Detection equipment and detection method for aircraft external store putting system

Abstract

The invention discloses detection equipment and a detection method for an aircraft external store delivery system. The equipment comprises an aircraft crosslinking interface module, a function control module and a function indication module, the aircraft cross-linking interface module is connected with the aircraft pylon end so as to realize signal transmission between the aircraft pylon end and the aircraft external store putting system detection equipment; the function control module is connected with the airplane cross-linking interface module, and controls signal transmission of an airplane hanger end through a control device arranged in the function control module; the function indication module is connected with the airplane crosslinking interface module and the function control module, and indicates whether the function of the airplane external store putting system is normal or not through an indication piece arranged in the function indication module. According to the invention, the circuit structure is simple, the cost is low, and the comprehensive test of each function of the external hanging object throwing system during the maintenance of an aircraft without a hanging rack or an ejection hanging hook is realized, so that the fault rate is reduced, the maintenance cost is saved, the maintenance range is shortened, the maintenance workload is reduced, and the availability of equipment is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft external store delivery system detection, and in particular to an aircraft external store delivery system detection device and a detection method. Background Art

[0002] The aircraft's external store delivery system is a system specifically used to manage and control aircraft external stores (such as weapons, fuel tanks, electronic pods, etc.). The system ensures that external stores can be released or dropped from the aircraft at a specified time and under safe conditions. Its main application scenarios include weapon delivery from military aircraft and load release in emergency situations on civil aircraft.

[0003] After the aircraft structure, finished products, cables and ducts are repaired, the external storage delivery system needs to be checked for functions when it enters the whole machine assembly and debugging stage. However, when the aircraft enters the factory for overhaul, some guide racks or catapult hooks in the guide racks are not brought into the factory, resulting in some functions of the external storage delivery system being unable to be powered on for inspection when the aircraft enters the whole machine debugging stage, making it impossible to ensure the integrity of some of the onboard lines and some finished accessories of the external storage system during the overhaul process. If an unchecked item fails in the military, it will require troubleshooting and rework inside and outside the field, which seriously affects the repair cycle and repair quality, increases maintenance costs, and reduces overall efficiency. Summary of the invention

[0004] Technical problem to be solved by the present invention: In view of the above-mentioned problems in the prior art, a detection device and a detection method for an aircraft external store delivery system are provided, which can realize power-on inspection of all functions of the external store delivery system on an aircraft that is not equipped with a hanger or catapult hook, thereby improving the reliability of the aircraft external store delivery system, shortening the delivery cycle, improving production efficiency, and ensuring delivery quality.

[0005] In order to solve the above technical problems, the technical solution adopted by the present invention is: An aircraft external storage delivery system detection 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 to the aircraft pylon end to realize signal transmission between the aircraft pylon end and the aircraft external storage delivery system detection equipment; The function control module is connected to the aircraft cross-linking interface module, and controls the transmission of the aircraft pylon end signal through the 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 storage delivery system is normal through the indicator arranged in the function indication module.

[0006] Further, the aircraft cross-linking interface module includes a plurality of internal sockets, a plurality of external plugs connected to the internal sockets, and a plurality of cross-linking interface cables connecting the external plugs to the aircraft pylon end; The numbers of the internal sockets, external plugs and cross-linked interface cables correspond to each other. Each of the internal sockets is plugged into an external plug. Each of the external plugs is connected to the aircraft suspension signal terminal, power supply terminal, grounding terminal, emergency delivery signal terminal and normal delivery signal terminal through a cross-linked interface cable.

[0007] Further, the control device in the functional control module includes a relay J1 and a relay J2; The two ends of the relay J1 are respectively connected to the aircraft emergency delivery signal end and the ground end through the aircraft cross-linking interface module, and the relay J1 controls the opening and closing of the contacts P1 and P2; The two ends of the relay J2 are respectively connected to the normal aircraft delivery signal end and the ground end through the aircraft cross-linking interface module; the relay J2 controls the opening and closing of the contacts P3 and P4; The contacts P1, P2, P3, and P4 are connected in series in sequence and are connected between the ground terminal and the aircraft suspension signal terminal through the aircraft cross-linking interface module; the contacts P1 and P2 controlled by the relay J1 and the contacts P3 and P4 controlled by the relay J2 are in a normally closed state.

