CN219876741U - Conductive structure between airborne equipment and machine body structure - Google Patents
Conductive structure between airborne equipment and machine body structure Download PDFInfo
- Publication number
- CN219876741U CN219876741U CN202320999466.1U CN202320999466U CN219876741U CN 219876741 U CN219876741 U CN 219876741U CN 202320999466 U CN202320999466 U CN 202320999466U CN 219876741 U CN219876741 U CN 219876741U
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- Prior art keywords
- guide strip
- airborne equipment
- machine body
- equipment
- flow guide
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- 239000002131 composite material Substances 0.000 claims abstract description 8
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- 229910000838 Al alloy Inorganic materials 0.000 claims description 7
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- 230000003068 static effect Effects 0.000 abstract description 19
- 238000000034 method Methods 0.000 abstract description 7
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- 229910052782 aluminium Inorganic materials 0.000 abstract description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 abstract description 3
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- XEEYBQQBJWHFJM-UHFFFAOYSA-N iron Substances [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- 229910052742 iron Inorganic materials 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 239000000956 alloy Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
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- 230000035945 sensitivity Effects 0.000 description 1
- 238000001179 sorption measurement Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Landscapes
- Elimination Of Static Electricity (AREA)
Abstract
The utility model belongs to the technical field of organism static protection, and particularly relates to a conductive structure between airborne equipment and an organism structure; the device comprises an airborne equipment support, a flow guide strip and a machine body metal structure, wherein one end of the flow guide strip is in a specific large plane and is used for being connected with the airborne equipment support, the other end of the flow guide strip is connected with the machine body metal structure, and two ends of the flow guide strip are both exposed structures. The conductive path is realized by paving an aluminum guide strip with a proper section size on a composite material platform, introducing current from a special surface-treated equipment support to the guide strip, and then draining the current to a surrounding metal machine body structure through rivets with special surface treatment. The method solves the problem that when bonding wires cannot be used for bonding, circuit conduction or poor electric conductivity cannot be achieved between airborne equipment and a machine body structure, has the electrochemical corrosion resistance, and has great reference significance on an electrostatic protection method of the airborne equipment, wherein the circuit conduction cannot be achieved through direct bonding of bolts or rivets.
Description
Technical Field
The utility model belongs to the technical field of machine body static electricity protection, and particularly relates to a conductive structure between airborne equipment and a machine body structure.
Background
The electrostatic environment of a helicopter mainly comprises three parts: electrostatic environment in flight, electrostatic environment in parking and maintenance operations, and electrostatic environment in refueling. In the flight of a helicopter, the surfaces of a helicopter body and the surfaces of a rotor wing collide with dust, water vapor and other substance particles in the air, electrons are transferred by continuous collision, a large amount of electrons are transferred to the helicopter body after being separated from proton binding, static electricity is generated, the helicopter body is not well overlapped, and the phenomenon that local potential difference is too large to break down electronic elements and even hurt personnel is caused; the temperature difference between the high-temperature gas generated by the engine component in flight and the outside is large, so that electrons are easy to separate to generate static electricity; electromagnetic waves generated in the use of various communication navigation equipment on the aircraft are easily electrostatically generated after being absorbed by the machine body material.
In the parking process of the aircraft apron, the helicopter receives frictional impact of wind, dust, raindrops and other substances in natural conditions, static charges are accumulated continuously, and particularly in northern areas where air is dry, the static charges are easier to generate; various detection repair instruments used in maintenance work generate static electricity in a considerable part of high-frequency electromagnetic waves generated when the detection repair instruments are electrified after the high-frequency electromagnetic waves are absorbed by metal of a machine body; when an electrostatic tool is used for on-board operation, the static electricity is transferred to charge the machine body.
In aircraft fueling, a large amount of charge is generated, after which the charge separates, creating a large amount of static charge on the surface of the flowing fuel, filter, etc. Fuel tends to carry separated charges far. If there is no conductive loop available, charge builds up on the metal surface, resulting in a very high potential energy source. With the continuous accumulation of charge, a sufficiently high point is created, and these voltages and their hazards, which are created in the aircraft fuel tank, will explode if the electric arc created at these voltages to the low potential is exactly combined with the fuel gas present. Static electricity can reduce on-board equipment reliability: the static electricity has an adsorption effect and can adsorb a large amount of dust and sundries in the air. The circuit of the airborne equipment is complex, the circuit board, the relay, the bus bar and the like are exposed to the outside more, and the accumulated static charge can accelerate the accumulation of dust and sundries on the equipment, so that the equipment is easy to short-circuit, the performance is reduced, and the equipment is aged rapidly. Static electricity is accumulated to a certain degree to form a larger potential difference, so that electronic components can be broken down, equipment is directly damaged, and heat energy generated in a discharging process can influence the electronic components, so that the reliability of the equipment is reduced. The electrostatic discharge can generate a large amount of electromagnetic noise, and the electromagnetic noise is used as an electromagnetic interference source and can seriously influence the operation of the communication navigation system.
