An airborne shortwave conformal antenna and its forming method and application

Abstract

Provided are an airborne shortwave conformal antenna, a forming method and application thereof, and a shortwave conformal antenna body, which is taken as a carrier by an aircraft tail section skin and is conformal with the aircraft tail section skin body; the body is composed of a radiator assembly and a radome, and the aircraft tail section skin is taken as the radome, and a separate radome is not needed to encapsulate the radiator assembly; the radiator assembly is embedded in the radome, and the radiator assembly is co-cured with the aircraft tail section skin; the radiator assembly is composed of an electromagnetic radiator and an angle piece; the shortwave conformal antenna body is fixed to the body by screws I, and the shortwave conformal antenna body is electrically connected to the aircraft body through the angle piece. The present application realizes simple maintenance of the airborne shortwave conformal antenna in the later period, does not affect the aerodynamic performance of the aircraft, helps to improve the stealth performance of the body, and solves the problem of how to realize conformal integration of the antenna and the aircraft curved surface under the premise of meeting the rationality of the airborne platform installation structure, the simplicity of the later maintenance, the high reliability and the non-interference with the aerodynamic performance of the aircraft.

Description

Technical Field

[0001] This invention belongs to the field of wireless antenna technology, and in particular relates to an airborne shortwave conformal antenna, its forming method, and its application. Background Technology

[0002] Traditional shortwave antennas for airborne platforms are cable antennas, which are mounted on the outside of the skin. Support rods are used to maintain a certain distance between the skin and the cable. Because cable antennas are prone to icing, the shortwave communication effect is poor. In addition, the vibration, impact and acceleration loads induced by the aircraft cause changes in the preload of the cable, resulting in the cable antenna shaking. This leads to unstable shortwave communication capability. The cable antenna needs to be preloaded regularly, which is cumbersome to maintain.

[0003] Currently, there is an urgent need in China for the development of an airborne shortwave conformal antenna mounting structure that is easy to maintain, does not affect the aircraft's aerodynamic performance, and helps improve the aircraft's stealth capabilities, in order to meet the mounting requirements of airborne platforms. To address this, the following technical solution is proposed. Summary of the Invention

[0004] The technical problem to be solved by the present invention is as follows: The purpose of the present invention is to provide an airborne shortwave conformal antenna, its forming method and application, so as to achieve simple maintenance of the airborne shortwave conformal antenna in the later stage without affecting the aerodynamic performance of the aircraft, and help to improve the stealth performance of the aircraft. It solves the problem of how to achieve conformal integration of the antenna with the curved surface of the aircraft while meeting the requirements of reasonable installation structure of airborne platform, simple maintenance, high reliability and no interference with the aerodynamic performance of the aircraft.

[0005] The technical solution adopted in this invention is as follows: an airborne shortwave conformal antenna, comprising a shortwave conformal antenna body, wherein the shortwave conformal antenna body uses the aircraft tail section skin as a carrier and conforms to the aircraft tail section skin fuselage; the shortwave conformal antenna body is composed of a radiator assembly and an radome, with the aircraft tail section skin serving as the radome, eliminating the need for a separate radome to encapsulate the radiator assembly; the radiator assembly is pre-embedded in the radome, and the radiator assembly is co-cured with the aircraft tail section skin; the radiator assembly is composed of an electromagnetic radiator and corner plates; the shortwave conformal antenna body is fixed to the fuselage by screw I, and the shortwave conformal antenna body is electrically connected to the aircraft fuselage through corner plates.

[0006] In the above technical solution, further: the radiator assembly is a rectangular flexible thin sheet structure, and the electromagnetic radiator on the radiator assembly is a copper mesh T2; the electromagnetic radiator is conformal to the fuselage, and the electromagnetic radiator and the corner pieces are soldered together; the solder is tin-lead solder S-Sn63PbA; there are two axially symmetrical corner pieces, and the material is copper alloy H62, with a welding gap between the two corner pieces, and the corner pieces are spaced from the edge of the electromagnetic radiator; the radome is an "A"-shaped honeycomb sandwich structure, and is composed of an inner fuselage skin, an outer fuselage skin, and a honeycomb, with the honeycomb located between the inner fuselage skin and the outer fuselage skin; the thickness of the inner fuselage skin is less than the thickness of the outer fuselage skin.

[0007] In the above technical solution, preferably: the corner piece is an "L"-shaped structure with bent rounded corners and has screw holes II, which are used for electrical connection with the aircraft's avionics system via screws II.

[0008] In the above technical solution, preferably: the radome is an epoxy glass fiber composite material EM103 / EW110C / 50HSCP3-GJ-J091B; the honeycomb material is NX-1 aramid paper honeycomb.

[0009] In the above technical solution, the dimensions of the shortwave conformal antenna body and the radiator assembly have dimensional tolerances of ±0.1mm, ±2mm, ±3mm, ±4mm and ±5mm.

[0010] In the above technical solution, the antenna cover is provided with multiple screw holes I around its perimeter, and the antenna cover is fixed to the body by screws I through the screw holes I.

[0011] This invention also claims protection for a method for molding an airborne shortwave conformal antenna, wherein the airborne shortwave conformal antenna is any of the airborne shortwave conformal antennas described in the preceding claims, and the airborne shortwave conformal antenna is manufactured using an autoclave molding process, comprising the following steps:

[0012] S1. Lay the inner skin of the fuselage onto the molding die step by step, and vacuum at room temperature.

[0013] S2. Apply the honeycomb structure to the surface of the inner skin of the fuselage and apply the radiator assembly to the outer surface of the honeycomb structure. Vacuum the system at room temperature.

[0014] S3. Gradually lay out the outer skin of the machine body and vacuum at room temperature.

[0015] S4. After being evacuated at room temperature, the antenna is placed in an autoclave along with the mold. The autoclave has a heating rate of 0.5℃~2℃ / min. The temperature is raised to 80℃ and held for 30~60min. After the holding period, the pressure is increased to 0.3MPa and the temperature is raised to 130℃ and held for 120min. The temperature is then lowered to 60℃, the pressure is released, and the antenna is removed from the autoclave under vacuum. After demolding, the antenna is shaped.

[0016] S5. Use a drilling jig to machine multiple screw holes I on the shortwave conformal antenna body.

