An aircraft external store delivery system detection apparatus and method

Abstract

The application discloses an aircraft external load release system detection device and a detection method. The device comprises an aircraft cross-linking interface module, a function control module and a function indication module. The aircraft cross-linking interface module is connected with an aircraft pylon end to realize signal transmission between the aircraft pylon end and the aircraft external load release system detection device. The function control module is connected with the aircraft cross-linking interface module and controls the transmission of the aircraft pylon end signal through a control device arranged in the function control module. The function indication module is connected with the aircraft cross-linking interface module and the function control module and indicates whether the function of the aircraft external load release system is normal through an indication device arranged in the function indication module. The application has simple circuit structure and low cost. The application realizes comprehensive testing of each function of the external load release system when the aircraft is maintained without being equipped with a pylon or a launching and hanging projectile hook, thereby reducing the failure rate, saving the maintenance cost, shortening the maintenance range, reducing the maintenance workload, improving the availability of the equipment and the like.

Description

Technical Field

[0001] This invention relates to the field of testing technology for aircraft external stores delivery systems, specifically to a testing device and method for aircraft external stores delivery systems. Background Technology

[0002] An aircraft external stores delivery system is a system specifically designed to manage and control external stores (such as weapons, fuel tanks, and electronic pods) on an aircraft. This system ensures that external stores can be released or deployed from the aircraft at a specified time and under safe conditions. Its main applications include weapon delivery from military aircraft and load release in emergency situations on civilian aircraft.

[0003] After the aircraft's structure, finished products, cables, and conduits have been repaired, the aircraft enters the final assembly and testing phase, requiring a functional check of the external stores delivery system. However, some guide pylons or ejection hooks within the guide pylons were not brought into the factory during the major overhaul. This resulted in some functions of the external stores delivery system being unable to be tested during the final assembly and testing phase, compromising the integrity of certain wiring and external stores delivery system components during the overhaul process. If any of these unchecked items malfunction during service, troubleshooting and rework at both the field and airfield locations are required, severely impacting repair timelines and quality, increasing maintenance costs, and reducing overall efficiency. Summary of the Invention

[0004] The technical problem to be solved by this invention is to provide a testing device and method for an aircraft external stores delivery system, which can perform power-on checks on all functions of the external stores delivery system on aircraft that are not equipped with pylons or ejection hooks, thereby improving the reliability of the aircraft external stores delivery system, shortening the delivery cycle, increasing production efficiency, and ensuring delivery quality.

[0005] To solve the above-mentioned technical problems, the technical solution adopted by the present invention is as follows: An aircraft external stores delivery system testing device includes: an aircraft crosslink interface module, a function control module, and a function indication module; The aircraft crosslink interface module is connected to the aircraft pylon end to realize signal transmission between the aircraft pylon end and the detection equipment of the aircraft external load distribution system; The functional control module is connected to the aircraft cross-link interface module and controls the transmission of signals at the aircraft pylon end through the controllers located in the functional control module. The function indicator module is connected to the aircraft cross-linking interface module and the function control module, and uses an indicator located in the function indicator module to indicate whether the aircraft external stores delivery system is functioning properly.

[0006] Furthermore, the aircraft crosslink interface module includes multiple inner sockets, multiple external plugs connected to the inner sockets, and multiple crosslink interface cables connecting the external plugs to the aircraft rack end; The number of internal sockets, external plugs, and cross-linked interface cables are consistent. Each internal socket is connected to one external plug. Each external plug is connected to the aircraft's suspended signal terminal, power supply terminal, grounding terminal, emergency deployment signal terminal, and normal deployment signal terminal respectively through a cross-linked interface cable.

[0007] Furthermore, the control devices within the functional control module include relay J1 and relay J2; The relay J1 is connected to the aircraft emergency delivery signal terminal and the ground terminal respectively through the aircraft cross-linking interface module. The relay J1 controls the opening and closing of contacts P1 and P2. The relay J2 is connected to the aircraft's normal deployment signal terminal and ground terminal respectively via the aircraft crosslink interface module; the relay J2 controls the opening and closing of contacts P3 and P4; The contacts P1, P2, P3, and P4 are connected in series and connected in parallel between the grounding terminal and the aircraft suspension signal terminal through the aircraft crosslinking interface module; the contacts P1 and P2 controlled by relay J1 and the contacts P3 and P4 controlled by relay J2 are normally closed.

[0008] Furthermore, the control device within the functional control module also includes a switch K1, which is connected in series with contacts P1, P2, P3, and P4. The switch K1 has an automatic mode and a manual mode. When in the automatic mode, the switch K1 is closed, and when in the manual mode, the switch K1 is open.

