Auxiliary tooling for narrow space in ground joint test of aircraft standard interface with live ammunition

Abstract

The utility model provides an auxiliary tool for narrow space of airplane standard interface real bullet ground joint test belongs to the technical field of detecting missile, including support frame, it is the shape structure card in the suspension bracket side, namely the support plate of forming the corner end in two sides, two support plates are parallel to each other, threaded hole, it is vertically through setting on one of support plates, threaded rod, it is in threaded hole cooperation rotation is equipped, when threaded rod moves up and down, can touch the spring pin on the suspension bracket and resist into the suspension bracket, the utility model discloses can clamp the tool in the narrow space on the suspension bracket, thereby can press the spring pin into the suspension bracket, further can realize the detection after the need not to transport the missile to the suspension point area and hang.

Description

Technical Field

[0001] This utility model relates to the field of missile testing equipment technology, specifically to auxiliary tooling for live-fire ground testing of aircraft standard interfaces in confined spaces. Background Technology

[0002] In the field of live-fire ground testing and fault detection of air-to-ground weapon systems, traditional operating methods present significant technical bottlenecks. When conducting missile inspection, chain inspection, alignment, and telemetry signal detection, a crane is required to transfer the weapon from the ammunition transport vehicle to the missile loading vehicle, and then to the mounting point for loading. This process involves multiple manual operations, which is not only time-consuming and labor-intensive (each transfer takes 2-3 hours), but also poses safety hazards such as missile slippage and mechanical collisions, directly threatening the safety of ground personnel and equipment.

[0003] First, the two ends of the test cable must be connected to the mounting bracket interface and the missile test port respectively. Then, the release safety pin on the missile needs to be pressed into the housing using tooling to simulate the onboard state after the weapon is powered on.

[0004] Secondly, the signal interaction mechanism between the weapon and its pylon and bomb rack relies on the presence of a signal push rod mechanism and a disengagement signal assembly. The former identifies the status of the suspended object on the pylon through a micro-switch assembly (reporting the presence of the suspended object when the push rod is compressed and the micro-switch is activated). The latter compresses the micro-switch during weapon mounting to simulate the weapon's on-board status and ensures safe ground power supply. After launch, it resets by disengaging the safety pin push rod to establish a zero point for flight control timing. However, existing technologies lack the necessary tooling to achieve this. Utility Model Content

[0005] In view of this, the present invention provides an auxiliary tooling for the narrow space of the aircraft standard interface live-fire ground test. The present invention can place the tooling in the narrow space of the rack, so that the spring pin can be pressed into the rack, thereby realizing the test without transporting the missile to the mounting point area for post-mounting testing.

[0006] To solve the above-mentioned technical problems, this utility model provides an auxiliary tooling for the narrow space of the live-fire ground test of the aircraft standard interface, including a support frame, which is a U-shaped structure that is clamped on the side of the hanger, that is, the two sides form a corner support plate, the two support plates are parallel to each other, and one of the support plates can be attached to the top or bottom of the hanger.

[0007] A threaded hole is vertically installed through one of the support plates, and the threaded hole and the spring pin are located on the same axis.

[0008] The threaded rod is rotatably mounted in the threaded hole. The threaded rod can slide up and down when it rotates in the threaded hole. When the threaded rod moves up and down, it can abut the spring pin on the bracket into the bracket.

[0009] The threaded rod has an abutment block at one end near the bracket. The abutment block has a horizontal planar structure at one end near the bracket. The threaded rod can drive the abutment block to abut against the spring pin.

[0010] The contact block has a circular plate-like structure.

[0011] The end of the threaded rod away from the contact block is also equipped with a force-applying component, which facilitates the application of force to the threaded rod.

[0012] The force-applying component has a Y-shaped structure, and the bottom cross-section of the force-applying component is larger than the cross-section of the threaded rod, so that the threaded rod will not fall out of the threaded hole during the up-and-down sliding process.

[0013] In summary, compared with the prior art, this application includes at least one of the following beneficial technical effects:

[0014] 1. Breakthrough in non-mounted inspection technology: Through the U-shaped snap-fit ​​structure of the support frame and the precise pressure design of the threaded rod, the spring pin can be pressed into the rack without transporting the missile to the mounting point area for post-mounting inspection. This achieves the missile's power-off state conversion, solving the efficiency bottleneck of traditional technology that requires disassembling the missile for inspection. The single inspection time is shortened from 2-3 hours to minutes, while avoiding potential damage to the missile structure during the disassembly process.

[0015] 2. Optimized adaptability to narrow spaces: The tooling adopts a compact design. The parallel structure of the double support plates of the support frame can be stably snapped into the narrow area on the side of the hanger. The axial layout of the threaded rod and the contact block ensures that the operating space is minimized, making it particularly suitable for working environments with complex mechanical structure restrictions near aircraft hangers.

[0016] 3. Significantly reduced safety risks: By replacing manual operation with mechanical top rods, the risks of human error such as projectile slippage and mechanical collisions are eliminated. At the same time, the problem of poor contact caused by repeated plugging and unplugging of detection cables during the installation and disassembly process is avoided, ensuring the safety of personnel and equipment on the ground.

