A s76d engine ignition test tool

Abstract

This utility model relates to the field of engine testing technology, and in particular to an S76D engine ignition testing tool, including a testing mechanism for engine ignition testing. The testing mechanism includes: a main body component, including an aviation plug that inserts into a helicopter-specific ignition test connector; a plurality of circumferentially distributed elastic clamping teeth fixed at the rear end of the aviation plug; a rubber sleeve disposed between the plurality of circumferentially distributed elastic clamping teeth; a knob sleeve threadedly installed at the rear end of the aviation plug; and a tapered inclined surface formed on the inner wall of the knob sleeve; a control component disposed on the main body component for switch control; and a protective component disposed on the main body component for protecting the pins on the aviation plug; it connects to the helicopter ignition system through a standard interface, employs a progressive clamping mechanism to ensure reliable connection, integrates a control circuit to achieve one-button trigger testing, and is equipped with an automatic locking and sealing protection structure, combining ease of operation and environmental adaptability.

Description

Technical Field

[0001] This utility model relates to the field of engine testing technology, specifically to an S76D engine ignition testing tool. Background Technology

[0002] The S76D helicopter, a widely used twin-engine medium helicopter in modern aviation, requires regular functional testing of its engine ignition system to ensure flight safety. This helicopter employs an advanced electronic ignition system, generating an ignition spark through a high-voltage transformer assembly. Its dedicated test interface design conforms to aviation industry standards, providing ground maintenance personnel with a convenient access point for testing. Engine ignition testing is a crucial part of routine helicopter maintenance, directly impacting flight safety and engine performance evaluation.

[0003] According to CN119334648B, an ignition testing device with switchable engine models is disclosed. This technology discloses a technical solution including "a side plate and an ignition testing machine, one side plate being fixedly connected to the ignition testing machine, two side plates being provided, and fixing rings being fixedly connected to the sides of the two side plates that are close to each other by bolts. Four fixing seats are fixedly connected to the sides of the two fixing rings that are close to each other, and a transmission ring is fixedly connected to the fixing seats." It has the technical effect of "supporting the movement of the base by the effect of the stabilizing wheel rolling in the stabilizing groove, preventing the engine from being unstable after being placed on the fixing pin, achieving the purpose of safely transferring the engine to the vicinity of the ignition testing machine, avoiding the situation where the engine is easily dropped due to the engine tilting when turning when using a trolley to transfer the engine, reducing the danger of manually transferring the engine by trolley, and also reducing unnecessary maintenance costs caused by the engine being dropped."

[0004] The existing S76D helicopter engine ignition test tool has significant shortcomings in terms of connection reliability. Its traditional plug structure is prone to loosening in the high vibration environment of the helicopter engine nacelle, resulting in unstable signal transmission during the test. At the same time, it lacks an effective cable fixing mechanism, which can easily cause fatigue fracture of the internal wires of the connector after frequent plugging and unplugging operations. Utility Model Content

[0005] To address the shortcomings of existing technologies, this utility model provides an S76D engine ignition test tool that connects to the helicopter ignition system via a standard interface, employs a progressive clamping mechanism to ensure reliable connection, integrates a control loop to achieve one-button trigger testing, and is equipped with an automatic locking and sealing protection structure, combining ease of operation with environmental adaptability.

[0006] To achieve the above objectives, this utility model provides the following technical solution: an S76D engine ignition test tool, comprising a test mechanism and used for engine ignition testing, the test mechanism comprising:

[0007] The main components include an aviation plug that is inserted into a helicopter-specific ignition test connector. The rear end of the aviation plug is fixed with several circumferentially distributed elastic teeth. A rubber sleeve is provided between the several circumferentially distributed elastic teeth. A knob sleeve is threaded onto the rear end of the aviation plug. A tapered bevel is provided on the inner wall of the knob sleeve.

[0008] A control component, mounted on the main component and used for switch control;

[0009] A protective component is mounted on the main body and is used to protect the pins on the aviation connector.

[0010] Preferably, the control component includes a wire harness electrically connected to the rear end of the aviation plug, and the other end of the wire harness is electrically connected to a momentary switch, forming a complete ignition test control loop.

[0011] Preferably, the main component also includes a button that is rotatably mounted on the outer wall of the aviation plug via a shaft. A clip is fixed at the bottom of the front end of the button, and the clip engages with a slot on the helicopter-specific ignition test connector. A torsion spring is sleeved on the outside of the shaft.