[0009] Furthermore, the function indication module includes indicators D1, D2, and D3; The indicator D1 is connected to the aircraft's power supply terminal at one end and to the aircraft's suspension signal terminal at the other end to indicate the on / off state of the suspension signal of the bomb hook at the aircraft's pylon end. The indicator D2 is connected to the emergency release signal terminal of the aircraft at one end and to the ground terminal of the aircraft at the other end, so as to indicate the on / off state of the emergency release signal at the aircraft pylon end. The indicator D3 is connected at one end to the normal deployment signal terminal of the aircraft and at the other end to the ground terminal of the aircraft, so as to indicate the on / off state of the normal deployment signal at the aircraft pylon end.

[0010] Furthermore, the indicators D1, D2 and D3 include, but are not limited to, signal lights, light-emitting diodes (LEDs), small incandescent bulbs, neon lamps, fluorescent lamps and organic light-emitting diodes (OLEDs).

[0011] Furthermore, the number of aircraft crosslink interface modules, function control modules, and function indication modules are all four sets, which are respectively connected to the outer side of the left wing, the inner side of the left wing, the outer side of the right wing, and the inner side of the right wing pylon.

[0012] Furthermore, the detection equipment for the aircraft external stores delivery system also includes a housing and a control panel. The housing houses and fixes the aircraft crosslink interface module, the function control module, and the function indicator module. The function indicator module and part of the function control module are exposed on the control panel.

[0013] Furthermore, the present invention also provides a detection method using the above-mentioned aircraft external stores delivery system detection equipment, comprising the following steps: S1, connect the aircraft external load distribution system detection equipment to the aircraft end through the aircraft crosslink interface module and cable, set all power switches in the aircraft cockpit to the off position, connect the ground DC power supply to the aircraft, and turn on the ground power switch of the aircraft battery. S2, according to the requirements of the item to be tested, set the switch in the function control module to the automatic or manual position; S3, test the output of the aircraft suspension signal, normal deployment signal and emergency deployment signal, and confirm whether the test is qualified according to the status of the function indicator module.

[0014] Further, step S3 includes: S31, turn on the automatic protection switches for "outer tactical release" and "inner tactical release" on the aircraft, turn on the automatic protection switches for "firing and bombing" and "landing gear, navigation lights, and drag chute" on the aircraft, set the "bomb release selection" switch to the "inner / outer" position, set the weapon selection switch on the control box panel to the "bomb" position, and set switches K1, K2, K3, and K4 in the function control module located on the outer, inner, outer, and inner pylon ends of the left wing, left wing, right wing, and right wing, respectively, to the "manual" position; at this time, the indicators D1, D4, D7, and D10 in the function indication module that indicate the bomb hook suspension signal on the outer, inner, outer, and inner pylon ends of the left wing, left wing, right wing, and right wing, respectively, should be extinguished; S32, turn on the automatic protection switch for "emergency deployment of external objects" on the machine, and set switches K1, K2, K3 and K4 to the "automatic" position. At this time, indicators D1, D4, D7 and D10 should light up. Turn on the automatic protection switch for "emergency deployment of external objects" on the machine, and set switches K1, K2, K3 and K4 to the "manual" position. At this time, indicators D1, D4, D7 and D10 should be off. S33, lift the "XH-6 inspection light", press the "fire and bomb release" button, and set switches K1, K2, K3 and K4 to the "automatic" position. At this time, the indicators D3, D6, D9 and D12 in the function indicator module that indicate the normal release signal of the outer side of the left wing, the inner side of the left wing, the outer side of the right wing and the inner side of the right wing should light up. Release the "XH-6 Inspection Light" and "Fire and Bomb Discharge" buttons, and set switches K1, K2, K3 and K4 to the "Automatic" position. At this time, indicators D3, D6, D9 and D12 should be off. S34, turn on the automatic protection switch for "emergency release of external objects" on the aircraft, press the "release of internal suspended objects" button, and set switches K1, K2, K3 and K4 to the "automatic" position. At this time, the indicators D5 and D8 in the function indicator module that indicate the emergency release signal of the inner side of the left wing and the inner side of the right wing respectively should light up. Release the automatic protection switch for "Emergency Dispatch of External Items" on the machine, release the button for "Dispatch of Internal Suspended Items", and set switches K1, K2, K3 and K4 to the "Manual" or "Automatic" position. At this time, indicators D5 and D8 should be off. S35, turn on the automatic protection switch for "emergency release of external objects" on the aircraft, press the "release of external suspended objects" button, and set switches K1, K2, K3 and K4 to the "automatic" position. At this time, the indicators D2 and D11 in the function indicator module that indicate the emergency release signal on the outer side of the left wing and the outer side of the right wing respectively should light up. Release the automatic protection switch for "Emergency Drop of External Items" on the machine, release the "Drop of External Suspended Items" button, and set switches K1, K2, K3 and K4 to the "Automatic" position. At this time, indicators D2 and D11 should be off.

