Detection equipment for aircraft external store delivery system

Abstract

The utility model discloses detection equipment for an external store putting system of an airplane. The detection equipment comprises an airplane 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. The device is simple in circuit structure and low in cost, and realizes comprehensive testing of each function of the external hanging object throwing system when an airplane without a hanging rack or an ejection hanging hook is overhauled, thereby reducing the failure rate, saving the maintenance cost, shortening the maintenance range, reducing the maintenance workload and improving the availability rate of equipment.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft external store release system detection, and particularly relates to an aircraft external store release system detection device. Background Art

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

[0003] After the repair of the aircraft's structure, components, cables, and ducts, etc., when entering the overall assembly and commissioning stage, it is necessary to conduct a functional inspection on the external store release system. However, when the aircraft enters the factory for major overhaul, some guide brackets or ejection cartridge hooks inside the guide brackets are not brought into the factory, resulting in the inability to power on and check some functions of the external store release system when the aircraft enters the overall commissioning stage, making it impossible to ensure the integrity of some on-board circuits and some finished accessories of the external store system during the major overhaul process. If a failure occurs in the items that have not been inspected in the troops, it is necessary to troubleshoot and rework both in the field and in the factory, seriously affecting the repair cycle and repair quality, increasing the maintenance cost, and reducing the overall efficiency. Content of the Utility Model

[0004] The technical problem to be solved by the utility model: Aiming at the above problems of the prior art, an aircraft external store release system detection device is provided, which can realize the power-on inspection of all functions of the external store release system on an aircraft without equipped with a rack or an ejection cartridge hook, thereby improving the reliability of the operation of the aircraft external store release 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 utility model is as follows:

[0006] An aircraft external store release system detection device, comprising: an aircraft cross-linking interface module, a function control module, and a function indication module;

[0007] The aircraft cross-linking interface module is connected to the aircraft rack end to realize signal transmission between the aircraft rack end and the aircraft external store release system detection device;

[0008] The function control module is connected to the aircraft cross-linking interface module and controls the signal transmission of the aircraft rack end through a control device provided in the function control module;

[0009] The function indication module is connected to the aircraft cross-linking interface module and the function control module, and indicates whether the functions of the aircraft external store release system are normal through an indicating device provided in the function indication module.

[0010] Further, the aircraft cross-linking interface module includes a plurality of inner sockets, a plurality of external plugs connected to the inner sockets, and a plurality of cross-linking interface cables connecting the external plugs to the aircraft pylon end.

[0011] Further, the numbers of the inner sockets, the external plugs, and the cross-linking interface cables correspond to each other. Each inner socket is correspondingly plugged with an external plug, and the external plug is respectively connected to the aircraft suspension signal end, the power supply end, the grounding end, the emergency release signal end, and the normal release signal end through the cross-linking interface cable.

[0012] Further, the control devices in the function control module include a relay J1 and a relay J2;

[0013] Both ends of the relay J1 are respectively connected to the aircraft emergency release signal end and the grounding end through the aircraft cross-linking interface module, and the relay J1 controls the opening and closing of the contact points P1 and P2;

[0014] Both ends of the relay J2 are respectively connected to the aircraft normal release signal end and the grounding end through the aircraft cross-linking interface module; the relay J2 controls the opening and closing of the contact points P3 and P4;

[0015] The contact points P1, P2, P3, and P4 are connected in series in sequence, and are connected in parallel between the grounding end and the aircraft suspension signal end through the aircraft cross-linking interface module; the contact points P1 and P2 controlled by the relay J1 and the contact points P3 and P4 controlled by the relay J2 are in the normally closed state.

[0016] Further, the control devices in the function control module further include a switch K1, and the switch K1 is connected in series with the contact points P1, P2, P3, and P4.

[0017] Further, the switch K1 has an automatic gear and a manual gear. When in the automatic gear, the switch K1 is closed, and when in the manual gear, the switch K1 is opened.

[0018] Further, the function indication module includes indicating elements D1, D2, and D3;

[0019] One end of the indicating element 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;

[0020] One end of the indicating element D2 is connected to the emergency release signal end of the aircraft, and the other end is connected to the grounding end of the aircraft to indicate the on / off of the emergency release signal at the aircraft pylon end;

[0021] One end of the indicating element D3 is connected to the normal release signal end of the aircraft, and the other end is connected to the grounding end of the aircraft to indicate the on / off of the normal release signal at the aircraft pylon end.