[0012] Preferably, the protective component includes a flexible connecting strip fixed to the outer wall of the aviation plug, and a protective cover is fixed to the lower end of the flexible connecting strip.

[0013] Preferably, the protective component further includes a rubber plug fixed inside the protective cover, which forms an interference fit sealing structure with the pin end face of the aviation plug when the protective cover is closed.

[0014] Preferably, the protective assembly further includes a buckle fixed to the outer wall of the protective cover and used to extend to form a force-applying part.

[0015] Beneficial effects

[0016] This invention provides an ignition testing tool for an S76D engine. Compared with the prior art, it has the following advantages:

[0017] 1. The knob sleeve is connected to the rear end of the aviation plug through a precision thread. The tapered bevel on its inner wall and the elastic clamping teeth form a progressive clamping structure, which realizes the firm fixation and stress relief of the cable. It can withstand the strong vibration of the helicopter engine compartment and prevent the connection from loosening due to long-term use.

[0018] 2. When the operator presses the momentary switch, a signal is transmitted to the aviation plug through the wiring harness, triggering the ignition logic of the engine high-voltage pack, forming a complete ignition test control loop, and achieving the test objective. Attached Figure Description

[0019] Figure 1 This is a three-dimensional structural diagram of the present invention;

[0020] Figure 2 This is a schematic diagram of the protective component in this utility model;

[0021] Figure 3 This is a cross-sectional view of the main components of this utility model;

[0022] Figure 4 This is an exploded view of the main components of this utility model.

[0023] In the diagram: 1. Testing mechanism; 11. Main component; 111. Aviation connector; 112. Elastic clamping teeth; 113. Rubber sleeve; 114. Knob sleeve; 115. Conical bevel; 116. Shaft; 117. Button; 118. Clip; 119. Torsion spring; 12. Control component; 121. Wire harness; 122. Instantaneous switch; 13. Protective component; 131. Flexible connecting strip; 132. Protective cover; 133. Rubber plug; 134. Buckle. Detailed Implementation

[0024] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0025] Please see Figure 1 - Figure 4 This utility model provides a technical solution: an S76D engine ignition test tool, including a test mechanism 1 and used for engine ignition testing, the test mechanism 1 including:

[0026] The main component 11 includes an aviation plug 111 that is inserted into a helicopter-specific ignition test connector. The rear end of the aviation plug 111 is fixed with a number of circumferentially distributed elastic teeth 112. A rubber sleeve 113 is provided between the number of circumferentially distributed elastic teeth 112. A knob sleeve 114 is threadedly installed on the rear end of the aviation plug 111. A tapered inclined surface 115 is provided on the inner wall of the knob sleeve 114.

[0027] Control component 12 is disposed on main component 11 and used for switch control;

[0028] The protective component 13 is disposed on the main body component 11 and is used to protect the pins on the aviation plug 111.

[0029] In this embodiment, the knob sleeve 114 is connected to the rear end of the aviation plug 111 through a precision thread, and the tapered inclined surface 115 on its inner wall forms a progressive clamping structure with the elastic clamping teeth 112; thus, the cable is firmly fixed and stress is eliminated, which can withstand the strong vibration of the helicopter engine compartment and prevent the connection from loosening due to long-term use.

[0030] Specifically, the control component 12 includes a wire harness 121 electrically connected to the rear end of the aviation plug 111, and the other end of the wire harness 121 is electrically connected to a momentary switch 122, forming a complete ignition test control loop.

[0031] In this embodiment, when the operator presses the momentary switch 122, a signal is transmitted to the aviation plug 111 through the wire harness 121, triggering the ignition logic of the engine high-voltage pack, forming a complete ignition test control loop, and achieving the test objective.

[0032] Specifically, the main component 11 also includes a button 117 rotatably mounted on the outer wall of the aviation plug 111 via a shaft 116. A clip 118 is fixed at the bottom front end of the button 117, and the clip 118 mates with a slot on the helicopter-specific ignition test connector. A torsion spring 119 is sleeved on the outside of the shaft 116.

[0033] In this embodiment, before the aviation plug 111 is inserted, the operator presses button 117 to make the locking head 118 tilt up to avoid it. After the aviation plug 111 is inserted into place, the button 117 is released. At this time, the reset torque generated by the torsion spring 119 sleeved on the shaft 116 pushes the button 117 to rotate, causing the locking head 118 to automatically lock into the corresponding slot of the helicopter special ignition test connector, thereby achieving locking.