[0015] Compared with the prior art, the advantages of the present invention are as follows: The aircraft external stores delivery system testing equipment of this invention connects the testing equipment to the aircraft external stores delivery system through an aircraft cross-linking interface module. A function control module controls the on / off state of the bomb hook suspension signal at the aircraft pylon end. The indicator status of the function indicator module during the test reflects whether the bomb hook suspension and delivery functions are normal. The circuit structure is simple and low-cost, enabling comprehensive testing of all functions of the external stores delivery system during maintenance of aircraft without pylons or ejection bomb hooks. This facilitates early detection of potential problems or faults in the system, effectively preventing, controlling, and eliminating system and circuit failures before they occur, thereby reducing the failure rate, saving maintenance costs, shortening the maintenance scope, reducing maintenance workload, and improving equipment availability. Furthermore, the testing can prevent problems such as mis-attaching or mis-delivering, further improving the reliability and safety of the aircraft external stores delivery system during operation. Attached Figure Description

[0016] Figure 1 This is a schematic block diagram of the structure of a detection device for an aircraft external stores delivery system according to an embodiment of the present invention.

[0017] Figure 2 This is a three-dimensional structural diagram of the detection equipment for the aircraft external stores delivery system in this embodiment.

[0018] Figure 3 This is a circuit diagram of the detection equipment for the aircraft external stores delivery system in this embodiment.

[0019] Figure 4 This is a schematic block diagram of the aircraft crosslinking interface module in the aircraft external stores delivery system testing equipment of this embodiment.

[0020] Figure 5 This is a schematic block diagram of the automatic control circuit in the functional control module of the aircraft external stores delivery system detection equipment in this embodiment.

[0021] Figure 6 This is a schematic block diagram of the manual control circuit in the functional control module of the aircraft external stores delivery system detection equipment in this embodiment.

[0022] Figure 7 This is a schematic block diagram of the function indicator module in the aircraft external stores delivery system detection equipment of this embodiment.

[0023] Figure 8 This is a schematic diagram of the control panel in the detection equipment of the aircraft external stores delivery system in this embodiment. Detailed Implementation

[0024] To better understand the above technical solutions, the following will provide a detailed explanation of the technical solutions in conjunction with the accompanying drawings and specific implementation methods.

[0025] like Figures 1 to 3 As shown, this embodiment of the invention provides a detection device for an aircraft external stores delivery system, including: an aircraft crosslinking interface module, a function control module, and a function indication module; The aircraft crosslink interface module is connected to the aircraft pylon end to realize signal transmission between the aircraft pylon end and the detection equipment of the aircraft external load distribution system; The functional control module is connected to the aircraft cross-link interface module and controls the transmission of signals at the aircraft pylon end through the controllers located in the functional control module. The function indicator module is connected to the aircraft cross-linking interface module and the function control module, and uses an indicator located in the function indicator module to indicate whether the aircraft external stores delivery system is functioning properly.

[0026] It is understood that the aircraft external stores delivery system testing equipment in this embodiment connects the testing equipment to the aircraft external stores delivery system through the aircraft crosslink interface module, and controls the on / off of the suspension signal of the bomb hook at the aircraft pylon end through the function control module. Then, the indication status of the function indicator module during the test reflects whether the suspension function and delivery function of the bomb hook are normal. The circuit structure is simple and low cost, realizing comprehensive testing of all functions of the external stores delivery system when the aircraft is not equipped with pylons or ejection bomb hooks. It is beneficial to discover potential problems or faults in the system in advance, so that system and circuit faults can be effectively prevented, controlled and eliminated before they occur, thereby reducing the failure rate, saving maintenance costs, shortening the maintenance scope, reducing maintenance workload, and improving equipment availability. Moreover, the detection can avoid problems such as mis-attaching or mis-delivery, further improving the reliability and safety of the aircraft external stores delivery system during operation.

