A rotorcraft-borne electronic jamming load structure

Abstract

The present invention relates to an electronic jamming load structure carried by a rotorcraft, which optimizes the layout of its internal modules and antennas. The module is installed horizontally on the upper part of the load, and the jamming flat spiral antenna is located in a spherical antenna cover at the lower part of the load. The spiral antenna is installed in an axially symmetrical manner and at a downward tilt angle in the antenna cover to meet the airspace coverage requirements of the jamming equipment. At the same time, a blank area is left in the airspace directly below the antenna to protect the ground command station from interference. The aperture size of the jamming spiral antenna is increased to the maximum extent within the limited space of the spherical antenna cover to meet the gain requirements. The module is installed on a heat sink plate, and the heat sink plate and the heat dissipation fins are connected by a heat pipe. The heat dissipation fins are symmetrically distributed and a fan is installed. The inlet wind direction and the outlet wind direction of the jet fan meet the horizontal symmetrical distribution, which minimizes the influence of the fan's wind output on the stability of the rotorcraft.

Description

Technical Field

[0001] The present invention belongs to the field of electronic jamming technology, and relates to the fields of mechanics, mechanics and heat transfer technology, and is particularly concerned with a rotorcraft-mounted electronic jamming load structure. Background Art

[0002] Electronic jamming equipment can be carried on platforms such as fixed stations, vehicles, aircraft, and missiles. Fixed-station and vehicle-mounted electronic jamming equipment is less constrained by size and weight, and most are large, multifunctional devices designed to counter a wide range of targets. Airborne and missile-mounted jamming equipment, constrained by size, weight, and environmental conditions, is often specialized for countering a specific target type, and its radiated power is also limited. Airborne jamming equipment can be carried on platforms such as fighter jets, helicopters, fixed-wing drones, and rotary-wing drones. Missile-mounted platforms include cruise missiles and artillery shells. Different platforms have different payload requirements and targets to counter. Summary of the Invention

[0003] Technical problems to be solved

[0004] To overcome the shortcomings of the prior art, the present invention provides a rotorcraft-mounted electronic jamming payload structure. This electronic jamming payload is designed using the rotorcraft as a carrier platform, and its countermeasure target is ground-based radar equipment. The payload's structural design is based on the rotorcraft's platform characteristics and the characteristics of the countermeasure target.

[0005] Technical Solution

[0006] A rotorcraft-mounted electronic jamming payload structure, characterized by comprising an antenna radiation area, an electronic module area, and a heat dissipation area, wherein the antenna radiation area is located at the lower part of the payload, the electronic module area is in the middle, and the heat dissipation areas are on both sides of the upper part;

[0007] The antenna radiation area is provided with a radome, an antenna bracket, and a flat spiral antenna;

[0008] The electronic module area is provided with a main housing, a power module, a frequency synthesis module, a digital module, a final transceiver module, an upper heat sink plate, a lower heat sink plate, a front cover plate, a rear cover plate, and a top cover plate. The power module, the frequency synthesis module, the digital module, the final transceiver module, the upper heat sink plate, and the lower heat sink plate are all located in the main housing. The power module and the frequency synthesis module are respectively installed on the upper and lower sides of the upper heat sink plate, and the digital module and the final transceiver module are respectively installed on the upper and lower sides of the lower heat sink plate;

[0009] The heat dissipation area is divided into left and right parts, which are symmetrically arranged on both sides of the electronic module area. The heat dissipation area is provided with a heat dissipation component, a fan and a fan cover. The heat dissipation component is a heat pipe fin combination. One end of the heat pipe is flattened and welded into the heat conduction plate of the electronic module area, and the other end is bent 90 degrees and welded into the heat dissipation fin group; the fan and the fan cover are fixed to the outside of the heat dissipation fins to form an air duct.

[0010] A further technical solution of the present invention is that the antenna cover is divided into two parts, the part that interfaces with the main structure is a ring structure of hard aluminum material, and the remaining main part adopts a quartz honeycomb sandwich structure. The two parts are assembled and bonded with epoxy resin.

[0011] A further technical solution of the present invention is that the antenna cover is a semicircular structure.

[0012] A further technical solution of the present invention is as follows: there are four flat spiral antennas, which are distributed circumferentially with the axis of the antenna bracket as the center.

[0013] A further technical solution of the present invention is that a sealing ring is provided between the top cover plate and the main shell.

[0014] A further technical solution of the present invention is that demoulding rubber pads are provided between the front cover plate, the rear cover plate and the main shell.

[0015] A further technical solution of the present invention is that a sealing ring is provided between the antenna cover and the main shell.