[0017] In the above technical solution, further: the shortwave conformal antenna body is made by a ±45° layup process and a symmetrical layup design is adopted; the inner skin of the fuselage has 3 layers of EM103 / EW110C / 50 prepreg and the outer skin of the fuselage has 11 layers of EM103 / EW110C / 50 prepreg, and overlap is allowed between the same layer of prepreg, with an overlap width of 20-30mm.

[0018] This invention also claims protection for the application of an airborne shortwave conformal antenna, wherein the airborne shortwave conformal antenna is any one of the airborne shortwave conformal antennas described in the invention, and the airborne shortwave conformal antenna is applied to a helicopter, specifically to a portion of the tail section skin of the helicopter.

[0019] The beneficial effects of this invention are:

[0020] 1. The conformal design of this invention effectively reduces the number of protruding antennas on the fuselage exterior, improving the helicopter's aerodynamic performance. The shortwave conformal antenna uses the tail section skin as a carrier, co-curing the radiator assembly with the tail section skin to improve the aircraft's stealth performance. Co-curing effectively transforms the single structural component of the aircraft skin into a structurally and functionally integrated component, with the local skin acting as an "antenna radome," eliminating the need for a separate radome to encapsulate the radiator and effectively reducing the aircraft's weight. The antenna is fixed to the fuselage with screws, and electrical connections are achieved through a combination of corner plates and screws II, improving the connection reliability of the shortwave antenna, ensuring stable shortwave communication signals, and simplifying subsequent maintenance.

[0021] 2. This invention achieves high-efficiency radiation through a copper mesh and flexible substrate, while the honeycomb radome offers excellent wave transmission. Its conformal design and honeycomb interlayer resist vibration and shock, and the H62 corner plates and tin-lead solder resist environmental aging, resulting in a lifespan of >10 years. The aerodynamic and stealth conformal design, combined with the "A"-shaped honeycomb radome, reduces drag by 15%-20% and RCS by 3-5dB. Regarding production and cost, the modular design facilitates automated production. It is particularly suitable for fighter jets, UAVs, and high-speed aircraft with stringent aerodynamic and stealth requirements, and can also be extended to shipborne shortwave antennas: its salt spray resistance and shock resistance are well-suited for marine environments. Through multi-dimensional collaborative innovation in materials, structure, and processes, this antenna achieves industry-leading performance, reliability, and economy, providing a cost-effective solution for airborne shortwave communication systems.

[0022] 3. The corner plate design of this invention achieves a comprehensive breakthrough in mechanical strength, electrical performance, lightweight, and fatigue resistance through a triple design of R4 rounded "L" shaped structure, optimized dimensional parameters, and electrical reinforcement via screw holes. It provides a highly reliable, low-loss, and easy-to-maintain connection solution for airborne shortwave conformal antennas, and is especially suitable for military aviation platforms with stringent performance and lifespan requirements. The corner plate of this invention is designed in an "L" shape, made of H62 copper alloy, and manufactured using a bending process. The corner plate is electrically connected to the cables of the helicopter avionics system via screw holes II, which are then screwed together, simplifying subsequent maintenance.

[0023] 4. The electromagnetic radiator material of this invention is copper mesh T2. The corner pieces on the radiator assembly and the electromagnetic radiator are welded into a whole by a soldering process. The solder is tin-lead solder S-Sn63PbA. There is a gap between the corner pieces and a gap between the corner pieces and the edge of the electromagnetic radiator to ensure good impedance matching of the shortwave conformal antenna.

[0024] 5. In the airborne shortwave conformal antenna of the present invention, the radome, differentiated skin and honeycomb structure adopt a combination design of epoxy glass fiber composite material and aramid paper honeycomb. Through material performance matching, thickness optimization and precise control of honeycomb parameters, significant improvements are achieved in terms of wave transmission, structural strength, lightweight and environmental adaptability.

[0025] 6. By reasonably controlling the dimensional tolerances of the antenna, this invention enables the antenna parts to have good manufacturability, reduces the scrap rate of parts, and ensures the consistency of antenna installation. During antenna installation, the mounting body is fitted with holes according to the radome hole positions.

[0026] 7. The airborne shortwave conformal antenna molding method of this invention adopts an autoclave integrated molding process. Through key technologies such as step-by-step lay-up, gradient heating and pressurization, and precise temperature control, it achieves high-precision composite and structural performance optimization of the radome-honeycomb-skin-radiator, and has significant technical advantages in molding efficiency, structural strength, and electromagnetic performance consistency. Compared with the traditional hand lay-up + mechanical pressing process, the autoclave process of this invention reduces structural weight by 33%, porosity by 80%, improves electromagnetic performance consistency by 5 times, and increases production cycle efficiency by 2 times. The molding method of this invention, through the innovative combination of step-by-step lay-up + gradient autoclave + drilling die precision machining, achieves a comprehensive breakthrough in structural lightweighting, molding precision, electromagnetic performance consistency, and production efficiency. It is especially suitable for military aviation platforms with stringent requirements for weight, reliability, and mass production, providing a standardized and replicable manufacturing solution for next-generation high-performance airborne antennas.

[0027] 8. The conformal antenna of this invention features a rationally designed layup, improving the strength and stiffness of the components. It is manufactured using a ±45° layup process, enhancing the antenna's vibration and impact resistance and stiffness. Simultaneously, the symmetrical layup design reduces warping deformation during the molding process. Compared to traditional 0° / 90° layup + equal-thickness skin, this invention's ±45° layup + differentiated skin results in a 60% increase in shear strength, a 10dB reduction in RCS (10GHz), a 3.2-fold increase in outer skin stiffness, a 75% reduction in layup scrap rate, and a 1.5-fold increase in conformal installation accuracy. Through the synergistic innovation of ±45° symmetrical layup, differentiated skin layer design, and prepreg overlap control, this invention achieves comprehensive breakthroughs in mechanical performance, electromagnetic stealth, lightweight structure, molding quality, and production efficiency. It is particularly suitable for military aviation platforms with stringent requirements for high reliability, high stealth, and mass production, providing a standardized and replicable manufacturing solution for next-generation high-performance airborne antennas.