[0008] Furthermore, 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 gear position and a manual gear position. When in the automatic gear position, the switch K1 is closed, and when in the manual gear position, the switch K1 is open.

[0009] Further, the function indication module includes indication elements D1, D2 and D3; One end of the indicator D1 is connected to the power supply end of the aircraft, and the other end is connected to the suspension signal end of the aircraft to indicate the on / off of the suspension signal of the bomb hook at the aircraft pylon end; One end of the indicator D2 is connected to the emergency delivery signal terminal of the aircraft, and the other end is connected to the ground terminal of the aircraft to indicate whether the emergency delivery signal at the aircraft hanger end is on or off; One end of the indicator D3 is connected to the normal delivery signal end of the aircraft, and the other end is connected to the ground end of the aircraft to indicate whether the normal delivery signal of the aircraft hanger end is on or off.

[0010] Furthermore, the indicator elements 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 the aircraft cross-linking interface modules, function control modules and function indication modules are 4 groups, which are respectively connected to the aircraft left wing outer side, left wing inner side, right wing outer side and right wing inner side mounting ends.

[0012] Furthermore, the aircraft external load delivery system detection equipment also includes a box and a control panel, the box accommodates and fixes the aircraft cross-linking interface module, the function control module and the function indication module, and the function indication module and part of the function control module are exposed on the control panel.

[0013] In addition, the present invention also provides a detection method using the above-mentioned aircraft external storage delivery system detection device, comprising the steps of: S1, connect the aircraft external load delivery system detection equipment to the aircraft end through the aircraft cross-linking interface module and the cable, set each power switch in the aircraft cabin to the off position, connect the ground DC power supply to the aircraft, and turn on the ground power switch of the battery on the aircraft; S2, according to the requirements of the item to be tested, placing the switch in the function control module in the automatic position or the manual position; S3, testing the output of the aircraft suspension signal, normal delivery signal and emergency delivery signal, and confirming whether the test is qualified according to the status of the function indication module.

[0014] Further, step S3 includes: S31, turn on the "outer tactical release" and "inner tactical release" automatic protection switches on the aircraft, turn on the "shooting and bombing", "landing gear, navigation lights, drag parachute" automatic protection switches on the aircraft, set the "bomb release selection" switch on the aircraft to the "inner and outer" position, set the weapon selection switch on the control box panel to the "bomb" position, and set the switches K1, K2, K3 and K4 located at the pylon ends of the aircraft's left wing outer side, left wing inner side, right wing outer side and right wing inner side in the function control module to the "manual" position; at this time, the indicator elements D1, D4, D7 and D10 in the function indication module that indicate the bomb hook hanging signals at the pylon ends of the aircraft's left wing outer side, left wing inner side, right wing outer side and right wing inner side should be extinguished; S32, turn on the automatic protection switch of "external load emergency release" on the aircraft, and put switches K1, K2, K3 and K4 in the "automatic" position. At this time, indicators D1, D4, D7 and D10 should light up; Turn on the automatic protection switch for "external load emergency release" on the aircraft, and set switches K1, K2, K3 and K4 to the "manual" position. At this time, indicators D1, D4, D7 and D10 should go out; S33, lift the "XH-6 inspection light", press the "shooting and bombing" button, and put switches K1, K2, K3 and K4 in the "automatic" position. At this time, the indicator D3, D6, D9 and D12 in the function indication module indicating the normal bombing signals of the aircraft's left wing outer side, left wing inner side, right wing outer side and right wing inner side pylon end should light up; Release the "XH-6 Light Check" and "Fire and Drop" buttons, and set switches K1, K2, K3 and K4 to the "Automatic" position. Indicators D3, D6, D9 and D12 should go out. S34, turn on the "external load emergency release" automatic protection switch on the aircraft, press the "inner load release" button, and put switches K1, K2, K3 and K4 in the "automatic" position. At this time, the indicator D5 and D8 indicating the emergency release signal of the inner side of the left wing and the inner side of the right wing of the aircraft in the function indication module should light up; Release the automatic protection switch of "external load emergency release" on the aircraft, release the button of "inner load release", and set switches K1, K2, K3 and K4 to "manual" or "automatic" position. At this time, indicators D5 and D8 should go out; S35, turn on the automatic protection switch of "external load emergency release" on the aircraft, press the "outer hanging load release" button, and put switches K1, K2, K3 and K4 in the "automatic" position. At this time, the indicator D2 and D11 indicating the emergency release signal of the hanger end of the outer side of the left wing and the outer side of the right wing of the aircraft in the function indication module should light up; Release the automatic protection switch of "external load emergency release" on the aircraft, release the "outer hanging load release" button, and put switches K1, K2, K3 and K4 in the "automatic" position. At this time, indicators D2 and D11 should go out.