[0016] Beneficial effects

[0017] The present invention provides a rotorcraft-mounted electronic jamming payload structure that utilizes a fully enclosed design. The payload's structure meets design requirements for size, weight, center of gravity, and antenna radiation range, and also meets operational requirements under environmental conditions such as high and low temperatures, rain, and vibration. The details are as follows:

[0018] 1. The size and weight requirements of the rotorcraft payload are met through lightweight and highly integrated design. The payload body is designed to have an axisymmetric structure, and the heat dissipation area is designed to have a bilaterally symmetrical structure to ensure that the center of gravity is located on the central axis of the installation area.

[0019] 2. Low-temperature operation of the load is achieved by selecting low-temperature components. High-temperature operation of the load is achieved primarily through heat dissipation design, in addition to selecting high-temperature-resistant components. This design utilizes a heat sink, heat dissipation components, and a fan.

[0020] 3. The main load structure is designed as a four-sided open frame. The top is a roof panel, with front and rear covers located at the front and back, respectively. The bottom is a removable radome. This structure meets both strength requirements and ease of operation.

[0021] 4. The overall structure meets sealing and rainproof requirements. The front and rear covers are in curved contact with the main structure, and the seal is formed using a demolded rubber gasket to ensure a secure connection between the gasket and the main shell. The upper cover is flat and sealed with a slotted sealing rope. The lower portion is the interface between the radome and the main shell, which is installed using a sleeve-type method. At the sleeve-type interface, a groove is cut into the side of the main shell to install an O-ring to achieve a sealed connection. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] The accompanying drawings are only for the purpose of illustrating particular embodiments and are not to be considered limiting of the present invention. Like reference symbols denote like parts throughout the drawings.

[0023] Figure 1 Installation diagram of interference load on tethered rotorcraft;

[0024] Figure 2 Axonometric drawing of interference load structure;

[0025] Figure 3 Cross-sectional view of interference load structure;

[0026] Figure 4 Main structure welding assembly manufacturing process diagram;

[0027] Figure 5 Main structure bonding and sealing diagram;

[0028] Figure 6 Interference payload antenna radiation airspace coverage diagram. DETAILED DESCRIPTION

[0029] In order to make the objectives, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and examples. It should be understood that the specific embodiments described herein are only intended to illustrate the present invention and are not intended to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.

[0030] The electronic jamming payload on a tethered rotorcraft consists primarily of a functional module, antenna, main structure, antenna bracket, radome, and thermal pad. The functional module includes a power module, frequency synthesizer module, digital module, and final transceiver module. The antennas are four flat spiral antennas, and the main structure includes the main housing, heat sink assembly, heat sink plate, and seals.

[0031] The design layout of the interference payload is divided into an antenna radiation zone, an electronic module zone, and a heat dissipation zone. The antenna radiation zone is located at the bottom of the payload, with the electronic module zone in the middle and heat dissipation zones on both sides of the upper portion. The antenna radiation zone is where the flat-screw antenna is installed. Antenna installation in this zone must meet airspace coverage requirements and maximize the diameter of the flat-screw antenna within the permitted installation space to increase radiation gain. The electronic module zone is where the individual modules are installed. This zone must ensure ease of assembly, commissioning, and maintenance, while also meeting the module's thermal management requirements. Modules in this zone are stacked on a heat conducting plate within the main structure, which transfers heat to the heat dissipation zone via heat pipes. The heat dissipation zone houses a heat dissipation assembly and fan. The heat dissipation assembly consists of a heat pipe and fin assembly. One end of the heat pipe is flattened and welded to the heat conducting plate in the electronic module area, and the other end is bent 90 degrees and welded to the heat dissipation fin assembly. This design ensures heat transfer from the horizontal surface of the heat conducting plate to the vertical heat dissipation zone. The fan and fan cover are fixed to the top of the heat dissipation fins, forming an air duct that dissipates heat from the fins through jet cooling. The heat dissipation fins are arranged horizontally so that the air outlet of the air duct is in a horizontal direction to avoid the air outlet affecting the rise and fall of the rotorcraft.