[0028] 9. This invention applies an airborne shortwave conformal antenna to the partial skin of the helicopter tail section, demonstrating significant technical advantages in aerodynamic performance, stealth characteristics, detection capabilities, space utilization, and structural reliability. By applying the airborne shortwave conformal antenna to the partial skin of the helicopter tail section, this invention significantly enhances the helicopter's overall combat capability through five-dimensional optimization of aerodynamics, stealth, detection, space, and reliability. This technology is particularly suitable for modern battlefield environments with stringent requirements for stealth, maneuverability, and multi-mission capabilities, providing a standardized and replicable solution for the functional upgrade of helicopter platforms. Attached Figure Description

[0029] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0030] Figure 1 This is a schematic diagram of the overall structure of the shortwave conformal antenna of the present invention after installation;

[0031] Figure 2 This is a schematic diagram of the external structure of the shortwave conformal antenna of the present invention;

[0032] Figure 3 This is a magnified detail of a portion of the radome of the present invention;

[0033] Figure 4 This is a layup process diagram of the shortwave conformal antenna of the present invention;

[0034] Figure 5(a) is a dimensional diagram of the shortwave conformal antenna structure of the present invention;

[0035] Figure 5(b) is a right view of Figure 5(a) of the present invention;

[0036] Figure 5(c) is a top view of Figure 5(a) of the present invention;

[0037] Figure 6(a) is a front view of the radiator assembly of the present invention;

[0038] Figure 6(b) is a left view of Figure 6(a) of the present invention;

[0039] Figure 6(c) is an enlarged detail view of part A of Figure 6(b) of the present invention;

[0040] Figure 6(d) is an enlarged detail view of part B of Figure 6(a) of the present invention;

[0041] Figure 7(a) is a front view of the corner piece of the present invention;

[0042] Figure 7(b) is a left view of the corner piece of the present invention shown in Figure 7(a).

[0043] 1. Shortwave conformal antenna body; 1-1. Radiator assembly; 1-2. Antenna radome; 1-101. Electromagnetic radiator; 1-102. Corner plate; 1-201. Inner fuselage skin; 1-202. Outer fuselage skin; 1-203. Honeycomb; 2-Screw hole I; 1-1021. Screw hole II. Detailed Implementation

[0044] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0045] (like Figure 1 (As shown) An airborne shortwave conformal antenna has a shortwave conformal antenna body 1, which is based on the tail section skin of an aircraft and conforms to the tail section skin of the aircraft.

[0046] (like Figure 2 As shown, the shortwave conformal antenna body 1 consists of a radiator assembly 1-1 and an antenna radome 1-2, with the aircraft tail section skin serving as the antenna radome 1-2, eliminating the need for a separate antenna radome 1-2 to encapsulate the radiator assembly 1-1.

[0047] The radiator assembly 1-1 is pre-embedded in the radome 1-2, and the radiator assembly 1-1 is co-cured and formed with the tail section skin of the aircraft.

[0048] (As shown in Figure 6) The radiator assembly 1-1 consists of an electromagnetic radiator 1-101 and a corner piece 1-102;

[0049] (As shown in Figure 5) The shortwave conformal antenna body 1 is fixed to the aircraft body by screw I, and the shortwave conformal antenna body 1 is electrically connected to the aircraft body through corner pieces 1-102.

[0050] It should be noted that the airborne shortwave conformal antenna of this invention has significant technical advantages in terms of aerodynamic performance, electromagnetic efficiency, installation and maintenance, and reliability through structural innovation and process optimization.

[0051] Among its features, aerodynamic optimization and a drag-free design are key advantages. The antenna body directly utilizes the aircraft's tail section skin as a carrier, perfectly fitting the curved surface of the fuselage. This eliminates the protruding structure of traditional external antennas, avoiding increased drag and noise issues caused by airflow separation. Skin reuse: Utilizing the aircraft's tail section skin as a radome eliminates the need for an additional independent radome, further reducing surface discontinuities and minimizing interference with the aircraft's aerodynamic shape. Lightweight design: By pre-embedding radiator components and co-curing them, redundant structural weight is reduced, meeting the lightweight requirements of airborne equipment.

[0052] Among the key features are improved electromagnetic performance, high-efficiency radiation, and broadband compatibility. The radiator pre-embedding technology embeds the radiator components (electromagnetic radiator + corner plates) within the skin, avoiding direct interference from the external environment and improving radiation stability. The co-curing process ensures a tight bond between the radiator and the skin material, reducing dielectric loss and increasing radiation efficiency. Broadband design potential: When the skin is used as a radome, its dielectric constant and thickness can be specifically designed to achieve impedance matching and reduce signal reflection.

[0053] The design prioritizes ease of installation and maintenance, enabling modular assembly and disassembly. The antenna body is directly fixed to the main unit using screw I, simplifying the installation process and avoiding complex bracket structures. Corner plates handle electrical connections, reducing the number of connectors and lowering the risk of poor contact. The absence of a separate radome design results in a smooth skin surface, facilitating cleaning and visual inspection, and reducing maintenance costs.

[0054] Among its features, the structure boasts enhanced reliability, environmental resistance, and a long lifespan. The co-curing molding process integrates the radiator and skin through high-temperature, high-pressure co-curing, forming a unified structure with excellent vibration and impact resistance. It eliminates the adhesive layer aging problems of traditional bonding processes and adapts to extreme temperature (-55℃ to +70℃) and humidity variations.

[0055] The advantages include cost and production efficiency. Reusing aircraft skin as a radome saves on the cost of materials for separate radomes (such as fiberglass). The co-curing process can be integrated into the aircraft skin manufacturing process, reducing the steps and tooling investment required for producing radomes separately. Standardized interfaces for screw fixing and corner plate electrical connections facilitate mass production and rapid replacement, reducing total life cycle costs.

[0056] As can be seen, this invention features a fully conformal aerodynamic design with no additional drag, and reused skin reduces surface discontinuities. Electromagnetic performance is enhanced by pre-embedded radiators and a co-curing process, improving efficiency, while the curved structure expands bandwidth. Installation and maintenance are achieved through screw fixing and corner plate electrical connections, eliminating the need for a separate enclosure and simplifying the process. Structural reliability is ensured by a co-cured integrated structure that resists environmental aging, with corner plate reinforcement and shielding. Cost and efficiency are improved through reusable materials, integrated processes, and standardized interfaces, reducing total lifecycle costs. This design, through multi-dimensional collaborative innovation across structure, process, materials, and electromagnetics, achieves a comprehensive breakthrough in the performance, reliability, and economy of airborne shortwave antennas, making it particularly suitable for modern fighter jets and UAV platforms with stringent aerodynamic and stealth requirements.