[0027] In this embodiment, as Figure 3 and Figure 4 As shown, the aircraft crosslink interface module includes multiple inner sockets, multiple external plugs connected to the inner sockets, and multiple crosslink interface cables connecting the external plugs to the aircraft rack end; The number of internal sockets, external plugs, and cross-linked interface cables are consistent. Each internal socket is connected to one external plug. Each external plug is connected to the aircraft's suspended signal terminal, power supply terminal, grounding terminal, emergency deployment signal terminal, and normal deployment signal terminal respectively through a cross-linked interface cable.

[0028] Specifically, please refer to Figure 3 and Figure 4 The aircraft crosslink interface module includes four P20J9A type sockets (internal sockets), four P20K9Q type external plugs that mate with each internal socket, two 5.5-meter left and right inner hook crosslink interface cables, and two 6-meter left and right outer hook crosslink interface cables. The four sets of sockets, plugs, and cables are connected to the aircraft pylon ends 176, 180, 142, and 162 plugs (representing the outer left wing, inner left wing, outer right wing, and inner right wing pylon ends, respectively) via a P32J11Q type socket, thus enabling the transmission of aircraft signals between the aircraft and detection equipment. Of course, the plug and socket models and the length of the crosslink interface cables for the aircraft crosslink interface module are not unique and can be adjusted according to actual needs.

[0029] In this embodiment, as Figure 3 and Figure 5 As shown, the control devices within the functional control module include relay J1 and relay J2, which serve as an automatic control circuit. The relay J1 is connected to the aircraft emergency delivery signal terminal and the ground terminal respectively through the aircraft cross-linking interface module. The relay J1 controls the opening and closing of contacts P1 and P2. The relay J2 is connected to the aircraft's normal deployment signal terminal and ground terminal respectively via the aircraft crosslink interface module; the relay J2 controls the opening and closing of contacts P3 and P4; The contacts P1, P2, P3, and P4 are connected in series and connected in parallel between the grounding terminal and the aircraft suspension signal terminal through the aircraft crosslink interface module. When no normal or emergency deployment signal is received from the aircraft, the contacts P1 and P2 controlled by relay J1 and the contacts P3 and P4 controlled by relay J2 are in a normally closed state.

[0030] Specifically, please refer to Figure 3 and Figure 5 The functional control module consists of eight J300-C1A relays. Its main function is to control the disconnection of the missile hook suspension signal on the inner and outer pylons of the left and right wings when the normal or emergency missile release signal is activated. Taking the outer pylon of the left wing as an example, the two ends of relay J1 are connected to the emergency release signal terminal and the ground terminal, respectively, and the two ends of relay J2 are connected to the normal release signal terminal and the ground terminal, respectively. Before the normal or emergency missile release signal is activated, the P1-P2 contacts controlled by relay J1 are normally closed, and the P3-P4 contacts controlled by relay J2 are normally closed, allowing the aircraft suspension signal to be output normally, indicating that the missile is properly suspended. When the normal or emergency missile release signal is activated, the P1-P2 contacts or the P3-P4 contacts are opened, indicating that the normal or emergency missile release is successful. Similarly, relays J3-J8 control the on / off state of the bomb hook suspension signals on the inner left wing, inner right wing, and outer right wing pylons, respectively. Their circuit connections are identical to those of relays J1 and J2 on the outer left wing pylon, and will not be repeated here. Furthermore, Figure 5 The missile hook suspension feedback signal in the system sends a ground signal to the missile hook suspension indicator light in the aircraft cockpit. The missile hook suspension signal indicates the current status of the missile hook; an illuminated light indicates that a missile is mounted, while an off light indicates that no missile is mounted or that the missile has been launched. Of course, the specific connection method of the relays and contacts is not limited to the scheme in this embodiment, as long as it can ensure that the missile hook suspension signal on the inner and outer wing pylons is disconnected when the normal or emergency missile release signal is activated.

[0031] In this embodiment, as Figure 3 and Figure 6As shown, the controller in the functional control module also includes a switch K1 as a manual control circuit. The switch K1 is connected in series with contacts P1, P2, P3, and P4. The switch K1 has an automatic mode and a manual mode. When in the automatic mode, the switch K1 is closed, and when in the manual mode, the switch K1 is open. By manually operating the switch K1 to be in the closed or open state, the on / off state of the suspension signal of the bomb hook at the aircraft pylon end can be manually controlled.