[0032] The jamming payload 3 is installed at the bottom of a tethered UAV payload platform. The tethered UAV system consists of a tethered UAV 2 and a command vehicle 1. The command vehicle provides power and communication to the UAV via a tethered cable. The jamming payload primarily consists of structural components 4, a power module 5, a frequency synthesizer module 6, a digital module 7, a final-stage transceiver module 8, a flat-screw antenna 9, an electrical interface 10, and a fan 11. There are four flat-screw antennas, two fans, and two electrical interfaces: a high-frequency interface and a low-frequency interface. The remaining components are either single or separate components. The structural assembly consists of a main structure 12, an antenna bracket 13, a radome 14, a fan cover 15, a front cover 16, a rear cover 17, and a top cover 18. There are two fan covers, and the remaining components are also single components. The main structure is constructed by welding and bonding multiple structural components, heat dissipation components, and sealing components. It consists of a main housing 19, a left heat pipe cooling assembly 20, a right heat pipe cooling assembly 21, an upper heat sink plate 22, a lower heat sink plate 23, a top sealing ring 24, a radome sealing ring 25, a front cover demolding rubber pad 26, and a rear cover demolding rubber pad 27. The main housing 19 is first welded to the heat sink components (left heat pipe cooling assembly 20, right heat pipe cooling assembly 21, upper heat sink plate 22, and lower heat sink plate 23), followed by bonding and forming the sealing pads. The heat pipe cooling assembly consists of heat pipes 28, a heat sink base plate 29, and heat sink fins 30, and is manufactured by welding. The radome is divided into two parts. The portion that interfaces with the main structure is a ring-shaped structure 31 made of duralumin, while the remaining main body is a quartz honeycomb sandwich structure 32. The two parts are assembled and bonded with epoxy resin. During installation, the electrical modules (structural assembly 4, power module 5, frequency synthesizer module 6, and digital module 7) are affixed with a 0.5 mm thick thermal pad 33 on the bottom surface of the heat sink. See the detailed structure diagram Figure 2 、 Figure 3 .

[0033] The structural layout design aims to counter ground-based radar equipment with the interference load. The optimal design layout is characterized by a radiation zone at the bottom, a functional module zone in the middle of the upper section, and heat dissipation zones on both sides of the upper section. The lower antenna cover is semicircular to minimize its impact on the flat-screw antenna's radiation beam. The structural material is a quartz honeycomb sandwich structure that meets broadband wave transmission requirements. The functional module area is the main equipment installation area, with modules stacked and mounted on a heat conduction plate. The power module and frequency synthesizer module share a heat conduction plate, while the digital module and final-stage transceiver module share a heat conduction plate. There is a heat dissipation zone on each side. Heat pipes transfer heat from the module zone's heat conduction plate to the fins in the heat dissipation zone, where the heat is dissipated through air cooling. The fins are arranged horizontally, directing the cooling air horizontally to avoid affecting the rotorcraft's ascent and descent.

[0034] Regarding thermal design, the heat dissipation of the power module, frequency synthesizer module, digital module, and final-stage transceiver module in the system's electrical modules is 20W, 30W, 35W, and 20W, respectively. The flat spiral antenna consumes very little power, so heat dissipation can be disregarded. The total system power consumption is no more than 120W. The heat dissipation bottom surfaces of the power module and frequency synthesizer module are symmetrically mounted on both sides of the upper heat conduction plate 31, while the heat dissipation bottom surfaces of the digital module and final-stage amplifier module are symmetrically mounted on both sides of the lower heat conduction plate 32. The heat pipes are 8mm powder-sintered copper heat pipes, each with a power output of 25W. Due to the thickness of the heat conduction plate, the heat absorbing end of the heat pipe is flattened to 3mm and welded into the reserved groove 32 of the heat conduction plate. The heat dissipation end does not need to be flattened and is simply bent and welded into the thermal fins. The power loss after flattening is no more than 10W. The total heat transfer power of the upper and lower heat pipes is no less than 60W, meeting the thermal conductivity requirements. The heat dissipation fins in the heat dissipation zone are 0.3mm thick copper fins with a spacing of 1mm. Select appropriate fan direct blowing blades to meet the air volume of not less than 35m 3 / h.

[0035] Regarding rainproof design, the system utilizes a fully enclosed equipment cavity. To ensure ease of assembly and maintainability, the main structure features four openings: the upper cover, front cover, rear cover, and radome. The upper cover and radome are sealed with sealing ropes during installation, while the front and rear covers are sealed with molded rubber gaskets. Heat is transferred from the interior of the equipment compartment to the heat dissipation zones on both sides via thermally conductive plates, dissipating the heat without compromising the cavity's seal. The fan is rainproof, and the fan cable connects to the equipment compartment through a through-hole for power supply, which is sealed with sealant.

[0036] Regarding the design of airspace coverage. The interference load countermeasure targets are ground targets and low-altitude targets, while avoiding interference with the tethered drone command vehicle. The airspace coverage is designed to be 360-degree ground and low-altitude coverage, and a hollow area is reserved directly below the interference load to avoid interference with the command vehicle. When airspace coverage is met, the antenna installation position is adjusted to obtain a larger flat spiral antenna aperture size to improve the radiation intensity, such as Figure 6 shown.