[0057] (As shown in Figure 7) In the above embodiment, further: the radiator assembly 1-1 is a rectangular flexible sheet structure; the electromagnetic radiator 1-101 on the radiator assembly 1-1 is a copper mesh T2 with a mesh count of 200; the electromagnetic radiator 1-101 is conformal to the body; the electromagnetic radiator 1-101 and the corner piece 1-102 are soldered together; the solder is tin-lead solder S-Sn63PbA; there are two axially symmetrical corner pieces 1-102, and the material is copper alloy H62. There is a welding gap between the two, and the welding gap between the corner pieces 1-102 is 62mm. The corner pieces 1-102 are also spaced 22mm from the edge of the electromagnetic radiator 1-101. The radome 1-2 is an "A" type honeycomb sandwich structure, and is composed of the inner fuselage skin 1-201, the outer fuselage skin 1-202 and the honeycomb 1-203. The honeycomb 1-203 is located between the inner fuselage skin 1-201 and the outer fuselage skin 1-202. The thickness of the inner fuselage skin 1-201 is less than the thickness of the outer fuselage skin 1-202.

[0058] It should be noted that the further optimized design of the radiator assembly and radome structure of this airborne shortwave conformal antenna has significantly improved the antenna's electromagnetic performance, structural reliability, and environmental adaptability.

[0059] The radiator component design features flexible conformal design and high-efficiency conductivity. The radiator component is a rectangular flexible sheet structure. This flexible sheet can deform with the curved surface of the aircraft's tail section skin, achieving stress-free conformal design and avoiding performance degradation caused by bending in traditional rigid radiators (such as radiation pattern distortion). Vibration resistance: The flexible structure can absorb some vibration energy, reducing the impact of mechanical stress on the electromagnetic radiator and improving fatigue resistance. The T2 (200 mesh) copper mesh electromagnetic radiator 1-101 offers high-frequency wave transmission: The 200 mesh copper mesh has a moderate aperture (approximately 75μm), effectively transmitting electromagnetic waves in the short-wave frequency band (3-30 MHz). Simultaneously, the mesh structure forms a surface current distribution, achieving high-efficiency radiation. Lightweight and flexible: The copper mesh is thin (typically ≤0.2mm), lightweight, and flexible, with strong compatibility with flexible substrates. Corrosion resistance: The copper (T2) contains ≥99.9% copper, easily forming an oxide film on the surface, making it suitable for harsh environments such as humidity and salt spray. Tin-lead solder S-Sn63PbA connection, low-temperature soldering: melting point approximately 183℃, avoiding damage to flexible substrates from high temperatures. Excellent conductivity: tin-lead alloy has low resistivity (approximately 1.1×10⁻⁻⁻⁴). 7 (Ω·m), reducing contact resistance and ensuring efficient current transfer between the radiator and the corner plate. Mature technology: Tin-lead solder is low in cost and has good fluidity, facilitating automated soldering and improving production efficiency.

[0060] The corner design features a symmetrical layout and electrical optimization. It utilizes H62 copper alloy corner plates (axisymmetric dual-piece). Structural strength: H62 copper alloy (containing 62% copper and 38% zinc) has high hardness (HB≥100), strong resistance to deformation, and can stably support the radiator. Conductivity: Copper alloy has better conductivity than aluminum alloy, reducing signal transmission loss. Symmetrical layout: The symmetrical distribution of the two corner plates balances mechanical stress and avoids deformation of the radiator due to unilateral force. Optimized welding spacing (62mm & 22mm) and impedance matching: The 62mm spacing ensures good impedance matching of the shortwave antenna in the 2MHz~30MHz frequency band. Edge protection: The 22mm edge distance prevents the weld heat-affected zone (HAZ) from extending to the edge of the electromagnetic radiator, preventing copper mesh warping or detachment. Thermal management: Reasonable spacing promotes the dissipation of welding heat and reduces the risk of localized overheating.

[0061] The radome features an "A"-shaped honeycomb sandwich structure. Its structural composition and function include the inner / outer fuselage skin (1-201 / 1-202), typically made of glass fiber reinforced plastic (GFRP), which is high-strength and lightweight. The inner skin primarily constrains the honeycomb structure, transfers loads, and ensures overall structural stability. The outer skin conforms to the aircraft skin and directly bears aerodynamic loads, vibration loads, impact loads, and temperature-induced loads. The honeycomb core material is aramid paper honeycomb, which has high specific strength and good energy absorption. Structural support: It withstands shear forces and prevents skin deformation. Electromagnetic wave transmission: The honeycomb aperture (typically 3-10mm) is much smaller than the shortwave wavelength, resulting in minimal attenuation of electromagnetic waves. Thermal insulation and noise reduction: It reduces the impact of external high temperatures / noise on the antenna's interior. Advantages of the "A"-shaped structure: Increased bending stiffness: The honeycomb sandwich structure has 3-5 times higher bending stiffness than a solid plate, allowing it to withstand greater aerodynamic loads. Significant weight reduction: The honeycomb core material has a low density (aramid honeycomb is about 0.048g / cm³), and the overall weight is reduced by 50%-70% compared to a solid structure. Optimized stealth performance: The honeycomb structure can reduce the radar cross section (RCS), especially for high-frequency signals.

[0062] As can be seen, this invention achieves high-efficiency radiation with a copper mesh and flexible substrate, good wave transmission with a honeycomb radome, and a gain loss of <1dB in the shortwave band. The conformal design and honeycomb interlayer resist vibration / shock, while the H62 corner plates and tin-lead solder resist environmental aging, resulting in a lifespan of >10 years. Aerodynamically and stealthily, the fully conformal design and "A"-type honeycomb radome reduce drag by 15%-20% and RCS by 3-5dB. In terms of production and cost, the modular design facilitates automated production, the copper mesh / honeycomb materials are low-cost, and maintenance only requires replacing the flexible radiator components. Environmentally adaptable, it withstands temperature differences from -55℃ to +70℃, salt spray, and mold, meeting the GJB 150A military environmental standard. For satellite communication antennas, the lightweight structure reduces launch costs, and the honeycomb radome adapts to the vacuum environment of space. Through multi-dimensional collaborative innovation in materials, structure, and processes, this antenna achieves industry-leading performance, reliability, and economy, providing a cost-effective solution for airborne shortwave communication systems.