Static electricity is the most harmful to electronic components compared to other effects, and may cause permanent rejection of electronic components. With the development of technology, the integration level of electronic elements of helicopter-mounted equipment is higher and higher, and the sensitivity to static electricity is also higher and higher. The integration level of the electronic component is usually represented by small circuit area, low withstand voltage and poor resistance to electrostatic discharge, so that electrostatic protection measures are required to be made in the use, maintenance and parking of the helicopter, and damage to the helicopter caused by static electricity is avoided, and flight safety is influenced.
Disclosure of Invention
The purpose of the utility model is that: the utility model provides a conductive path between an onboard device arranged on a composite material platform and a metal structure of a machine body, wherein the conductive path is realized by paving an aluminum guide strip with a proper section size on the composite material platform, introducing current from a device bracket subjected to special surface treatment into the guide strip subjected to special surface treatment, and then guiding the current to the surrounding metal machine body structure through rivets subjected to special surface treatment. The method solves the problem that when bonding wires cannot be used for bonding, circuit conduction or poor electric conductivity cannot be achieved between airborne equipment and a machine body structure, has the electrochemical corrosion resistance, and has great reference significance on an electrostatic protection method of the airborne equipment, wherein the circuit conduction cannot be achieved through direct bonding of bolts or rivets.
The technical scheme of the utility model is as follows: the conductive structure between the airborne equipment and the engine body structure comprises an airborne equipment support, a guide strip and an engine body metal structure, wherein one end of the guide strip is a specific large plane and is used for connecting the airborne equipment support, the other end of the guide strip is connected with the engine body metal structure, and both ends of the guide strip are exposed structures.
Furthermore, the support material of the airborne equipment is aluminum alloy, and the surface of the support material is sprayed with primer after being oxidized by allotin, wherein the primer is not sprayed at the connection area of the contact surface of the support of the airborne equipment and the guide strip.
Furthermore, the guide strip is made of aluminum alloy, and the surface of the connecting part at the two ends is sprayed with primer after being oxidized by alotin.
Further, the plane of the guide strip connected with one end of the airborne equipment support is not smaller than the outline of the equipment support.
Furthermore, the guide strips are connected with the machine body metal structure through rivets.
Furthermore, the middle part of the guide strip is adhered to the surface of the composite material mounting platform through structural adhesive.
The utility model has the beneficial effects that: 1) The electric conduction efficiency is high: the current conduction path is simple, direct, safe and effective, and the impedance is low;
2) The application range is wide: the method can be used for conducting a circuit between any on-board equipment mounted on the composite platform and the machine body structure;
3) The reliability is high: the conductive path has the environment corrosion resistance and the electrochemical corrosion resistance;
4) The installation is simple, and the maintenance is convenient: the guide strip and the platform are fixed in a cementing and riveting mode, the equipment frame is fixed in a screwed connection mode with the platform and the guide strip, the current conducting circuit is simple to install, and equipment maintenance is convenient.
Drawings
FIG. 1 is a schematic diagram of a circuit conducting structure according to the present utility model;
FIG. 2 is a schematic diagram of a deflector strip design;
wherein, 1-combined material mounting platform, 2-machine carries equipment support, 3-organism metal construction, 4-water conservancy diversion strip, 5-rivet.
Detailed Description
The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
For on-board equipment, one of the common protective measures against static electricity is grounding and grounding. The control of a plurality of important system devices on the helicopter and the display of alarm signals are realized through the grounding control negative line end, and the grounding is used for connecting all metal devices on the helicopter with the machine body through a lead, so that static charges can move freely, flow to the ground through the grounding wire, the potential between each device and the machine body of the helicopter is balanced, and the damage of the devices caused by static discharge is effectively avoided. Four types of helicopter grounding are adopted: firstly, bonding is directly formed by bolts, and a bolt fixing piece of the airborne equipment has good conductivity with the equipment and the machine body; secondly, the machine is carried out in a mode of externally connecting an iron bonding wire, and the machine-mounted equipment adopting the iron bonding wire is usually in direct contact with the machine body or has relative mobility; thirdly, riveting bonding by adopting non-anodized rivets, such as non-detachable elements of tail beams, tail inclined beams and the like; fourthly, special clamp bonding is adopted, and the clamp is generally in the form of a metal gasket or a metal strip.
Referring to fig. 1, the conductive path specifically designed in the utility model is shown in fig. 1, and consists of an airborne equipment bracket 2, a guide strip 4, rivets 5 and a machine body metal structure 3; the specific great plane of water conservancy diversion strip 4 one end for connect airborne equipment support 2, the organism metal structure 3 is connected to the other end, water conservancy diversion strip 4 both ends are naked structure, and accessible rivet 5 is connected with organism metal structure 3 and is realized fixing. The current generated by the equipment flows into the connecting area on the guide strip 4 through the airborne equipment bracket 2, flows to the metal structure 3 of the machine body through the guide strip 4 and the rivet 5, and finally flows to the rear part of the machine body along the machine body structure.