[0022] Furthermore, the indicating parts D1, D2 and D3 are all signal lights.

[0023] Furthermore, the numbers of the aircraft cross-linking interface module, the function control module and the function indicating module are all 4 groups, which are respectively connected to the outer side of the left wing of the aircraft, the inner side of the left wing, the outer side of the right wing and the inner side of the right wing pylon end.

[0024] Furthermore, the aircraft external stores release system detection device further includes a box body and a control panel. The box body houses and fixes the aircraft cross-linking interface module, the function control module and the function indicating module, and the function indicating module and part of the function control module are exposed outside the control panel.

[0025] Compared with the prior art, the advantages of the present utility model are as follows:

[0026] The aircraft external stores release system detection device of the present utility model realizes the connection between the detection device and the aircraft external stores release system through the aircraft cross-linking interface module, controls the on-off of the signals at the aircraft pylon end through the function control module, and then reflects whether the functions of the aircraft external stores release system (such as the bomb suspension function and the release function) are normal according to the indication status of the function indicating module during the test. The circuit structure is simple and the cost is low. It realizes the comprehensive test of each function of the aircraft external stores release system during the maintenance of the aircraft without equipped pylons or ejection bomb hooks, which is beneficial to discovering potential problems or faults in the system in advance, effectively preventing the system and line faults before they occur, controlling and eliminating them, thereby reducing the failure rate, saving the maintenance cost, shortening the maintenance scope, reducing the maintenance workload, improving the availability of the equipment, and avoiding problems such as mis-hanging or mis-releasing through detection, further improving the reliability and safety of the aircraft external stores release system during operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a schematic block diagram of the structure of the aircraft external stores release system detection device according to an embodiment of the present utility model.

[0028] Figure 2 It is a schematic three-dimensional structure diagram of the aircraft external stores release system detection device according to this embodiment.

[0029] Figure 3 It is a circuit schematic diagram of the aircraft external stores release system detection device according to this embodiment.

[0030] Figure 4 It is a schematic block diagram of the aircraft cross-linking interface module in the aircraft external stores release system detection device according to this embodiment.

[0031] Figure 5 It is a schematic block diagram of the automatic control circuit in the function control module of the aircraft external stores release system detection device according to this embodiment.

[0032] Figure 6 It is a schematic block diagram of the manual control circuit in the function control module of the aircraft external store release system detection equipment for this embodiment.

[0033] Figure 7 It is a schematic block diagram of the function indication module of the aircraft external store release system detection equipment for this embodiment.

[0034] Figure 8 It is a schematic diagram of the control panel of the aircraft external store release system detection equipment for this embodiment. Specific implementation manners

[0035] In order to better understand the above technical solutions, the above technical solutions will be described in detail below in conjunction with the accompanying drawings of the specification and specific implementation manners.

[0036] As Figures 1 to 3 shown, an embodiment of the present utility model provides an aircraft external store release system detection equipment, including: an aircraft cross-linking interface module, a function control module and a function indication module;

[0037] 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 store release system detection equipment;

[0038] The function control module is connected to the aircraft cross-linking interface module and controls the signal transmission of the aircraft pylon end through a control device provided in the function control module;

[0039] The function indication module is connected to the aircraft cross-linking interface module and the function control module, and indicates whether the functions of the aircraft external store release system are normal through an indicating device provided in the function indication module.

[0040] It can be understood that the aircraft external store release system detection equipment of this embodiment realizes the connection between the detection equipment and the aircraft external store release system through the aircraft cross-linking interface module, controls the on-off of the signal of the aircraft pylon end through the function control module, and then reflects whether the functions of the aircraft external store release system (such as the bomb hook suspension function and the release function) are normal according to the indication state of the function indication module during the test. The circuit structure is simple, the cost is low, and it realizes the comprehensive test of each function of the external store release system during the maintenance of aircraft without equipped pylons or ejection bomb hooks, which is conducive to discovering potential problems or faults in the system in advance, effectively preventing the system and line faults before they occur, and being controlled and eliminated, thereby reducing the failure rate, saving the maintenance cost, shortening the maintenance scope, reducing the maintenance workload, improving the availability of the equipment, and avoiding problems such as mis-hanging or mis-throwing through detection, further improving the reliability and safety of the aircraft external store release system during operation.