[0015] Compared with the prior art, the advantages of the present invention are: The aircraft external store delivery system detection device of the present invention realizes the connection between the detection device and the aircraft external store delivery system through the aircraft cross-linking interface module, and controls the on-off of the hanging signal of the aircraft hanger end hook through the function control module, and then reflects whether the aircraft hanger hook hanging function and delivery function are normal according to the indication state of the function indication module during the test process. The circuit structure is simple and the cost is low, and a comprehensive test of various functions of the external store delivery system is realized during the maintenance of an aircraft not equipped with a hanger or an ejection hanger hook, which is conducive to discovering potential problems or faults in the system in advance, so that system and line faults can be effectively prevented before they occur, and they can be controlled and eliminated, thereby reducing the failure rate, saving maintenance costs, shortening the maintenance scope, reducing the maintenance workload, and improving the availability of equipment. In addition, problems such as wrong hanging or wrong delivery can be avoided through detection, and the reliability and safety of the aircraft external store delivery system during operation are further improved. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0017] Figure 2 It is a schematic diagram of the three-dimensional structure of the aircraft external storage delivery system detection equipment of this embodiment.

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

[0019] Figure 4 This is a schematic block diagram of the aircraft cross-linking interface module in the aircraft external storage delivery system detection equipment of this embodiment.

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

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

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

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

[0024] In order to better understand the above technical solution, the above technical solution will be described in detail below in conjunction with the accompanying drawings and specific implementation methods.

[0025] like Figures 1 to 3 As shown, an embodiment of the present invention provides an aircraft external storage delivery system detection device, including: an aircraft cross-linking interface module, a function control module and a function indication module; The aircraft cross-linking interface module is connected to the aircraft pylon end to realize signal transmission between the aircraft pylon end and the aircraft external storage delivery system detection equipment; The function control module is connected to the aircraft cross-linking interface module, and controls the transmission of the aircraft pylon end signal through the 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 storage delivery system is normal through the indicator arranged in the function indication module.

[0026] It can be understood that the aircraft external store delivery system detection equipment of this embodiment realizes the connection between the detection equipment and the aircraft external store delivery system through the aircraft cross-linking interface module, and controls the on-off of the aircraft hanger end hook hanging signal through the function control module, and then reflects whether the aircraft hanger hook hanging function and delivery function are normal according to the indication state of the function indication module during the test process. The circuit structure is simple and the cost is low, and a comprehensive test of various functions of the external store delivery system is realized during the maintenance of aircraft that are not equipped with hangers or catapult hooks, which is conducive to the early discovery of potential problems or faults in the system, so that system and line faults can be effectively prevented before they occur, and they can be controlled and eliminated, thereby reducing the failure rate, saving maintenance costs, shortening the maintenance scope, reducing the maintenance workload, and improving the availability of equipment. In addition, problems such as mishanging or misdelivery can be avoided through detection, further improving the reliability and safety of the aircraft external store delivery system during operation.

[0027] In this embodiment, Figure 3 and Figure 4 As shown, the aircraft cross-linking interface module includes a plurality of internal sockets, a plurality of external plugs connected to the internal sockets, and a plurality of cross-linking interface cables connecting the external plugs and the aircraft pylon ends; The numbers of the internal sockets, external plugs and cross-linked interface cables correspond to each other. Each of the internal sockets is plugged into an external plug. Each of the external plugs is connected to the aircraft suspension signal terminal, power supply terminal, grounding terminal, emergency delivery signal terminal and normal delivery signal terminal through a cross-linked interface cable.