[0032] Specifically, please refer to Figure 3 and Figure 6 The control switches include four JK-1 switches, whose main function is to manually and automatically control the on / off state of the bomb hook suspension signals on the inner and outer pylons of the left and right wings of the aircraft. Taking the outer pylon of the left wing as an example, one end of switch K1 is connected to contact P4, and the other end is connected to the suspension signal terminal of the aircraft. Switch K1 has an automatic position 1 and a manual position 2. When in automatic position 1, switch K1 is closed, and the on / off state of the bomb hook suspension signal is achieved by controlling the on / off state of the corresponding contacts through relays J1 and J2. When in manual position 2, switch K1 is open, thereby achieving manual control of disconnecting the bomb hook suspension signal. Similarly, switches K2, K3, and K4 are used to manually and automatically control the on / off state of the bomb hook suspension signals on the inner left wing, inner right wing, and outer right wing pylons, respectively. Their circuit connection method is the same as that of switch K1 on the outer left wing pylon of the aircraft, and will not be described again here.

[0033] In this embodiment, as Figure 3 and Figure 7 As shown, the function indicator module includes indicators D1, D2 and D3; The indicator D1 is connected to the aircraft's power supply terminal at one end and to the aircraft's suspension signal terminal at the other end to indicate the on / off state of the suspension signal of the bomb hook at the aircraft's pylon end. The indicator D2 is connected to the emergency release signal terminal of the aircraft at one end and to the ground terminal of the aircraft at the other end, so as to indicate the on / off state of the emergency release signal at the aircraft pylon end. The indicator D3 is connected at one end to the normal deployment signal terminal of the aircraft and at the other end to the ground terminal of the aircraft, so as to indicate the on / off state of the normal deployment signal at the aircraft pylon end.

[0034] In this embodiment, the indicators D1, D2, and D3 include, but are not limited to, signal lights, LEDs, small incandescent bulbs, neon lamps, fluorescent lamps, and OLEDs. Of course, the indicators can also be other observable modules, as long as the on / off state of the signal can be visually observed through their illumination. In this embodiment, signal lights are preferred as the indicators.

[0035] Specifically, please refer to Figure 3 and Figure 7The functional indicator module includes 12 ZSD-3 signal lights. Their main function is to determine the success of the external stores delivery system and the proper functioning of the bomb hook suspension by observing the on / off status of the signal lights during power-on checks of the external stores delivery system, when the normal and emergency delivery switches are activated in the aircraft cockpit. Specifically, signal lights D1, D4, D7, and D10 are connected in parallel between the power supply and suspension signal terminals on the inner and outer pylons of the left and right wings, respectively, to indicate the on / off status of the bomb hook suspension signal on the inner and outer pylons of the left and right wings; signal lights D2, D5, D8, and D11 are connected in parallel between the emergency delivery signal terminal and the grounding terminal on the inner and outer pylons of the left and right wings, respectively, to indicate the on / off status of the emergency delivery signal on the inner and outer pylons of the left and right wings; and signal lights D3, D6, D9, and D12 are connected in parallel between the normal delivery signal terminal and the grounding terminal on the inner and outer pylons of the left and right wings, respectively, to indicate the on / off status of the normal delivery signal on the inner and outer pylons of the left and right wings. The relationship between the illumination of signal lights and the function of the aircraft's external stores release system is as follows: Before the missile is launched normally or in an emergency, the P1-P2 and P3-P4 contacts of the relay are normally closed, and the inner and outer switches K1-K4 are closed. At this time, the missile hook suspension indicator lights D1, D4, D7, and D10 should light up, indicating that the missile has been properly suspended. By observing whether the missile hook suspension indicator lights are on or off, it is possible to determine whether the missile hook suspension function of each external payload delivery system is intact.

[0036] When the emergency release signal is activated on the inner or outer side of the missile, the P1-P2 or P3-P4 contacts of the relay will disconnect. At this time, the missile hook suspension indicator lights D1, D4, D7, and D10 will turn off, and the emergency release indicator lights D5, D8 or D2, D11 should light up, indicating that the emergency release is successful. By observing the on / off state of the emergency release indicator lights, it is possible to determine whether the emergency release circuit of each external payload release system is functioning properly.

[0037] When the missile is successfully launched, the P1-P2 or P3-P4 contacts of the relay will open. At this time, the missile hook suspension indicator lights D1, D4, D7, and D10 will turn off, and the normal launch indicator lights D3, D6, D9, and D12 should light up, indicating that the normal launch was successful. By observing whether the normal launch indicator lights are on or off, it is possible to determine whether the normal launch circuit of each external payload launch system is working properly.