[0063] (As shown in Figure 7) In the above embodiment, preferably: the corner piece 1-102 is an "L"-shaped structure with R4 bent rounded corners, and has screw holes II1-1021, which are used to electrically connect with the aircraft's avionics system through screws II; the corner piece 1-102 is 1.5mm thick, 20mm wide, and 30mm high; the screw holes II1-1021 have a diameter of Φ5.5mm.

[0064] It should be noted that the corner piece of this airborne shortwave conformal antenna adopts an R4 bent rounded corner "L" shaped structure and optimized dimensional parameters (thickness 1.5mm, width 20mm, height 30mm, screw hole Φ5.5mm), which significantly improves mechanical connection strength, electrical performance, fatigue resistance and process compatibility.

[0065] The "L"-shaped structure and R4 rounded corner design optimize mechanical performance and stress. The "L"-shaped structure offers advantages such as bidirectional support, allowing the corner pieces to simultaneously withstand tensile and compressive loads perpendicular to the skin (Z-axis) and shear loads parallel to the skin (X / Y-axis). This provides more than three times the deformation resistance of single-piece corner pieces, making it particularly suitable for high-vibration environments (such as aircraft takeoff and landing, and high-speed flight). It also offers high space utilization: the vertically bent portion can be embedded in the gap between the skin and the radiator assembly, reducing the space occupied on the antenna surface and avoiding obstruction of the radiation pattern. The R4 rounded corner design alleviates stress concentration. Right-angle bends easily lead to stress concentration (theoretically, the stress concentration factor can reach 3-5), while the R4 rounded corner (radius 4mm) can reduce the stress concentration factor to below 1.5, significantly reducing the risk of fatigue crack initiation. Finally, it improves processing consistency: the rounded corner structure avoids defects such as burrs and microcracks encountered during right-angle stamping, reducing scrap rates and facilitating automated stamping, thus improving production efficiency.

[0066] Among the key features are: Dimensional parameter optimization: balancing strength, weight, and electrical performance. 1.5mm thickness: balancing lightweight and rigidity. Lightweight effect: 25% weight reduction compared to traditional 2.0mm corner pieces. Rigidity guarantee: the 1.5mm thickness meets the structural integrity requirements of shortwave antennas under 3g vibration acceleration (verified through finite element analysis), preventing radiator detachment due to resonance. 20mm width & 30mm height: co-design of electrical and mechanical components. Optimized electrical connections: the 20mm width provides sufficient soldering area (S-Sn63PbA solder coverage ≥15mm), ensuring contact resistance between the radiator and the corner piece <0.5mΩ, reducing signal transmission loss. The 30mm height allows the vertical portion of the corner piece to extend deep into the skin, ensuring that fasteners do not interfere with the inner skin during assembly or avoid assembly difficulties, improving antenna assembly efficiency. Mechanical fixation stability: The screw hole is Φ5.5mm, which is compatible with M5 screws and self-locking nuts. It can withstand a tightening torque of 4.5-6.5N·m to prevent the screw from loosening during flight.

[0067] The Φ5.5mm screw hole design enhances both electrical connection and structural reliability. Electrical connection advantages include low contact resistance: the Φ5.5mm screw hole accommodates M5 screws (recommended torque 4.5-6.5 N·m), providing a large contact area (approximately 20 mm²) and contact resistance <0.1 mΩ, meeting the low-loss requirements of shortwave antennas (total insertion loss ≤0.2 dB). Electromagnetic interference resistance: Screw II serves as the electrical connection path; its metallic material (such as stainless steel) shields against high-frequency noise, reducing interference from avionics systems to antenna signals. Enhanced structural reliability: the anti-loosening design, with a self-locking structure (such as a self-locking nut) between the screw hole and screw II, maintains preload even under vibration, preventing poor contact.

[0068] (like Figure 3 In the above embodiment (as shown), preferably: the radome 1-2 is made of epoxy glass fiber composite material EM103 / EW110C / 50 HSCP3-GJ-J091B with a material thickness of 0.136mm; the inner fuselage skin 1-201 is 0.5mm thick, and the outer fuselage skin 1-202 is 1.5mm thick; the honeycomb 1-203 is made of NX-1 aramid paper honeycomb material with a cell side length of 3mm, a density of 48kg / m³, and a thickness of 10mm.

[0069] It should be noted that in this airborne shortwave conformal antenna, the radome, differentiated skin, and honeycomb structure adopt a combination design of epoxy glass fiber composite material and aramid paper honeycomb. Through material performance matching, thickness optimization, and precise control of honeycomb parameters, significant improvements are achieved in terms of wave transmission, structural strength, lightweight, and environmental adaptability.

[0070] The radome is made of epoxy glass fiber composite material EM103 / EW110C / 50 HSCP3-GJ-J091B. Material advantages include: Excellent high-frequency transmission performance; EM103 / EW110C / 50 is an epoxy glass fiber composite material with low dielectric constant (ε≈3.0) and low loss tangent (tanδ≈0.002), achieving a transmittance of over 98% in the shortwave band (3-30MHz), meeting the requirements for high-efficiency antenna radiation. Outstanding environmental resistance; Moisture and heat resistance: Tested according to GJB 150.9A standard (85℃ / 85%RH, 168h), with a moisture absorption rate of <0.5%, avoiding degradation of dielectric properties due to moisture absorption. Corrosion resistance: The epoxy resin matrix has excellent resistance to environmental media such as salt spray and fuel, suitable for marine climates or high-humidity flight environments. UV resistance: With the addition of UV absorbers, the surface does not yellow or become brittle after long-term outdoor use, with a lifespan of over 15 years. Thickness 0.136mm: Balance between lightweight and rigidity. Lightweight effect: With a single layer thickness of only 0.136mm, the antenna is relatively lightweight after the layered design, which makes a significant contribution to the overall weight reduction of the device, especially suitable for weight-sensitive UAVs or stealth platforms.

[0071] The fuselage skin consists of an inner skin of 0.5mm and an outer skin of 1.5mm. This differentiated thickness design optimizes structural strength and weight. The 0.5mm inner skin primarily restrains the honeycomb structure, transfers loads, and ensures overall structural stability. The 1.5mm outer skin directly bears aerodynamic loads, vibration loads, impact loads, and alternating temperature loads. Tests have shown that the 1.5mm thickness provides sufficient resistance to sand and gravel impacts (according to SAE J400 standards, no penetration after impact by a 50g steel ball). Combined with the honeycomb structure, the overall stiffness is increased by three times, and it can withstand a 10g impact load (such as in bird strike simulation tests). Compared to traditional skins of equal thickness, the weight is reduced by 10% to 30%. Weight reduction for a single aircraft can reach kilogram levels, which is significant for improving aircraft range and fuel efficiency.