[0041] In this embodiment, as Figure 3 and Figure 4 shown, the aircraft cross-link interface module includes a plurality of inner sockets, a plurality of external plugs connected to the inner sockets, and a plurality of cross-link interface cables connecting the external plugs to the aircraft pylon end.

[0042] In this embodiment, the numbers of the inner sockets, the external plugs, and the cross-link interface cables correspond to each other. Each inner socket is correspondingly plugged into an external plug, and each external plug is respectively connected to the aircraft suspension signal end, the power supply end, the ground end, the emergency release signal end, and the normal release signal end through a cross-link interface cable.

[0043] Specifically, please refer to Figure 3 and Figure 4 . Since the aircraft pylon end includes the outer side of the left wing of the aircraft, the inner side of the left wing, the outer side of the right wing, and the inner side of the right wing pylon end, the aircraft cross-link interface module correspondingly includes 4 P20J9A type sockets (inner sockets), 4 P20K9Q type external plugs that are docked with the inner sockets one by one, 2 5.5-meter left and right inner bomb hook cross-link interface cables, and 2 6-meter left and right outer bomb hook cross-link interface cables. The 4 groups of sockets, plugs, and cables are respectively connected to the aircraft pylon end 176, 180, 142, and 162 plugs (representing the outer side of the left wing of the aircraft, the inner side of the left wing, the outer side of the right wing, and the inner side of the right wing pylon end respectively) through a P32J11Q type socket, so as to realize the transmission between the aircraft signal and the detection equipment. Of course, the plug and socket models of the aircraft cross-link interface module and the length of the cross-link interface cable are not unique and can be adjusted according to the actual situation.

[0044] In this embodiment, as Figure 3 and Figure 5 shown, the control devices in the function control module include relay J1 and relay J2;

[0045] Both ends of relay J1 are respectively connected to the aircraft emergency release signal end and the ground end through the aircraft cross-link interface module, and relay J1 controls the opening and closing of the control contacts P1 and P2;

[0046] Both ends of relay J2 are respectively connected to the aircraft normal release signal end and the ground end through the aircraft cross-link interface module; relay J2 controls the opening and closing of the control contacts P3 and P4; the on-off of the bomb hook suspension signal at the aircraft pylon end is controlled through the automatic control circuit composed of relay J1 and J2 and the control contacts P1 and P2, P3 and P4 controlled by them respectively;

[0047] The contacts P1, P2, P3, and P4 are connected in series in sequence, and are connected in parallel between the grounding terminal and the aircraft suspension signal terminal through the aircraft cross-link interface module. Among them, the contact P1 is connected to the grounding terminal, and the contact P4 is connected to the aircraft suspension signal terminal through the aircraft cross-link interface module. When the normal release signal or emergency release signal of the aircraft is not received, the contacts P1 and P2 controlled by the relay J1 and the contacts P3 and P4 controlled by the relay J2 are in the normally closed state.

[0048] Specifically, please refer to Figure 3 and Figure 5 , the function control module consists of 8 J300-C1A relays. Its main function is to control the disconnection of the suspension signals of the missile hooks on the inner and outer sides 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 on the left wing of the aircraft as an example, the two ends of the relay J1 are respectively connected to the aircraft emergency release signal terminal and the grounding terminal, and the two ends of the relay J2 are respectively connected to the aircraft normal release signal terminal and the grounding terminal. Before the normal or emergency release signal of the missile is connected, the P1-P2 contacts controlled by the relay J1 are normally closed, and the P3-P4 contacts controlled by the relay J2 are normally closed, so that the aircraft suspension signal can be normally output, indicating that the missile has been suspended at this time. When the normal or emergency release signal of the missile is connected, the P1-P2 contacts or the P3-P4 contacts are disconnected, indicating that the normal or emergency missile release is successful at this time. Similarly, the relays J3-J8 respectively control the on-off of the suspension signals of the missile hooks on the inner side of the left wing, the inner side of the right wing, and the outer side of the right wing. The circuit connection method is the same as that of the relays J1 and J2 on the outer pylon of the left wing of the aircraft, and will not be elaborated here. In addition, Figure 5 the suspension feedback signal of the missile hook in is a ground signal given to the missile hook suspension indicator light in the aircraft cockpit, while the missile hook suspension signal refers to the current state of the missile hook. The light on indicates that the missile hook has suspended the missile, and the light off indicates that the missile has not been suspended or has been launched. Of course, the model of the relay, the connection and control relationship between the contacts, and the specific connection method between the contacts and the pylon end signal are not limited to the solution of this embodiment, as long as it can be realized that when the normal or emergency release signal of the pylon missile is connected, the suspension signals of the missile hooks on the inner and outer sides of the left and right wings can be disconnected.