[0038] In this embodiment, there are four sets of aircraft crosslinking interface modules, function control modules, and function indication modules, respectively connected to the outer side of the left wing, the inner side of the left wing, the outer side of the right wing, and the inner side of the right wing pylon, thereby realizing the functional detection of the external stores deployment system on the inner and outer pylons of the left and right wings. Its circuit structure is as follows: Figure 3As shown, from left to right, the circuit diagrams for the external stores delivery system testing equipment are as follows: left wing outer pylon, left wing inner pylon, right wing inner pylon, and right wing outer pylon. The specific structure of each circuit and the connection relationships of its components have been given above and will not be repeated here. Furthermore, the sockets, switches, relays, and indicator lights within the aircraft external stores delivery system testing equipment are interconnected by wires. Their main function is to transmit normal delivery signals, emergency delivery signals, power signals, grounding signals, and suspension signals of the aircraft external stores delivery system, thereby completing the system's functional power-on check.

[0039] In this embodiment, as Figure 3 and Figure 8 As shown, the aircraft external stores delivery system testing equipment also includes a housing and a control panel. The housing houses and secures the aircraft crosslink interface module, function control module, and function indicator module. The function indicator module and some function control modules are exposed on the control panel. The housing and control panel have mounting points for sockets, switches, relays, and indicator lights. Their main function is to integrate the various modules onto the housing and control panel, and they provide power-on operation prompts. The control panel is made of 1mm thick stainless steel plate. The equipment housing consists of a portable metal housing with a snap-on lid and a simple stainless steel panel, and is designed with various mounting points to ensure secure fixation of components and wiring harnesses. The crosslink interface module is designed with quick-release clamps and single-pin transmission for easy and rapid connection between the equipment and the aircraft.

[0040] Furthermore, this embodiment also provides a detection method using the above-mentioned aircraft external stores delivery system detection equipment, including the following steps: S1, connect the aircraft external load distribution system detection equipment to the aircraft end through the aircraft crosslink interface module and cable, set all power switches in the aircraft cockpit to the off position, connect the ground DC power supply to the aircraft, and turn on the ground power switch of the aircraft battery. S2, according to the requirements of the item to be tested, set the switch in the function control module to the automatic or manual position; S3, test the output of the aircraft suspension signal, normal deployment signal and emergency deployment signal, and confirm whether the test is qualified according to the status of the function indicator module.

[0041] In this embodiment, step S3 includes: S31, turn on the automatic protection switches for "outer tactical release" and "inner tactical release" on the aircraft, turn on the automatic protection switches for "firing and bombing" and "landing gear, navigation lights, and drag chute" on the aircraft, set the "bomb release selection" switch to the "inner / outer" position, set the weapon selection switch on the control box panel to the "bomb" position, and set switches K1, K2, K3, and K4 in the function control module located on the outer, inner, outer, and inner pylon ends of the left wing, left wing, right wing, and right wing, respectively, to the "manual" position; at this time, the indicators D1, D4, D7, and D10 in the function indication module that indicate the bomb hook suspension signal on the outer, inner, outer, and inner pylon ends of the left wing, left wing, right wing, and right wing, respectively, should be extinguished; S32, turn on the automatic protection switch for "emergency deployment of external objects" on the machine, and set switches K1, K2, K3 and K4 to the "automatic" position. At this time, indicators D1, D4, D7 and D10 should light up. Turn on the automatic protection switch for "emergency deployment of external objects" on the machine, and set switches K1, K2, K3 and K4 to the "manual" position. At this time, indicators D1, D4, D7 and D10 should be off. S33, lift the "XH-6 inspection light", press the "fire and bomb release" button, and set switches K1, K2, K3 and K4 to the "automatic" position. At this time, the indicators D3, D6, D9 and D12 in the function indicator module that indicate the normal release signal of the outer side of the left wing, the inner side of the left wing, the outer side of the right wing and the inner side of the right wing should light up. Release the "XH-6 Inspection Light" and "Fire and Bomb Discharge" buttons, and set switches K1, K2, K3 and K4 to the "Automatic" position. At this time, indicators D3, D6, D9 and D12 should be off. S34, turn on the automatic protection switch for "emergency release of external objects" on the aircraft, press the "release of internal suspended objects" button, and set switches K1, K2, K3 and K4 to the "automatic" position. At this time, the indicators D5 and D8 in the function indicator module that indicate the emergency release signal of the inner side of the left wing and the inner side of the right wing respectively should light up. Release the automatic protection switch for "Emergency Dispatch of External Items" on the machine, release the button for "Dispatch of Internal Suspended Items", and set switches K1, K2, K3 and K4 to the "Manual" or "Automatic" position. At this time, indicators D5 and D8 should be off. S35, turn on the automatic protection switch for "emergency release of external objects" on the aircraft, press the "release of external suspended objects" button, and set switches K1, K2, K3 and K4 to the "automatic" position. At this time, the indicators D2 and D11 in the function indicator module that indicate the emergency release signal on the outer side of the left wing and the outer side of the right wing respectively should light up. Release the automatic protection switch for "Emergency Drop of External Items" on the machine, release the "Drop of External Suspended Items" button, and set switches K1, K2, K3 and K4 to the "Automatic" position. At this time, indicators D2 and D11 should be off.

