steps of voltage selection and insertion of the test cartridges are then repeated.

[0088] If the fault persists, the firing line is declared to be repaired. In the case of satisfactory operation, the electrical energy supplied is sufficient. The side indicator light 34, the front indicator light 32 and the audible indicator 36 are activated. The operation of the firing line is validated. The test cartridges and insert pyrotechnic cartridges so that the aircraft can carry out a planned mission.

Claims

Claims

1. An aircraft firing line test cartridge (20) configured for insertion into a pyrotechnic cartridge housing, said housing being formed in an aircraft conveying and dropping device, said test cartridge (20) comprising a body having a rearward front surface (24), a frontward front surface (22) and a side surface having a rearward portion (28) and a frontward portion (26); at least one indicator light (34) supported by the body spaced from the rearward front surface (24); a voltage test setting switch (38) supported by the body;two external electrical contacts and an electronic voltage detection circuit (66) connected to the two electrical contacts, arranged in the body and configured to detect at least one energy threshold received by the test cartridge and configured to, depending on the position of the adjustment switch, control said at least one light indicator, the electronic circuit (66) comprising an electrical energy storage, electrical energy stored in the electrical energy storage making it possible to activate said at least one light indicator.;

2. The test cartridge (20) of claim 1, comprising a color selection switch (74) mounted in the body and accessible from the front end surface (22), and configured to control the color of said at least one indicator light.

3. A test cartridge (20) according to claim 1 or 2, comprising an audible indicator (36) mounted in the body and an audible selection switch (76) mounted in the body and accessible from the front end surface or the front portion (26), and having an activation position and a deactivation position of said audible indicator (36).

4. Test cartridge (20) according to one of the preceding claims, wherein the electrical energy storage comprises at least one capacitor (68) with a capacity of at least 0.5 mF, preferably at least 1 mF, more preferably at least 1.5 mF and wherein an impedance between the side electrical contact (54) and the end electrical contact (56) is between 0.8 and 1.2 ohms.

5. Test cartridge (20) according to one of the preceding claims, in which the body is made of conductive metal, in particular stainless steel, aluminum alloy, zinc alloy, the lateral electrical contact (54) being provided by the body, or the body is made of plastic, the lateral electrical contact (54) being provided by a separate conductive part, for example a ring; the lateral electrical contact (54) forming the electrical ground of the test cartridge (20); and the test cartridge (20) comprising an output connected to the electronic voltage detection circuit (66) and configured to be connected to an external control device.

6. A test cartridge (20) according to any preceding claim, comprising at least one front indicator light (32) supported by the front front surface body (22); and at least one side indicator light (34) supported by the side surface body; preferably at least two front indicator lights (32) supported by the front front surface body (22); and at least two side indicator lights (34) supported by the side surface body.

7. Test assembly comprising a test cartridge (20) according to one of the preceding claims, and a verification housing (90) provided with a housing for receiving said test cartridge (20), the housing being configured to cooperate with the two electrical contacts of said test cartridge (20), the verification housing (90) being provided with a firing signal input and configured to transmit a firing signal coming from the firing signal input to said test cartridge (20) in the position plugged into the housing.

8. A method of testing an aircraft firing line by an aircraft firing line test cartridge (20) according to one of claims 1 to 6, comprising at least the steps: 1) Positioning the voltage test adjustment switch (38) in the position adapted to the supply voltage of the aircraft firing line to be tested. 2) Inserting the test cartridge (20) into a pyrotechnic cartridge housing of an aeronautical conveying and dropping device of the aircraft to be tested, the electrical contact (56) closing a first electrical circuit of the aeronautical conveying and dropping device and the electrical contact (54) closing a second electrical circuit of the aeronautical conveyor and drop device. 3) Trigger a dry shot on the firing line activating the indicators in the event of a satisfactory power supply.

9. The method of claim 8, wherein triggering the dry firing on the firing line causes a firing signal to be sent on the firing line generating a voltage between the electrical contact (54) and the electrical contact (56), said voltage being received by the electronic circuit (66), and electrical energy corresponding to said voltage being stored in said storage, then consumed by the electronic circuit (66) to activate the indicators in the event of a satisfactory power supply, the firing signal having a voltage of at least 18 volts and a duration of at least 20 ms.

10. A method according to claim 8 or 9, wherein steps 1) and 3) are repeated in the event of a detected faulty power supply.

11. A method according to claim 8, 9 or 10, wherein the operation of the test cartridge (20) is checked by plugging it into a receiving housing of a verification box (90), cooperating with the electrical contact (54) for grounding, the base being supplied with electrical energy and supplying the test cartridge (20) in the position plugged into the base by an electrical signal equivalent to a firing signal, and, in the event of a malfunction of the test cartridge (20), the test cartridge (20) is declared out of service.

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