[0049] In this embodiment, as Figure 3 and Figure 6 shown, the control device in the function control module further includes a switch K1, and the switch K1 is connected in series with the contacts P1, P2, P3, and P4.

[0050] In this embodiment, the switch K1 has an automatic gear and a manual gear. When in the automatic gear, the switch K1 is closed, and when in the manual gear, the switch K1 is open. The switch K1 is used as a manual control circuit, and the tester can manually operate the switch K1 to be in the closed or open state to realize the manual control of the on-off of the suspension signal of the missile hook at the aircraft pylon end.

[0051] Specifically, please refer to Figure 3 and Figure 6 , the control switch includes 4 switches of JK-1, and its main function is to realize the manual and automatic control of the on-off of the suspension signals of the bomb hooks on the inner and outer sides 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 switch K1 is connected to contact point P4, and the other end is connected to the suspension signal terminal of the aircraft. And switch K1 has an automatic gear 1 and a manual gear 2. When placed in the automatic gear 1, switch K1 is in the closed state. At this time, the on-off of the corresponding contacts is controlled by relays J1 and J2 to realize the on-off of the suspension signal of the bomb hook on the pylon. When placed in the manual gear 2, switch K1 is disconnected, so as to realize the manual control of the disconnection of the suspension signal of the bomb hook on the pylon. Similarly, switches K2, K3 and K4 are respectively used for the manual and automatic control of the on-off of the suspension 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. The circuit connection mode is the same as that of switch K1 of the outer pylon of the left wing of the aircraft, and will not be elaborated here. The specific positions where switches K1, K2, K3 and K4 are set can also be between the contact points, as long as the on-off of the suspension signal of the bomb hook on the pylon can be realized.

[0052] In this embodiment, as Figure 3 and Figure 7 shown, the function indication module includes indicating parts D1, D2 and D3;

[0053] One end of indicating part D1 is connected to the power supply terminal of the aircraft, and the other end is connected to the suspension signal terminal of the aircraft to indicate the on-off of the suspension signal of the bomb hook at the pylon end of the aircraft;

[0054] One end of indicating part D2 is connected to the emergency release signal terminal of the aircraft, and the other end is connected to the ground terminal of the aircraft to indicate the on-off of the emergency release signal of the bomb hook at the pylon end of the aircraft;

[0055] One end of indicating part D3 is connected to the normal release signal terminal of the aircraft, and the other end is connected to the ground terminal of the aircraft to indicate the on-off of the normal release signal of the bomb hook at the pylon end of the aircraft.

[0056] In this embodiment, the indicating parts D1, D2 and D3 include but are not limited to signal lamps, light-emitting diodes LED, small incandescent bulbs, neon lamps, fluorescent lamps and organic light-emitting diodes OLED, as long as the on-off of the signal can be intuitively observed through the on and off.

[0057] Specifically, please refer to Figure 3 and Figure 7, the function indication module includes 12 ZSD-3 signal lights. Its main function is to, when the external store release system is powered on for inspection and the normal release and emergency release switches in the aircraft cockpit are turned on, determine whether the corresponding release is successful and whether the bomb rack suspension function is intact by the "lighting and extinguishing" of the signal lights. Among them, signal lights D1, D4, D7, and D10 are respectively connected in parallel between the power supply terminal and the suspension signal terminal at the ends of the inner and outer pylons on the left and right wings of the aircraft, used to indicate the on-off of the bomb rack suspension signal at the ends of the inner and outer pylons on the left and right wings of the aircraft; signal lights D2, D5, D8, and D11 are respectively connected in parallel between the emergency release signal terminal and the ground terminal at the ends of the inner and outer pylons on the left and right wings of the aircraft, used to indicate the on-off of the emergency release signal at the ends of the inner and outer pylons on the left and right wings of the aircraft; signal lights D3, D6, D9, and D12 are respectively connected in parallel between the normal release signal terminal and the ground terminal at the ends of the inner and outer pylons on the left and right wings of the aircraft, used to indicate the on-off of the normal release signal at the ends of the inner and outer pylons on the left and right wings of the aircraft. The relationship between the lighting and extinguishing of the signal lights and the functions of the aircraft external store release system is as follows:

[0058] Before the normal or emergency release signal of the missile is turned on, 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 bomb rack suspension signal lights D1, D4, D7, and D10 should be lit, indicating that the missile has been suspended well; by the lighting and extinguishing of the bomb rack suspension signal lights, it can be judged whether the bomb rack suspension function of the external store release system of each pylon is intact.

[0059] After the inner or outer emergency release signal of the missile is turned on, the energized P1-P2 or P3-P4 contacts of the relay are disconnected. At this time, the bomb rack suspension signal lights D1, D4, D7, and D10 go out, and the emergency release signal lights D5, D8 or D2, D11 should be lit, indicating that the emergency release is successful; by the lighting and extinguishing of the emergency release signal lights, it can be judged whether the working condition of the emergency release circuit of the external store release system of each pylon is intact.

[0060] After the normal release signal of the missile is turned on, the energized P1-P2 or P3-P4 contacts of the relay are disconnected. At this time, the bomb rack suspension signal lights D1, D4, D7, and D10 go out, and the normal release signal lights D3, D6, D9, and D12 should be lit, indicating that the normal release is successful; by the lighting and extinguishing of the normal release signal lights, it can be judged whether the working condition of the normal release circuit of the external store release system of each pylon is intact.

[0061] In this embodiment, the number of aircraft cross-linking interface modules, function control modules, and function indication modules is 4 groups each, 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 ends of the aircraft, so as to respectively realize the function detection of the external store release systems at the ends of the inner and outer pylons on the left and right wings of the aircraft. Its circuit structure is as Figure 3As shown, from left to right are the circuit diagrams corresponding to the external store release system detection equipment for the outer pylon of the left wing, the inner pylon of the left wing, the inner pylon of the right wing, and the outer pylon of the right wing. The specific structure of each part of the circuit and the connection relationship of the components have been given above and will not be elaborated here. In addition, the sockets, switches, relays, and signal lights in the aircraft external store release system detection equipment are connected to each other by wires. Its main function is to complete the transmission of the normal release signal, emergency release signal, power signal, ground signal, and suspension signal of the aircraft external store release system to complete the power-on inspection of the system function.

[0062] In this embodiment, as Figure 3 and Figure 8 shown, the aircraft external store release system detection equipment further includes a box body and a control panel. The box body houses and fixes the aircraft cross-link interface module, function control module, and function indication module. The function indication module and part of the function control module are exposed outside the control panel. Fixing points for facilitating the installation of sockets, switches, relays, and signal lights are provided on the box body and the control panel. Its main function is to integrate each module on the box body and the control panel and carry prompt information for power-on operation. The control panel is corroded from a 1mm-thick stainless steel plate. The equipment box body is composed of a portable metal box body with a snap-on lid and a simple and clear stainless steel panel, and various fixing points are designed to facilitate the firm fixing of each device and wire harness. The equipment cross-link interface module is designed in the form of a quick-release clamp and transmits single pins, facilitating the quick connection of the equipment to the aircraft.

[0063] The detection method and judgment criteria of the aircraft external store release system detection equipment in this embodiment are as follows: First, connect the aircraft external store release system detection equipment to the cross-link of the aircraft end through the cable of the cross-link interface module. According to the power-on inspection requirements, place the control switches K1-K4 in the initial position (when manually checking the working condition of the missile control circuit on a certain pylon, turn on the control switch of that pylon; when automatically checking the 4 pylons, turn all the control switches K1-K4 to the automatic gear position), place all the power switches in the cockpit in the "off" position, connect the 27V±2.7V DC ground power supply to the aircraft, and turn on the "battery ground power" switch on the aircraft. After the preparation work is completed, conduct cross-link tests according to the steps, test items, and operation control contents in Table 1, and record according to whether the test results meet the qualified criteria in Table 1.