[0042] In a specific application embodiment, the crosslinking interface module is used to connect the aircraft external stores delivery system detection equipment to the aircraft. According to the power-on check requirements, control switches K1-K4 are set to the initial position (to manually check the operation of the missile control circuit on a certain pylon, turn on the control switch of that pylon; to automatically check all four pylons, turn on all control switches K1-K4 to the automatic position). All power switches in the cockpit are set to the "off" position. The 27V±2.7V DC power supply from the ground is connected to the aircraft, and the "battery ground power" switch on the aircraft is turned on.

[0043] After the preparation work is completed, crosslinking test is carried out according to the steps, test items and operation control contents in Table 1. Record the test results to see if they meet the qualification standards in Table 1.

[0044] Table 1. Cross-linking test contents between aircraft external stores delivery system testing equipment and aircraft external stores delivery system.

[0045] The above description is merely a preferred embodiment of the present invention. The scope of protection of the present invention is not limited to the above embodiments. All technical solutions falling within the scope of the present invention's concept are within the scope of protection of the present invention. It should be noted that for those skilled in the art, any improvements and modifications made without departing from the principles of the present invention should also be considered within the scope of protection of the present invention.

Claims

1. A detection device for an aircraft external stores delivery system, characterized in that, include: Aircraft cross-link interface module, function control module and function indication module; The aircraft crosslink interface module is connected to the aircraft pylon end to realize signal transmission between the aircraft pylon end and the detection equipment of the aircraft external load distribution system; The functional control module is connected to the aircraft cross-link interface module and controls the transmission of signals at the aircraft pylon end through the controllers located in the functional control module. The function indicator module is connected to the aircraft cross-link interface module and the function control module, and uses an indicator in the function indicator module to indicate whether the function of the aircraft external stores delivery system is normal. The control devices within the functional control module include relay J1 and relay J2; The relay J1 is connected to the aircraft emergency delivery signal terminal and the ground terminal respectively through the aircraft cross-linking interface module. The relay J1 controls the opening and closing of contacts P1 and P2. The relay J2 is connected to the aircraft's normal deployment signal terminal and ground terminal respectively via the aircraft crosslink interface module; the relay J2 controls the opening and closing of contacts P3 and P4; The contacts P1, P2, P3, and P4 are connected in series and connected in parallel between the grounding terminal and the aircraft suspension signal terminal through the aircraft crosslink interface module; the contacts P1 and P2 controlled by relay J1 and the contacts P3 and P4 controlled by relay J2 are normally closed. The control device in the functional control module also includes a switch K1, which is connected in series with contacts P1, P2, P3, and P4. The switch K1 has an automatic mode and a manual mode. When it is in the automatic mode, the switch K1 is closed, and when it is in the manual mode, the switch K1 is open. The function indicator module includes indicators D1, D2 and D3; The indicator D1 is connected to the aircraft's power supply terminal at one end and to the aircraft's suspension signal terminal at the other end to indicate the on / off state of the suspension signal of the bomb hook at the aircraft's pylon end. The indicator D2 is connected to the emergency release signal terminal of the aircraft at one end and to the ground terminal of the aircraft at the other end, so as to indicate the on / off state of the emergency release signal at the aircraft pylon end. The indicator D3 is connected at one end to the normal deployment signal terminal of the aircraft and at the other end to the ground terminal of the aircraft, so as to indicate the on / off state of the normal deployment signal at the aircraft pylon end.

2. The detection equipment for the aircraft external stores delivery system according to claim 1, characterized in that: The aircraft crosslink interface module includes multiple inner sockets, multiple external plugs connected to the inner sockets, and multiple crosslink interface cables connecting the external plugs to the aircraft rack end. The number of internal sockets, external plugs, and cross-linked interface cables are consistent. Each internal socket is connected to one external plug. Each external plug is connected to the aircraft's suspended signal terminal, power supply terminal, grounding terminal, emergency deployment signal terminal, and normal deployment signal terminal respectively through a cross-linked interface cable.