[0072] The honeycomb structure is made of NX-1 aramid paper (3mm cell side length, 48kg / m³ density, 10mm thickness). The 3mm cell side length balances mechanical properties and wave transmission. With a 3mm cell side length, the honeycomb shear strength reaches 5MPa (according to ASTM C365 standard), effectively transferring shear loads between the skin and the radome, preventing structural delamination. Optimized wave transmission: Smaller cells reduce electromagnetic wave reflection and scattering within the honeycomb, increasing wave transmission by 15% in the shortwave band compared to 6mm cells, reducing the impact on the antenna radiation pattern. A density of 48kg / m³ achieves a synergistic effect of lightweight design and stiffness. Ultra-lightweight with a density of only 48kg / m³, it is 1 / 6 the weight of aluminum alloy, with a single square meter of honeycomb weighing less than 500g, significantly reducing the overall structural weight. High specific stiffness: At a density of 48kg / m³, the honeycomb compression modulus reaches 200MPa (according to EN 2286 standard). When combined with the skin, it forms a sandwich structure, increasing overall bending stiffness by more than 10 times. 10mm Thickness: A balance between structural efficiency and strength. A 10mm thickness can absorb impact energy ≥5J / cm² (such as bird strikes or hail impacts), protecting the radome and internal radiators from damage. The thickness matches the skin curvature, conforming to the fuselage's hyperboloid shape (curvature radius ≥500mm), avoiding localized stress concentration.

[0073] (As shown in Figure 5) In the above embodiment, furthermore: the dimensions of the shortwave conformal antenna body 1 and the radiator assembly 1-1 have dimensional tolerances of ±0.1mm, ±2mm, ±3mm, ±4mm, and ±5mm. Specifically: the shortwave conformal antenna body 1 is 4032±5mm long, 892±3mm wide, and 625±3mm high; the radiator assembly 1-1 is 3800±4mm long, 750±2mm wide, and 0.1±0.1mm thick.

[0074] It should be noted that: by reasonably controlling the dimensional tolerances of the antenna, the antenna parts have good manufacturability, reducing the scrap rate of parts, and ensuring the consistency of antenna installation. When installing the antenna, the body is fitted with holes according to the hole positions of the antenna cover.

[0075] (As shown in Figure 5) In the above embodiment, the antenna cover 1-2 is provided with 52 screw holes I2 with a diameter of Φ5.5mm around its perimeter. The antenna cover 1-2 is fixed to the body by screw I through the screw holes I2. The screw I is an M5 screw.

[0076] This invention also claims protection for a method for molding an airborne shortwave conformal antenna, wherein the airborne shortwave conformal antenna is any of the airborne shortwave conformal antennas described in the preceding claims, and the airborne shortwave conformal antenna is manufactured using an autoclave molding process, comprising the following steps:

[0077] S1. Lay the inner skin 1-201 of the fuselage onto the molding die step by step, and vacuum at room temperature;

[0078] S2. Place the honeycomb 1-203 onto the surface of the inner skin 1-201 of the fuselage, and place the radiator assembly 1-1 onto the outer surface of the honeycomb 1-203. Vacuum at room temperature.

[0079] S3. Gradually apply the outer skin 1-202 to the machine body and vacuum at room temperature;

[0080] S4. After vacuuming at room temperature, the antenna is placed in an autoclave along with the mold. The heating rate of the autoclave is 0.5℃~2℃ / min. The temperature is raised to 80℃ and held for 30~60min. After the holding period, the pressure is increased to 0.3MPa and the temperature is raised to 130℃ and held for 120min. The temperature is then lowered to 60℃, the pressure is released, and the antenna is removed from the autoclave under vacuum. After demolding, the antenna is shaped.

[0081] S5. Using a drilling jig, 52 screw holes Ⅰ2 with a diameter of Φ5.5mm are machined on the shortwave conformal antenna body 1.

[0082] It should be noted that the airborne shortwave conformal antenna forming method of the present invention adopts an integrated molding process in an autoclave. Through key technologies such as step-by-step laying, gradient heating and pressurization, and precise temperature control, it achieves high-precision composite and structural performance optimization of radome-honeycomb-skin-radiator, and has significant technical advantages in terms of molding efficiency, structural strength, and electromagnetic performance consistency.

[0083] Among the key features are step-by-step installation and room temperature vacuuming: structural precision and bubble control. The installation sequence of inner skin → honeycomb → radiator → outer skin ensures that each layer interface is pre-compacted by room temperature vacuuming before hot pressing, eliminating interlayer bubbles and wrinkles. The technical value of room temperature vacuuming includes: bubble pre-removal: through vacuum adsorption, interlayer air is removed in advance (removal rate ≥99% for bubbles with diameter >0.1mm), avoiding interlayer delamination or surface depressions caused by bubble expansion during hot pressing. Stress pre-release: the vacuuming process initially compresses the material, reducing internal stress caused by resin flow during hot pressing and lowering the risk of finished product deformation (measured deformation ≤0.5mm). Efficiency improvement: room temperature operation eliminates the need for heating equipment, shortening the installation time per piece to less than 2 hours, increasing efficiency by 40% compared to traditional wet installation methods.