[0028] Specifically, see Figure 3 and Figure 4 The aircraft cross-linking interface module includes 4 P20J9A sockets (inner sockets), 4 P20K9Q external plugs connected to the inner sockets one by one, 2 5.5-meter left and right inner bomb hook cross-linking interface cables, and 2 6-meter left and right outer bomb hook cross-linking interface cables. The 4 groups of sockets, plugs and cables are connected to the aircraft rack end 176, 180, 142 and 162 plugs (representing the aircraft left wing outer side, left wing inner side, right wing outer side, right wing inner side rack end, respectively) through a P32J11Q socket, thereby realizing the transmission between the aircraft signal and the detection equipment. Of course, the plug and socket models of the aircraft cross-linking interface module and the length of the cross-linking interface cable are not unique and can be adjusted according to actual conditions.

[0029] In this embodiment, Figure 3 and Figure 5 As shown, the control device in the functional control module includes relay J1 and relay J2 as automatic control circuits; The two ends of the relay J1 are respectively connected to the aircraft emergency delivery signal end and the ground end through the aircraft cross-linking interface module, and the relay J1 controls the opening and closing of the contacts P1 and P2; The two ends of the relay J2 are respectively connected to the normal aircraft delivery signal end and the ground end through the aircraft cross-linking interface module; the relay J2 controls the opening and closing of the contacts P3 and P4; The contacts P1, P2, P3, and P4 are connected in series in sequence, and are connected between the ground terminal and the aircraft suspension signal terminal through the aircraft cross-linking interface module; when no normal aircraft delivery signal or emergency delivery signal is received, the contacts P1 and P2 controlled by the relay J1 and the contacts P3 and P4 controlled by the relay J2 are in a normally closed state.

[0030] Specifically, see Figure 3 and Figure 5 The function control module is composed of 8 J300-C1A relays. Its main function is to disconnect the suspension signal of the inner and outer pylons of the left and right wings of the aircraft when the normal release signal or emergency release signal of the pylon missile is connected. Taking the outer pylon of the left wing of the aircraft as an example, the two ends of the relay J1 are connected to the aircraft emergency release signal end and the ground end respectively, and the two ends of the relay J2 are connected to the aircraft normal release signal end and the ground end respectively; before the normal or emergency release signal of the missile is connected, the P1-P2 contact controlled by the relay J1 is normally closed, and the P3-P4 contact controlled by the relay J2 is normally closed, so that the aircraft suspension signal can be output normally, which means that the trajectory has been suspended; when the normal or emergency release signal of the missile is connected, the P1-P2 contact or the P3-P4 contact is disconnected, which means that the normal or emergency missile release is successful. Similarly, relays J3-J8 control the on / off of the hanger signals of the bomb hooks on the inner side of the left wing, the inner side of the right wing, and the outer side of the right wing, respectively. The circuit connection method is the same as the connection method of relays J1 and J2 on the outer side of the left wing of the aircraft, so it will not be repeated here. Figure 5 The hook suspension feedback signal is a ground signal to the hook suspension indicator light in the aircraft cockpit, and the hook suspension signal indicates the current state of the hook. The light is on, indicating that the hook has suspended a missile, and the light is off, indicating that no missile is suspended or the missile has been launched. Of course, the specific connection method of the relay and the contact is not limited to the solution of this embodiment, as long as the hook suspension signal of the inner and outer pylons of the left and right wings can be disconnected when the normal or emergency release signal of the pylon missile is connected.

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

[0032] Specifically, see Figure 3 and Figure 6 , the control switch includes 4 JK-1 switches, whose main function is to realize the manual and automatic control of the on-off of the hanging signal of the hanging hook of the inner and outer pylons of the left and right wings of the aircraft. Taking the outer pylon of the left wing of the aircraft as an example, one end of the switch K1 is connected to the contact P4 and the other end is connected to the hanging signal end of the aircraft, and the switch K1 has an automatic gear position 1 and a manual gear position 2. When it is set to the automatic gear position 1, the switch K1 is in a closed state. At this time, the on-off of the hanging signal of the hanging hook of the hanging rack is realized by controlling the on-off of the corresponding contacts by relays J1 and J2; when it is set to the manual gear position 2, the switch K1 is disconnected, thereby realizing the disconnection of the hanging signal of the hanging hook of the hanging rack manually controlled. Similarly, switches K2, K3 and K4 are used for manual and automatic control of the on-off of the hanging signal of the hanging hook of the inner side of the left wing, the inner side of the right wing and the outer side of the right wing, respectively. The circuit connection method is consistent with the connection method of the switch K1 of the outer pylon of the left wing of the aircraft, which will not be repeated here.