3. The detection equipment for the aircraft external stores delivery system according to claim 1, characterized in that: The indicator elements D1, D2, and D3 include one of the following: signal light, light-emitting diode (LED), small incandescent bulb, neon lamp, fluorescent lamp, and organic light-emitting diode (OLED).

4. The detection equipment for an aircraft external stores delivery system according to any one of claims 1-3, characterized in that: The number of aircraft crosslink interface modules, function control modules and function indication modules are all 4 sets, which are respectively connected to the outer side of the left wing, the inner side of the left wing, the outer side of the right wing and the inner side of the right wing pylon.

5. The detection equipment for an aircraft external stores delivery system according to any one of claims 1-3, characterized in that: The detection equipment for the aircraft external stores delivery system also includes a housing and a control panel. The housing houses and fixes the aircraft crosslink interface module, the function control module, and the function indicator module. The function indicator module and some of the function control modules are exposed on the control panel.

6. A detection method using the aircraft external stores delivery system detection equipment according to any one of claims 1-5, characterized in that, Including the following steps: S1, connect the aircraft external load distribution system detection equipment to the aircraft end through the aircraft crosslink interface module and cable, set all power switches in the aircraft cockpit to the off position, connect the ground DC power supply to the aircraft, and turn on the ground power switch of the aircraft battery. S2, according to the requirements of the item to be tested, set the switch in the function control module to the automatic or manual position; S3, test the output of the aircraft suspension signal, normal deployment signal and emergency deployment signal, and confirm whether the test is qualified according to the status of the function indicator module.

7. The detection method of the aircraft external stores delivery system detection equipment according to claim 6, characterized in that, Step S3 includes: S31, turn on the automatic protection switches for "outer tactical release" and "inner tactical release" on the aircraft, turn on the automatic protection switches for "firing and dropping bombs" and "landing gear, navigation lights, and drag chute" on the aircraft, set the "bomb release selection" switch to the "inner / outer" position, set the weapon selection switch on the control box panel to the "bomb" position, and set switches K1, K2, K3, and K4 in the function control module located on the outer, inner, outer, and inner pylon ends of the left wing, left wing, right wing, and right wing, respectively, to the "manual" position; at this time, the indicators D1, D4, D7, and D10 in the function indication module that indicate the bomb hook suspension signal on the outer, inner, outer, and inner pylon ends of the left wing, left wing, right wing, and right wing, respectively, should be extinguished; S32, turn on the automatic protection switch for "emergency deployment of external objects" on the machine, and set switches K1, K2, K3 and K4 to the "automatic" position. At this time, indicators D1, D4, D7 and D10 should light up. Turn on the automatic protection switch for "emergency deployment of external objects" on the machine, and set switches K1, K2, K3 and K4 to the "manual" position. At this time, indicators D1, D4, D7 and D10 should be off. S33, lift the "XH-6 inspection light", press the "fire and bomb release" button, and set switches K1, K2, K3 and K4 to the "automatic" position. At this time, the indicators D3, D6, D9 and D12 in the function indicator module that indicate the normal release signal of the outer side of the left wing, the inner side of the left wing, the outer side of the right wing and the inner side of the right wing should light up. Release the "XH-6 Inspection Light" and "Fire and Bomb Discharge" buttons, and set switches K1, K2, K3, and K4 to the "Automatic" position. At this time, indicators D3, D6, D9, and D12 should be off. S34, turn on the automatic protection switch for "emergency release of external objects" on the aircraft, press the "release of internal suspended objects" button, and set switches K1, K2, K3 and K4 to the "automatic" position. At this time, the indicators D5 and D8 in the function indicator module that indicate the emergency release signal of the inner side of the left wing and the inner side of the right wing respectively should light up. Release the "Emergency Dispatch of External Items" automatic protection switch on the machine, release the "Dispatch of Internal Suspended Items" button, and set switches K1, K2, K3 and K4 to the "Manual" or "Automatic" position. At this time, indicators D5 and D8 should be off. S35, turn on the automatic protection switch for "emergency release of external objects" on the aircraft, press the "release of external suspended objects" button, and set switches K1, K2, K3 and K4 to the "automatic" position. At this time, the indicators D2 and D11 in the function indicator module that indicate the emergency release signal of the outer side of the left wing and the outer side of the right wing of the aircraft should light up respectively. Release the "Emergency Drop of External Items" automatic protection switch on the machine, release the "Drop of External Suspended Items" button, and set switches K1, K2, K3 and K4 to the "Automatic" position. At this time, indicators D2 and D11 should be off.

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