[0017] 4. Improved ease of operation and reliability: The Y-shaped force-applying component combined with the threaded transmission mechanism forms a force-saving lever system. Operators only need to rotate the force-applying component to achieve precise displacement control of the threaded rod. The circular plate-shaped planar structure of the contact block ensures uniform contact with the end face of the spring pin, avoiding component deformation caused by local stress concentration. The pressure of the push rod is controllable and repeatable.

[0018] 5. Signal interaction mechanism compatibility: The tooling design takes into account the functional requirements of the hanger signal push rod mechanism and the disengagement signal component. While pressing in the spring pin to cut off the power, it maintains the mechanical stability of the micro switch component, ensuring the normal reporting of the hanger suspension status signal and the accurate formation of the flight control timing zero point. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the auxiliary tooling for the aircraft standard interface live-fire ground test in a narrow space according to the present invention.

[0020] Figure 2 This is a structural diagram of the present invention in use.

[0021] Explanation of reference numerals in the attached figures:

[0022] 1. Hanger; 2. Spring pin; 3. Support frame; 4. Threaded hole; 5. Threaded rod; 6. Abutment block; 7. Force-applying component. Detailed Implementation

[0023] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the following will be described in conjunction with the accompanying drawings of the embodiments of this utility model. Figure 1-2 The technical solutions of the embodiments of this utility model are clearly and completely described herein. Obviously, the described embodiments are only some, not all, of the embodiments of this utility model. All other embodiments obtained by those skilled in the art based on the described embodiments of this utility model are within the protection scope of this utility model.

[0024] This embodiment provides an auxiliary tooling for live-fire ground testing of aircraft standard interfaces in confined spaces, such as... Figure 1-2 As shown: This application is mainly used in the use of a pylon 1 in the missile bay. The pylon 1 is used to mount missiles. The top of the pylon 1 has a retractable spring pin 2. The auxiliary tooling includes a U-shaped support frame 3 with two corner ends forming support plates on the support frame 3. The two support plates are parallel to each other. The support frame 3 can be snapped onto the side of the pylon 1. One support plate is attached to the bottom of the pylon 1, and the other support plate is located directly above the spring pin 2. A threaded hole 4 is provided through the support plate located directly above the spring pin 2. A threaded rod 5 is provided in the threaded hole 4. The threaded rod 5 can rotate in the threaded hole 4. The rotation of the threaded rod 5 allows it to move up and down in the threaded hole 4. When the threaded rod 5 moves towards the pylon 1, it can contact the spring pin 2, thereby pushing the spring pin 2 into the pylon 1. The threaded rod 5 also abuts against the top of the pylon 1. One of the support plates is attached to the bottom of the pylon 1, and the tooling is fixed on the pylon 1.

[0025] Furthermore, an abutment block 6 is provided at one end of the threaded rod 5 near the bracket 1. The abutment block 6 is a circular plate structure, which means that when the threaded rod 5 moves up and down, it can drive the abutment block 6 to move up and down, so that the abutment block 6 can abut against the spring pin 2. Even when the tooling installation position is slightly tilted, the abutment block 6 can still abut against the threaded rod 5, thereby indirectly increasing the efficiency of missile detection.

[0026] Preferably, the end of the threaded rod 5 away from the contact block 6 is also provided with a force-applying element 7. The force-applying element 7 can facilitate the rotation of the threaded rod 5, thereby improving the efficiency of missile detection. Specifically, the force-applying element 7 has a Y-shaped structure, and the bottom cross section of the force-applying element 7 is larger than the cross section of the threaded rod 5. That is, the force-applying element 7 can not only facilitate the rotation of the threaded rod 5, but also prevent the threaded rod 5 from falling out of the threaded hole 4 during the rotation process. At the same time, the force-applying element 7 can also be set as other structures that facilitate the rotation of the threaded rod 5.

[0027] Furthermore, it should be noted that, in the description of this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0028] The above description is the preferred embodiment of this utility model. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of this utility model, and these improvements and modifications should also be considered within the protection scope of this utility model.

Claims

1. An auxiliary tooling for live-fire ground testing of aircraft standard interfaces in confined spaces, characterized by: include; The support frame (3) is a U-shaped structure that is placed on the side of the hanging frame (1), that is, the two sides form a corner support plate, and the two support plates are parallel to each other; A threaded hole (4) is vertically through one of the support plates; The threaded rod (5) is rotatably located in the threaded hole (4). When the threaded rod (5) moves up and down, it can abut the spring pin (2) on the bracket (1) into the bracket (1).

2. The auxiliary tooling for live-fire ground testing of aircraft standard interfaces in confined spaces as described in claim 1, characterized in that: The threaded rod (5) is provided with an abutment block (6) at one end near the bracket (1), and the abutment block (6) at one end near the bracket (1) has a horizontal planar structure.

3. The auxiliary tooling for live-fire ground testing of aircraft standard interfaces in confined spaces as described in claim 2, characterized in that: The contact block (6) has a circular plate-like structure.

4. The auxiliary tooling for live-fire ground testing of aircraft standard interfaces in confined spaces as described in claim 2, characterized in that: The threaded rod (5) is also provided with a force-applying element (7) at the end away from the contact block (6).

5. The auxiliary tooling for live-fire ground testing of aircraft standard interfaces in confined spaces as described in claim 4, characterized in that: The force-applying component (7) has a Y-shaped structure, and the bottom cross section of the force-applying component (7) is larger than the cross section of the threaded rod (5).

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