[0033] In this embodiment, Figure 3 and Figure 7 As shown, the function indication module includes indication elements D1, D2 and D3; One end of the indicator D1 is connected to the power supply end of the aircraft, and the other end is connected to the suspension signal end of the aircraft to indicate the on / off of the suspension signal of the bomb hook at the aircraft pylon end; One end of the indicator D2 is connected to the emergency delivery signal terminal of the aircraft, and the other end is connected to the ground terminal of the aircraft to indicate whether the emergency delivery signal at the aircraft hanger end is on or off; One end of the indicator D3 is connected to the normal delivery signal end of the aircraft, and the other end is connected to the ground end of the aircraft to indicate whether the normal delivery signal of the aircraft hanger end is on or off.

[0034] In this embodiment, the indicator D1, D2 and D3 include but are not limited to signal lights, light emitting diodes LED, small incandescent bulbs, neon lamps, fluorescent lamps and organic light emitting diodes OLED. Of course, the indicator can also be other forms of observable modules, as long as the on and off of the signal can be observed intuitively by turning on and off. In this embodiment, a signal light is preferably used as the indicator.

[0035] Specifically, see Figure 3 and Figure 7The function indication module includes 12 ZSD-3 signal lights, whose main function is to judge whether the corresponding delivery is successful and whether the hanging function of the bomb hook is intact by the "on and off" of the signal lights when the external storage delivery system is powered on for inspection, when the normal delivery and emergency delivery switches in the aircraft cockpit are turned on. Among them, the signal lights D1, D4, D7, and D10 are respectively connected in parallel between the power supply terminal and the hanging signal terminal of the inner and outer hanger ends of the left and right wings of the aircraft, and are used to indicate the on and off of the hanging signal of the bomb hook at the inner and outer hanger ends of the left and right wings of the aircraft; the signal lights D2, D5, D8, and D11 are respectively connected in parallel between the emergency delivery signal terminal and the ground terminal of the inner and outer hanger ends of the left and right wings of the aircraft, and are used to indicate the on and off of the emergency delivery signal of the inner and outer hanger ends of the left and right wings of the aircraft; the signal lights D3, D6, D9, and D12 are respectively connected in parallel between the normal delivery signal terminal and the ground terminal of the inner and outer hanger ends of the left and right wings of the aircraft, and are used to indicate the on and off of the normal delivery signal of the inner and outer hanger ends of the left and right wings of the aircraft. The relationship between the on and off of the signal light and the function of the aircraft external storage delivery system is as follows: When the missile is normally or before the emergency release signal is connected, 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 hanging signal lights D1, D4, D7, and D10 should light up, indicating that the missile has been hung. By turning on and off the missile hook hanging signal lights, it can be judged whether the missile hook hanging function of each rack external storage release system is intact.

[0036] When the emergency release signal from the inside or outside of the missile is connected, the P1-P2 or P3-P4 contacts of the relay are disconnected. At this time, the hanging signal lights D1, D4, D7, and D10 of the missile hook go out, and the emergency release signal lights D5, D8 or D2, D11 should light up, indicating that the emergency release is successful. By turning on and off the emergency release signal lights, it can be judged whether the emergency release circuits of each hanger external storage release system are working properly.

[0037] When the normal missile release signal is connected, the P1-P2 or P3-P4 contacts of the relay are disconnected, and the missile hook hanging signal lights D1, D4, D7, and D10 go out, and the normal release signal lights D3, D6, D9, and D12 should light up, indicating that the normal release is successful. By turning on and off the normal release signal lights, it can be judged whether the normal release circuits of each hanger external storage release system are working properly.

[0038] In this embodiment, the number of aircraft cross-linking interface modules, function control modules and function indication modules are all 4 groups, which are respectively connected to the aircraft left wing outer side, left wing inner side, right wing outer side and right wing inner side pylon ends, so as to respectively realize the function detection of the external storage delivery system of the inner and outer pylon ends of the left and right wings of the aircraft. Its circuit structure is as follows Figure 3As shown, from left to right are the circuit diagrams corresponding to the left wing outer pylon, the left wing inner pylon, the right wing inner pylon, and the right wing outer pylon external storage delivery system detection equipment. The specific structure of each part of the circuit and the connection relationship of the components have been given above and will not be repeated here. In addition, the sockets, switches, relays and signal lights in the aircraft external storage delivery system detection equipment are connected to each other by wires. Their main function is to complete the transmission of the normal delivery signal, emergency delivery signal, power supply signal, grounding signal and suspension signal of the aircraft external storage delivery system to complete the system's functional power-on inspection.