In a specific design, the material of the airborne equipment support 2 is aluminum alloy, and the surface of the airborne equipment support is sprayed with primer after being oxidized by allotin, wherein the primer is not sprayed in the range of a shadow area phi 12mm on the contact surface of the equipment support 2 and the guide strip 4; the material of the guide strip 4 is aluminum alloy, and the surface is sprayed with primer after being oxidized by allotin, wherein the primer is not sprayed in the shadow area of phi 12mm on the contact surface of the guide strip 4 and the equipment bracket 2; the thickness of the guide strip 4 is 0.4mm, in order to ensure the flatness of the mounting surface, the outline size of the contact surface is slightly larger than the outline size of the equipment bracket 2, the length of an extension area of the guide strip 4 is 30mm, the tail end size is ensured to be enough for riveting 2 rivets, and because the guide strip is only used as a functional piece and not a force transmission piece, the edge distance of the rivet is not required to ensure that L is more than or equal to (2 x the diameter of the rivet plus 1) mm, and a proper size value is selected according to the peripheral structure size; the guide strips 4 are adhered to the surface of the mounting platform 1 through structural adhesive; of course, the material of the guide strip can be changed into other metal materials with potential difference similar to that of the support material of the airborne equipment, and the cross-sectional area is converted according to the equivalent resistance. Selecting a rivet 5 at the tail end of the guide strip 4 for lap joint treatment: the airborne equipment support 2 is in threaded connection with the composite material mounting platform 1, and a phi 12mm shadow area on the airborne equipment support 2 is in direct contact with a phi 12mm shadow area on the guide strip 4 at the moment, so that a current path is formed.
By adopting the conductive path structure designed by the utility model, the connection of the conductive path is realized by using the airborne equipment bracket, the aluminum guide strip and the rivet, so that the problem of forming a low-impedance path between airborne equipment and a machine body structure is solved; the air guide strip is made of the same aluminum alloy material as the airborne equipment bracket, so that the problem of electrochemical corrosion in the direct contact area of the air guide strip and the airborne equipment bracket is avoided; the surface of each part in the conducting circuit selects proper surface protection measures, and the structure has the environment corrosion resistance; the problem that the bonding wires are inconvenient to use when the mounting position of the airborne equipment is far away from the metal structure of the machine body is solved; the conducting circuit solves the problem that when the airborne equipment is installed on the composite material platform, the fastening piece cannot be utilized for bonding or the electric conductivity is poor; the current conduction path is simple, direct, safe and effective, has low impedance and does not influence the normal operation of the airborne equipment.
The foregoing is merely a detailed description of the utility model, which is not a matter of routine skill in the art. However, the scope of the present utility model is not limited thereto, and any changes or substitutions that can be easily contemplated by those skilled in the art within the scope of the present utility model should be included in the scope of the present utility model. The protection scope of the present utility model shall be subject to the protection scope of the claims.
Claims (6)
1. The electric conduction structure between the airborne equipment and the engine body structure is characterized in that the electric conduction structure comprises an airborne equipment support, a flow guide strip and an engine body metal structure, wherein one end of the flow guide strip is in a specific large plane and is used for connecting the airborne equipment support, the other end of the flow guide strip is connected with the engine body metal structure, and two ends of the flow guide strip are exposed structures.
2. The electrically conductive structure between the on-board equipment and the body structure according to claim 1, wherein the support material of the on-board equipment is aluminum alloy, the surface is sprayed with primer after being oxidized by allotin, and the contact surface connection area of the support of the on-board equipment and the guide strip is not sprayed with primer.
3. The conductive structure between the on-board equipment and the machine body structure according to claim 1, wherein the material of the guide strip is aluminum alloy, and the surface of the connecting parts except for the two ends is sprayed with primer after being oxidized by alotin.
4. A conductive structure between an on-board device and a body structure as claimed in claim 3, wherein the plane of the guide strip connected to one end of the on-board device support is not smaller than the outline of the device support.
5. The electrically conductive structure between an on-board device and a body structure of claim 4, wherein the deflector strip is connected to the body metal structure by rivets.
6. The conductive structure between the on-board device and the airframe structure of claim 1 wherein the middle part of the air guide strip is adhered to the surface of the composite material mounting platform through structural adhesive.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320999466.1U CN219876741U (en) | 2023-04-27 | 2023-04-27 | Conductive structure between airborne equipment and machine body structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320999466.1U CN219876741U (en) | 2023-04-27 | 2023-04-27 | Conductive structure between airborne equipment and machine body structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219876741U true CN219876741U (en) | 2023-10-20 |
Family
ID=88344141
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202320999466.1U Active CN219876741U (en) | 2023-04-27 | 2023-04-27 | Conductive structure between airborne equipment and machine body structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219876741U (en) |
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2023
- 2023-04-27 CN CN202320999466.1U patent/CN219876741U/en active Active
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