[0037] The specific implementation steps are as follows:

[0038] Manufacturing process of the main structure:

[0039] 1. Process and manufacture the main shell and perform nickel plating on the surface;

[0040] 2. Manufacture copper powder sintered heat pipes of special length and diameter, flatten one end and bend the other end to the required size and shape before nickel plating the surface;

[0041] 3. Manufacture the gears and base plates for heat dissipation components and perform surface nickel plating;

[0042] 4. Solder the heat dissipation fins, base plate and heat pipes into the required shape to make heat dissipation components;

[0043] 5. Use 1.5mm thick copper plate to make the upper and lower temperature equalizer plates and plate them with nickel;

[0044] 6. Solder and install the nickel-plated main shell, heat dissipation components, and temperature plate according to the position shown in the figure ( Figure 4 );

[0045] 7. Use screws to fix the connection between the plate and the main shell. Apply high-strength thread sealant before installing the screws;

[0046] 8. Make molded rubber pads at the positions shown in the diagram on the front cover and rear cover of the main shell. After molding, the rubber pads are firmly combined with the main shell;

[0047] 9. Use XY-401 glue to glue the rubber rope of the upper cover and the rubber rope of the antenna cover interface to the corresponding position in the figure ( Figure 5 ).

[0048] Interference load assembly process:

[0049] 1. Stick the thermal pad on the bottom surface of the frequency synthesizer module and push it into the corresponding assembly area. Fix it with screws through the process holes on the upper thermal plate.

[0050] 2. Attach the thermal pad to the bottom of the digital module and install it in the corresponding position shown in the figure;

[0051] 3. Install the thermal pad on the heat dissipation area of the power module base plate into the corresponding position shown in the figure;

[0052] 4. Install the thermal pad on the heat dissipation area of the final amplifier module base plate into the corresponding position in the figure;

[0053] 5. Connect the cables;

[0054] 6. Install the antenna bracket at the corresponding position under the main structure;

[0055] 7. Install the flat screw antenna in the corresponding position;

[0056] 8. Install the upper cover, front cover, rear cover and antenna cover.

[0057] After the interference load assembly is completed, it is installed at the load position of the rotorcraft through cable connection and mechanical connection.

[0058] The above description is only a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any technician familiar with this technical field can easily think of various equivalent modifications or replacements within the technical scope disclosed in the present invention, and these modifications or replacements should all be included in the scope of protection of the present invention.

Claims

1. A rotorcraft-mounted electronic jamming load structure, characterized in that It includes antenna radiation area, electronic module area and heat dissipation area. The antenna radiation area is located at the bottom of the payload, the middle of the upper part is the electronic module area, and the two sides of the upper part are heat dissipation areas. The antenna radiation area is provided with a radome (14), an antenna bracket (13), and a flat spiral antenna (9); The electronic module area is provided with a main housing (19), a power module (5), a frequency synthesis module (6), a digital module (7), a final transceiver module (8), an upper heat sink plate (22), a lower heat sink plate (23), a front cover plate (16), a rear cover plate (17), and a top cover plate (18); the power module (5), the frequency synthesis module (6), the digital module (7), the final transceiver module (8), the upper heat sink plate (22), and the lower heat sink plate (23) are all located in the main housing (19); the power module (5) and the frequency synthesis module (6) are respectively installed on the upper and lower sides of the upper heat sink plate (22); the digital module (7) and the final transceiver module (8) are respectively installed on the upper and lower sides of the lower heat sink plate (23); The heat dissipation area is divided into left and right parts, which are symmetrically arranged on both sides of the electronic module area. The heat dissipation area is provided with a heat dissipation component, a fan and a fan cover. The heat dissipation component is a heat pipe fin combination. One end of the heat pipe is flattened and welded into the heat conduction plate of the electronic module area, and the other end is bent 90 degrees and welded into the heat dissipation fin group; the fan and the fan cover are fixed to the outside of the heat dissipation fins to form an air duct.

2. The rotorcraft-mounted electronic jamming load structure according to claim 1, characterized in that: The antenna cover (14) is divided into two parts. The part that interfaces with the main structure is a ring structure (31) made of hard aluminum material, and the remaining main body part adopts a quartz honeycomb sandwich structure (32). The two parts are assembled and bonded with epoxy resin.

3. The rotorcraft-mounted electronic jamming load structure according to claim 2, characterized in that: The radome (14) is a semicircular structure.

4. The rotorcraft-mounted electronic jamming load structure according to claim 1, characterized in that: There are four flat spiral antennas (9) distributed circumferentially with the axis of the antenna bracket (13) as the center.

5. The rotorcraft-mounted electronic jamming load structure according to claim 1, characterized in that: A sealing ring is provided between the top cover plate (18) and the main housing (19).

6. The rotorcraft-mounted electronic jamming load structure according to claim 1, characterized in that: A demoulding rubber pad is provided between the front cover plate (16), the rear cover plate (17) and the main housing (19).

7. The rotorcraft-mounted electronic jamming load structure according to claim 1, characterized in that: A sealing ring is provided between the radome (14) and the main housing (19).

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