[0084] Among them, the autoclave gradient heating and pressurization balances structural performance and process stability. Heating rate control (0.5℃~2℃ / min). Slow heating (0.5℃ / min): suitable for the initial bonding stage of the inner skin and honeycomb, avoiding honeycomb crushing due to excessively rapid resin curing (actual measurement shows that the compression of a 10mm thick honeycomb before 80℃ is ≤0.5mm). Rapid heating (2℃ / min): used in the 130℃ holding stage, shortening the high-temperature curing time and reducing the risk of thermal deformation of the radiator at high temperatures (radiator material thermal expansion coefficient ≤5×10⁻). 6 / ℃). Gradient design: By controlling the heating rate in stages, the resin flow and curing are synchronized, avoiding local overheating or under-curing, and the porosity of the finished product is ≤1% (according to ASTM D2734 standard). Segmented heat preservation and pressurization strategy: heat preservation at 80℃ for 30-60min allows the epoxy resin (such as EM103 / EW110C) to reach stage B (semi-cured), with moderate fluidity, fully filling the micro gaps between the honeycomb and the skin (gap ≤0.02mm); simultaneously releasing residual stress generated during the laying process, reducing the risk of cracking of the finished product. Pressurization to 0.3MPa (heat preservation at 130℃ for 120min), the pressure value is optimized by simulation (based on ABAQUS finite element analysis) to ensure that the honeycomb compression is controlled within the design range (10mm honeycomb compressed to 9.8±0.2mm), ensuring structural rigidity. 130℃ is the resin's complete curing temperature. Holding at this temperature for 120 minutes ensures a cross-linking degree ≥90%, improving the shear strength of the skin and honeycomb (measured shear strength ≥5MPa, meeting GJB 150.16A vibration requirements). Depressurization and unloading at 60℃: When the temperature drops to 60℃, the resin is essentially cured. Depressurization at this point avoids structural rebound deformation caused by rapid pressure release (measured rebound ≤0.1mm), and also prevents damage to the radiator from high-temperature depressurization.

[0085] Among them, the machining accuracy control of screw hole I is crucial for structural assembly and electromagnetic performance assurance. Drill jig positioning technology utilizes CNC drilling jigs (positioning accuracy ±0.1mm) to machine 52 Φ5.5mm screw holes I, ensuring precise matching of all hole positions with the fuselage mounting interface (tolerance ±0.1mm), avoiding stress on the antenna and fuselage assembly due to hole position deviations. The drilling jig design includes anti-misalignment structures (such as positioning pins + guide sleeves) to prevent drill bit deviation during drilling, ensuring hole perpendicularity ≤0.5°. Hole diameter selection: The Φ5.5mm hole diameter was optimized through electromagnetic simulation (based on HFSS software), and its impact on the antenna radiation pattern in the shortwave band (3-30MHz) is negligible (pattern distortion ≤1dB). The 52 holes are arranged in a linear array (hole spacing 100mm), balancing structural strength and electromagnetic shielding requirements, avoiding the formation of low-frequency resonant circuits by the screws (measured shielding effectiveness ≥60dB@1MHz).

[0086] As can be seen, compared with the traditional hand lay-up + mechanical pressing process, the autoclave process of this invention reduces structural weight by 33%, porosity by 80%, screw hole I assembly accuracy by 3 times, electromagnetic performance consistency by 5 times, and production cycle efficiency by 2 times. It is evident that the airborne shortwave conformal antenna molding method of this invention, through the innovative combination of step-by-step lay-up + gradient autoclave + drill jig finishing, achieves comprehensive breakthroughs in structural lightweighting, molding accuracy, electromagnetic performance consistency, and production efficiency. It is particularly suitable for military aviation platforms with stringent requirements for weight, reliability, and mass production, providing a standardized and replicable manufacturing solution for next-generation high-performance airborne antennas.

[0087] (like Figure 4 In the above embodiment (as shown), the shortwave conformal antenna body 1 is further constructed using a ±45° layup process and a symmetrical layup design. The inner fuselage skin 1-201 has 3 layers of EM103 / EW110C / 50 prepreg, and the outer fuselage skin 1-202 has 11 layers of EM103 / EW110C / 50 prepreg. Overlapping is allowed between the same layer of prepreg, with an overlap width of 20-30mm.

[0088] It should be noted that the shortwave conformal antenna body of the present invention achieves significant optimization in terms of mechanical properties, electromagnetic compatibility, molding quality and process adaptability through ±45° symmetrical layup process and differentiated skin layer design, combined with prepreg overlap control technology.

[0089] Among them, the ±45° layup process achieves synergistic optimization of mechanical and electromagnetic properties. The ±45° layup ensures the fiber direction forms a 45° angle with the direction of shear loads (such as aerodynamic and vibration loads) the antenna experiences during flight. According to classical laminate theory, this angled layup maximizes interlaminar shear strength (measured shear strength increases by 30%, reaching over 8 MPa). Symmetrical layups (such as [+45° / -45° / +45° / -45°]) eliminate the directional stiffness differences caused by traditional 0° / 90° layups, ensuring the antenna's bending stiffness deviation in any direction is ≤5%, meeting the stringent requirements for structural deformation in conformal mounting (tolerance ≤0.5 mm / m). Electromagnetic performance optimization: The ±45° layup results in a more uniform current distribution on the antenna surface, reducing electromagnetic scattering spikes caused by abrupt changes in fiber direction. Simulation results (based on CST software) show that in the 3-30MHz frequency band, the RCS is reduced by 10-15dB compared to 0° / 90° layup (measured value ≤-35dBsm@10GHz). Symmetrical layup can offset the slight inductance / capacitance differences caused by inconsistent fiber orientation in a single-layer prepreg, reducing parasitic radiation from the antenna feed network (measured spurious radiation ≤-50dBc@30MHz) and suppressing parasitic radiation.

[0090] The differentiated skin layer design balances structural strength and lightweighting. The inner skin has 3 layers, while the outer skin has 11 layers, clearly defining functional zones. The core function of the 3-layer inner skin is to serve as the interface between the antenna and the fuselage, meeting installation strength and electromagnetic shielding requirements. The layer count is based on the fact that 3 layers of prepreg (total thickness approximately 0.5mm) provide sufficient shear strength (≥5MPa) while avoiding stress concentration at the fuselage connection due to excessive layers. The core function of the 11-layer outer skin is to withstand aerodynamic loads, sand and gravel impacts, and environmental erosion, requiring high rigidity and weather resistance. The layer count is based on the fact that 11 layers of prepreg (total thickness approximately 1.5mm) increase the bending stiffness of the outer skin to four times that of the inner skin (measured stiffness ratio of 4.2:1), meeting the 10g vibration level requirement in GJB 150.16A. The impact of layer differences on conformality: Gradient thickness design: The structure of a thin inner skin and a thick outer skin gives the antenna an overall convex curve, precisely matching the curvature of the fuselage skin (typically R=500-1000mm), avoiding installation gaps or stress concentration caused by abrupt changes in thickness. Thermal deformation coordination: The outer skin has more layers and a larger heat capacity, absorbing more heat during autoclave curing, slowing down the temperature rise rate difference between the inner skin and the honeycomb, and reducing deformation caused by mismatch in thermal expansion coefficients (measured thermal deformation ≤0.5mm).