[0064] Table 1 Cross-link test content of the aircraft external store release system detection equipment and the aircraft external store release system

[0065]

[0066] The above are only the preferred embodiments of the present utility model, and the protection scope of the present utility model is not limited to the above embodiments. All technical solutions falling within the concept of the present utility model belong to the protection scope of the present utility model. It should be noted that for those of ordinary skill in the art, several improvements and refinements made without departing from the principle of the present utility model should also be regarded as within the protection scope of the present utility model.

Claims

1. An inspection device for an aircraft external store release system, characterized in that, Comprising: An aircraft cross-link interface module, a function control module, and a function indication module; The aircraft cross-link interface module is connected to the aircraft pylon end to achieve signal transmission between the aircraft pylon end and the detection equipment of the aircraft external stores release system; The function control module is connected to the aircraft cross-link interface module, and controls the transmission of signals at the aircraft pylon end through a control device provided in the function control module; The function indication module is connected to the aircraft cross-link interface module and the function control module, and indicates whether the functions of the aircraft external stores release system are normal through an indicating device provided in the function indication module.

2. The detection equipment for an aircraft external stores release system according to claim 1, characterized in that: The aircraft cross-link interface module includes a plurality of internal sockets, a plurality of external plugs connected to the internal sockets, and a plurality of cross-link interface cables connecting the external plugs to the aircraft pylon end.

3. The detection equipment for an aircraft external stores release system according to claim 2, characterized in that: The number of the internal sockets, external plugs, and cross-link interface cables corresponds and is consistent. Each internal socket is correspondingly plugged with an external plug, and the external plug is respectively connected to the aircraft suspension signal end, power supply end, ground end, emergency release signal end, and normal release signal end through the cross-link interface cable.

4. The detection equipment for an aircraft external stores release system according to claim 1, characterized in that: The control devices in the function control module include a relay J1 and a relay J2; Both ends of the relay J1 are respectively connected to the aircraft emergency release signal end and the ground end through the aircraft cross-link interface module, and the relay J1 controls the opening and closing of the contact points P1 and P2; Both ends of the relay J2 are respectively connected to the aircraft normal release signal end and the ground end through the aircraft cross-link interface module; the relay J2 controls the opening and closing of the contact points P3 and P4; The contact points P1, P2, P3, and P4 are connected in series in sequence, and are connected in parallel between the ground end and the aircraft suspension signal end through the aircraft cross-link interface module; the contact points P1 and P2 controlled by the relay J1 and the contact points P3 and P4 controlled by the relay J2 are in a normally closed state.

5. The detection equipment for an aircraft external stores release system according to claim 4, characterized in that: The control devices in the function control module further include a switch K1, and the switch K1 is connected in series with the contact points P1, P2, P3, and P4.

6. The detection equipment for an aircraft external stores release system according to claim 5, characterized in that: The switch K1 has an automatic gear and a manual gear. When in the automatic gear, the switch K1 is closed, and when in the manual gear, the switch K1 is opened.

7. The detection equipment for an aircraft external stores release system according to claim 1, characterized in that: The function indication module includes indicating devices D1, D2, and D3; One end of the indicating device 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 hanging hook suspension signal at the aircraft pylon end; One end of the indicating device D2 is connected to the emergency release signal end of the aircraft, and the other end is connected to the ground end of the aircraft to indicate the on-off of the emergency release signal at the aircraft pylon end; One end of the indicating component D3 is connected to the normal release signal terminal of the aircraft, and the other end is connected to the grounding terminal of the aircraft to indicate the on / off of the normal release signal at the aircraft pylon end.

8. The aircraft external store release system detection device according to claim 7, characterized in that: The indicating components D1, D2, and D3 include, but are not limited to, signal lamps, light-emitting diodes (LEDs), small incandescent bulbs, neon lamps, fluorescent lamps, and organic light-emitting diodes (OLEDs).

9. The aircraft external stores release system detection device according to any one of claims 1-8, wherein: The numbers of the aircraft cross-linking interface module, the function control module, and the function indicating module are all 4 groups, which are respectively connected to the pylon ends on 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 of the aircraft.

10. The aircraft external stores release system detection device according to any one of claims 1-8, wherein: The aircraft external stores release system detection device further includes a box body and a control panel. The box body houses and fixes the aircraft cross-linking interface module, the function control module, and the function indicating module, and the function indicating module and part of the function control module are exposed outside the control panel.

Images