[0034] Specifically, the protective component 13 includes a flexible connecting strip 131 fixed to the outer wall of the aviation plug 111, and a protective cover 132 is fixed to the lower end of the flexible connecting strip 131.

[0035] In this embodiment, the flexibility of the flexible connecting strip 131 allows the protective cover 132 to hang down naturally when opened, which not only effectively prevents the protective cover 132 from being lost, but also avoids collisions with other components by limiting the range of motion of the protective cover 132.

[0036] Specifically, the protective component 13 also includes a rubber plug 133 fixed inside the protective cover 132, which forms an interference fit sealing structure with the pin end face of the aviation plug 111 when the protective cover 132 is closed.

[0037] In this embodiment, when the protective cover 132 is closed, the rubber plug 133 forms an all-around interference fit sealing structure with the end face of the pin through elastic deformation, which isolates the pin from external dust, oil and moisture.

[0038] Specifically, the protective component 13 also includes a buckle 134 fixed to the outer wall of the protective cover 132 and used to extend to form a force-applying part.

[0039] In this embodiment, when it is necessary to open the protective cover 132, the operator can use his / her fingers to press the force application part of the buckle 134 to separate the protective cover 132 from the aviation plug 111.

[0040] The working principle and usage process of this utility model are as follows: First, the knob sleeve 114 is connected to the rear end of the aviation plug 111 through a precision thread. The tapered inclined surface 115 on its inner wall and the elastic clamping teeth 112 form a progressive clamping structure, which realizes the firm fixation and stress relief of the cable. It can withstand the strong vibration of the helicopter engine compartment and prevent the connection from loosening due to long-term use.

[0041] Before the aviation plug 111 is inserted, the operator presses button 117 to make the clamp head 118 tilt up to avoid it. After the aviation plug 111 is inserted into place, the button 117 is released. At this time, the reset torque generated by the torsion spring 119 sleeved on the shaft 116 pushes the button 117 to rotate, which drives the clamp head 118 to automatically snap into the corresponding slot of the helicopter special ignition test connector, thus achieving locking.

[0042] Finally, the operator presses the momentary switch 122, which transmits a signal to the aviation plug 111 through the wiring harness 121, triggering the ignition logic of the engine high-voltage pack, forming a complete ignition test control loop, and achieving the test objective.

[0043] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0044] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. An S76D engine ignition test tool characterized by: The test apparatus (1) includes a testing unit (1) and is used for engine ignition testing. The testing unit (1) includes: The main component (11) includes an aviation plug (111) that is inserted into a helicopter-specific ignition test connector. The rear end of the aviation plug (111) is fixed with several circumferentially distributed elastic teeth (112). A rubber sleeve (113) is provided between the several circumferentially distributed elastic teeth (112). A knob sleeve (114) is threaded onto the rear end of the aviation plug (111). A tapered inclined surface (115) is provided on the inner wall of the knob sleeve (114). A control component (12) is disposed on the main component (11) and used for switch control; A protective component (13) is disposed on the main body component (11) and is used to protect the pins on the aviation plug (111).

2. The S76D engine ignition test tool according to claim 1, characterized in that: The control component (12) includes a wire harness (121) electrically connected to the rear end of the aviation plug (111), and the other end of the wire harness (121) is electrically connected to a momentary switch (122), forming a complete ignition test control loop.

3. The S76D engine ignition test tool according to claim 1, characterized in that: The main component (11) also includes a button (117) that is rotatably mounted on the outer wall of the aviation plug (111) via a shaft (116). A clip (118) is fixed at the bottom front end of the button (117), and the clip (118) cooperates with the slot on the helicopter-specific ignition test connector. A torsion spring (119) is sleeved on the outside of the shaft (116).

4. The S76D engine ignition test tool according to claim 1, characterized in that: The protective component (13) includes a flexible connecting strip (131) fixed to the outer wall of the aviation plug (111), and a protective cover (132) is fixed to the lower end of the flexible connecting strip (131).

5. The S76D engine ignition test tool according to claim 4, characterized in that: The protective component (13) also includes a rubber plug (133) fixed inside the protective cover (132), which forms an interference fit sealing structure with the pin end face of the aviation plug (111) when the protective cover (132) is closed.

6. The S76D engine ignition test tool according to claim 4, characterized in that: The protective component (13) also includes a buckle (134) fixed to the outer wall of the protective cover (132) and used to extend to form a force-applying part.

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