[0039] In this embodiment, Figure 3 and Figure 8 As shown, the aircraft external storage delivery system detection equipment also includes a box and a control panel. The box is used to accommodate and fix the aircraft cross-linking interface module, function control module and function indication module. The function indication module and part of the function control module are exposed on the control panel. The box and the control panel are provided with fixing points for the installation of sockets, switches, relays and signal lights. Its main function is to integrate various modules on the box and the control panel, and it is accompanied by prompt information for power-on operation. The control panel is made of 1mm thick stainless steel plate corrosion. The equipment box is composed of a portable metal box with a snap-on box cover and a simple and clear stainless steel panel. Various fixing points are designed to facilitate the secure fixation of various components and wiring harnesses. The equipment cross-linking interface module is designed in the form of a quick-release clamp and single-pin transmission, which is convenient for the quick connection of the equipment and the aircraft.

[0040] In addition, this embodiment also provides a detection method using the above-mentioned aircraft external storage delivery system detection device, including the steps of: S1, connect the aircraft external load delivery system detection equipment to the aircraft end through the aircraft cross-linking interface module and the cable, set each power switch in the aircraft cabin to the off position, connect the ground DC power supply to the aircraft, and turn on the ground power switch of the battery on the aircraft; S2, according to the requirements of the item to be tested, placing the switch in the function control module in the automatic position or the manual position; S3, testing the output of the aircraft suspension signal, normal delivery signal and emergency delivery signal, and confirming whether the test is qualified according to the status of the function indication module.

[0041] In this embodiment, step S3 includes: S31, turn on the "outer tactical release" and "inner tactical release" automatic protection switches on the aircraft, turn on the "shooting and bombing", "landing gear, navigation lights, drag parachute" automatic protection switches on the aircraft, set the "bomb release selection" switch on the aircraft to the "inner and outer" position, set the weapon selection switch on the control box panel to the "bomb" position, and set the switches K1, K2, K3 and K4 located at the pylon ends of the aircraft's left wing outer side, left wing inner side, right wing outer side and right wing inner side in the function control module to the "manual" position; at this time, the indicator elements D1, D4, D7 and D10 in the function indication module that indicate the bomb hook hanging signals at the pylon ends of the aircraft's left wing outer side, left wing inner side, right wing outer side and right wing inner side should be extinguished; S32, turn on the automatic protection switch of "external load emergency release" on the aircraft, and put switches K1, K2, K3 and K4 in the "automatic" position. At this time, indicators D1, D4, D7 and D10 should light up; Turn on the automatic protection switch for "external load emergency release" on the aircraft, and set switches K1, K2, K3 and K4 to the "manual" position. At this time, indicators D1, D4, D7 and D10 should go out; S33, lift the "XH-6 inspection light", press the "shooting and bombing" button, and put switches K1, K2, K3 and K4 in the "automatic" position. At this time, the indicator D3, D6, D9 and D12 in the function indication module indicating the normal bombing signals of the aircraft's left wing outer side, left wing inner side, right wing outer side and right wing inner side pylon end should light up; Release the "XH-6 Light Check" and "Fire and Drop" buttons, and set switches K1, K2, K3 and K4 to the "Automatic" position. Indicators D3, D6, D9 and D12 should go out. S34, turn on the "external load emergency release" automatic protection switch on the aircraft, press the "inner load release" button, and put switches K1, K2, K3 and K4 in the "automatic" position. At this time, the indicator D5 and D8 indicating the emergency release signal of the inner side of the left wing and the inner side of the right wing of the aircraft in the function indication module should light up; Release the automatic protection switch of "external load emergency release" on the aircraft, release the button of "inner load release", and set switches K1, K2, K3 and K4 to "manual" or "automatic" position. At this time, indicators D5 and D8 should go out; S35, turn on the automatic protection switch of "external load emergency release" on the aircraft, press the "outer hanging load release" button, and put switches K1, K2, K3 and K4 in the "automatic" position. At this time, the indicator D2 and D11 indicating the emergency release signal of the hanger end of the outer side of the left wing and the outer side of the right wing of the aircraft in the function indication module should light up; Release the automatic protection switch of "external load emergency release" on the aircraft, release the "outer hanging load release" button, and put switches K1, K2, K3 and K4 in the "automatic" position. At this time, indicators D2 and D11 should go out.

[0042] In a specific application embodiment, the aircraft external storage delivery system detection equipment is connected to the aircraft end through the cable of the cross-linking interface module, and the control switches K1-K4 are placed in the initial position according to the power-on inspection requirements (manually check the working condition of the missile control circuit on a certain rack and turn on a certain rack control switch, and automatically check the four racks and turn all the control switches K1-K4 to the automatic gear position), and the power switches in the cockpit are placed in the "off" position, the ground 27V±2.7V DC power supply is connected to the aircraft, and the "battery ground power supply" switch on the aircraft is turned on.

[0043] After the preparation work is completed, the cross-linking test is carried out according to the steps, test items and operation control contents in Table 1, and the test results are recorded according to whether they meet the qualification standards in Table 1.

[0044] Table 1 Cross-linking test contents between aircraft external store delivery system detection equipment and aircraft external store delivery system

[0045] The above is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above embodiments. All technical solutions under the concept of the present invention belong to the protection scope of the present invention. It should be pointed out that for ordinary technicians in this technical field, some improvements and modifications without departing from the principle of the present invention should also be regarded as the protection scope of the present invention.

Claims

1. An aircraft external storage delivery system detection device, characterized in that: include: Aircraft cross-linking interface module, function control module and function indication module; The aircraft cross-linking interface module is connected to the aircraft pylon end to realize signal transmission between the aircraft pylon end and the aircraft external storage delivery system detection equipment; The function control module is connected to the aircraft cross-linking interface module, and controls the transmission of the aircraft rack end signal through the 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 storage delivery system is normal through the indicator arranged in the function indication module.

2. The aircraft external storage delivery system detection device according to claim 1, characterized in that: The aircraft cross-linking interface module includes a plurality of internal sockets, a plurality of external plugs connected to the internal sockets, and a plurality of cross-linking interface cables connecting the external plugs and the aircraft pylon ends; The numbers of the internal sockets, external plugs and cross-linked interface cables correspond to each other. Each of the internal sockets is plugged into an external plug. Each of the external plugs is connected to the aircraft suspension signal terminal, power supply terminal, grounding terminal, emergency delivery signal terminal and normal delivery signal terminal through a cross-linked interface cable.

3. The aircraft external storage delivery system detection device according to claim 1, characterized in that: The control devices in the functional control module include relay J1 and relay J2; The two ends of the relay J1 are respectively connected to the aircraft emergency delivery signal terminal and the ground terminal through the aircraft cross-linking interface module, and the relay J1 controls the opening and closing of the contacts P1 and P2; The two ends of the relay J2 are respectively connected to the normal aircraft delivery signal end and the ground end through the aircraft cross-linking interface module; the relay J2 controls the opening and closing of the contacts P3 and P4; The contacts P1, P2, P3, and P4 are connected in series in sequence and are connected between the ground terminal and the aircraft suspension signal terminal through the aircraft cross-linking interface module; the contacts P1 and P2 controlled by the relay J1 and the contacts P3 and P4 controlled by the relay J2 are in a normally closed state.

4. The aircraft external storage delivery system detection device according to claim 3 is characterized in that: 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 gear position and a manual gear position. When in the automatic gear position, the switch K1 is closed, and when in the manual gear position, the switch K1 is open.

5. The aircraft external storage delivery system detection equipment according to claim 1, characterized in that: The function indication module includes indication elements D1, D2 and D3; One end of the indicator D1 is connected to the power supply end of the aircraft, and the other end is connected to the suspension signal end of the aircraft to indicate the on / off of the suspension signal of the bomb hook at the aircraft pylon end; One end of the indicator D2 is connected to the emergency delivery signal terminal of the aircraft, and the other end is connected to the ground terminal of the aircraft to indicate whether the emergency delivery signal at the aircraft hanger end is on or off; One end of the indicator D3 is connected to the normal delivery signal end of the aircraft, and the other end is connected to the ground end of the aircraft to indicate whether the normal delivery signal of the aircraft hanger end is on or off.

6. The aircraft external storage delivery system detection device according to claim 5, characterized in that: 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).

7. The aircraft external storage delivery system detection device according to any one of claims 1 to 6, characterized in that: The number of the aircraft cross-linking interface modules, function control modules and function indication modules are all 4 groups, which are respectively connected to the aircraft left wing outer side, left wing inner side, right wing outer side and right wing inner side mounting bracket ends.

8. The aircraft external storage delivery system detection device according to any one of claims 1 to 6, characterized in that: The aircraft external load delivery system detection equipment also includes a box and a control panel. The box accommodates and fixes the aircraft cross-linking interface module, the function control module and the function indication module. The function indication module and part of the function control module are exposed on the control panel.

9. A detection method using the aircraft external storage delivery system detection device according to any one of claims 1 to 8, characterized in that: Includes steps: S1, connect the aircraft external load delivery system detection equipment to the aircraft end through the aircraft cross-linking interface module and the cable, set each power switch in the aircraft cabin to the off position, connect the ground DC power supply to the aircraft, and turn on the ground power switch of the battery on the aircraft; S2, according to the requirements of the item to be tested, placing the switch in the function control module in the automatic position or the manual position; S3, testing the output of the aircraft suspension signal, normal delivery signal and emergency delivery signal, and confirming whether the test is qualified according to the status of the function indication module.

10. The detection method of the aircraft external storage delivery system detection equipment according to claim 9, characterized in that: Step S3 includes: S31, turn on the "outer tactical release" and "inner tactical release" automatic protection switches on the aircraft, turn on the "shooting and bombing" and "landing gear, navigation lights, drag parachute" automatic protection switches on the aircraft, set the "bomb release selection" switch on the aircraft to the "inner and outer" position, set the weapon selection switch on the control box panel to the "bomb" position, and set the switches K1, K2, K3 and K4 located at the pylon ends of the aircraft's left wing outer side, left wing inner side, right wing outer side and right wing inner side in the function control module to the "manual" position; at this time, the indicator elements D1, D4, D7 and D10 in the function indication module that indicate the bomb hook hanging signals at the pylon ends of the aircraft's left wing outer side, left wing inner side, right wing outer side and right wing inner side should be extinguished; S32, turn on the "external load emergency release" automatic protection switch on the aircraft, and put switches K1, K2, K3 and K4 in the "automatic" position. At this time, indicators D1, D4, D7 and D10 should light up; Turn on the "external load emergency release" automatic protection switch on the aircraft, and set switches K1, K2, K3 and K4 to the "manual" position. At this time, indicators D1, D4, D7 and D10 should go out; S33, lift the "XH-6 inspection light", press the "shooting and bombing" button, and put switches K1, K2, K3 and K4 in the "automatic" position. At this time, the indicator D3, D6, D9 and D12 in the function indication module indicating the normal bombing signals of the aircraft's left wing outer side, left wing inner side, right wing outer side and right wing inner side pylon end should light up; Release the "XH-6 Light Check" and "Fire and Drop" buttons, and set switches K1, K2, K3 and K4 to the "Automatic" position. At this time, indicators D3, D6, D9 and D12 should go out. S34, turn on the "external load emergency release" automatic protection switch on the aircraft, press the "inner load release" button, and put switches K1, K2, K3 and K4 in the "automatic" position. At this time, the indicator D5 and D8 indicating the emergency release signal of the inner side of the left wing and the inner side of the right wing of the aircraft in the function indication module should light up; Release the "external load emergency release" automatic protection switch on the aircraft, release the "inner load release" button, and set switches K1, K2, K3 and K4 to the "manual" or "automatic" position. At this time, indicators D5 and D8 should go out; S35, turn on the "external storage emergency release" automatic protection switch on the aircraft, press the "outer storage release" button, and put switches K1, K2, K3 and K4 in the "automatic" position. At this time, the indicator D2 and D11 indicating the emergency release signal of the outer side of the left wing and the outer side of the right wing of the aircraft in the function indication module should light up; Release the automatic protection switch of "external load emergency release" on the aircraft, release the "outer hanging load release" button, and put switches K1, K2, K3 and K4 in the "automatic" position. At this time, indicators D2 and D11 should go out.

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