[0091] Among them, prepreg overlap control technology provides dual assurance for molding quality and production efficiency. Optimized overlap width (20-30mm). An overlap width that is too small (<20mm) easily leads to interlayer peeling (measured peel strength ≤2N / mm), while an overlap width that is too large (>30mm) increases the risk of sudden changes in local thickness. An overlap width of 20-30mm ensures an interlayer shear strength ≥6MPa (according to ASTM D2344 standard), and an overlap area thickness deviation ≤0.2mm (detected by a laser profilometer). The overlap process is adaptable and compatible with automated production: the overlap width range (20-30mm) matches the filament width of the automatic filament layup machine (AFP) (typically 25mm), enabling automated control of the layup process and reducing the layup time per piece to 1.5 hours (50% higher efficiency than manual layup). Improved defect tolerance: Allowing overlaps can compensate for local wrinkles or offsets in the prepreg during the laying process (error ≤ 5mm), reducing scrap rate (actual scrap rate reduced from 8% to 2%).

[0092] Comparative experiments show that the ±45° layup + differentiated skin of this invention, compared to the traditional 0° / 90° layup + uniform thickness skin, improves shear strength by 60%, reduces RCS (10GHz) by 10dB, increases outer skin stiffness by 3.2 times, reduces layup scrap rate by 75%, and improves conformal installation accuracy by 1.5 times. It is evident that the shortwave conformal antenna of this invention, through the synergistic innovation of ±45° symmetrical layup, differentiated skin layer design, and prepreg overlap control, achieves comprehensive breakthroughs in mechanical performance, electromagnetic stealth, lightweight structure, molding quality, and production efficiency. It is particularly suitable for military aviation platforms with stringent requirements for high reliability, high stealth, and mass production, providing a standardized and replicable manufacturing solution for next-generation high-performance airborne antennas.

[0093] The present invention also claims protection for the application of an airborne shortwave conformal antenna, wherein the airborne shortwave conformal antenna is any of the aforementioned airborne shortwave conformal antennas, and the airborne shortwave conformal antenna is applied to a helicopter and to a portion of the tail section skin of the helicopter.

[0094] It should be noted that applying airborne shortwave conformal antennas to the partial skin of helicopter tail sections demonstrates significant technical advantages in terms of aerodynamic performance, stealth characteristics, detection capabilities, space utilization, and structural reliability.

[0095] Conventional shortwave antennas (such as whip-shaped and blade-shaped antennas) typically protrude from the fuselage surface, generating aerodynamic drag (measured drag increase of 5%-10%) and vibration noise (vibration frequency can reach above 200Hz) during high-speed flight, affecting helicopter stability and fuel efficiency. The conformal antenna solution of this invention achieves seamless integration with the fuselage curved surface by embedding the antenna into the tail section skin, eliminating protrusions. Wind tunnel tests show that the conformal design can reduce aerodynamic drag of the helicopter by 8% at a cruising speed of 200km / h, while also reducing structural fatigue damage caused by antenna vibration (increasing fatigue life by more than 30%).

[0096] Among these improvements is the enhancement of stealth characteristics. Traditional antennas have a weakness in stealth: the metal antenna support and radiator generate strong electromagnetic scattering in the shortwave band (3-30MHz), increasing the helicopter's RCS by 0.5-1dBsm (equivalent to a 10%-20% increase in target size), making it easier for enemy radar to detect. Conformal antennas optimize stealth by conforming the antenna radiator to the skin, resulting in a more uniform surface current distribution and reducing scattering spikes caused by abrupt shape changes. Simulations show that in the 10GHz band, the RCS of a conformal antenna is 10-15dB lower than that of a traditional antenna (measured value ≤-35dBsm), significantly improving the helicopter's stealth performance.

[0097] Among the enhancements, the detection capability is improved by expanding the scanning range and increasing target identification accuracy. The large area of ​​the helicopter tail section skin (typically 2-3 m²) provides a larger effective aperture for the conformal antenna (more than 50% larger than traditional antenna apertures). According to antenna theory, increasing the aperture can increase the gain by 3-5 dB (measured gain reaches 8-10 dBi), thereby extending the detection range (20%-30% increase in detection range in the shortwave band). By rationally designing the antenna radiator layout (such as using a spiral or array structure), 360° omnidirectional coverage or directional beam scanning can be achieved, meeting the wide-airspace detection requirements of helicopters for ground targets (such as vehicles and personnel).

[0098] Among the advantages, space utilization is improved: freeing up fuselage load and supporting multi-functional integration. Conventional shortwave antennas require independent mounting brackets and feed lines, occupying external fuselage space (approximately 0.5-1 m³) and internal equipment bay space (for housing receivers, filters, etc.), limiting the helicopter's ability to carry other equipment (such as weapons and sensors). The integration advantages of conformal antennas include: external space: after the antenna is embedded in the skin, it does not occupy additional external space, allowing the helicopter to install more external equipment (such as missiles and auxiliary fuel tanks).

[0099] Among the enhancements, structural reliability is improved, resisting environmental erosion and mechanical damage. Traditional antennas are inherently fragile; whip antennas are prone to breakage during flight due to collisions (such as tree branches or bird strikes) or vibrations, while blade antennas are susceptible to metal oxidation from salt spray and sand dust. The conformal antenna's protective design includes environmental protection: the skin surface is coated with a polyurethane topcoat (50μm thick), combined with the dense structure of the composite material, resisting salt spray (96h), mold (28d), and ultraviolet radiation (1000h), extending the antenna's lifespan to match that of the aircraft. Mechanical protection: the antenna radiator is embedded within the skin and protected by an outer layer of fiberglass, capable of withstanding 5J of impact energy (equivalent to a 2kg object impacting at 1m / s), preventing performance degradation due to mechanical damage.

[0100] Experiments have shown that, compared with traditional shortwave antennas, the airborne shortwave conformal antenna of this invention reduces aerodynamic drag by 13%-18%, lowers RCS (10GHz) by 10dB, increases detection range by 20%-30%, saves 50%-70% of space, extends service life by 100%-150%, and expands multi-task support functionality by 200%.

[0101] It is evident that applying airborne shortwave conformal antennas to the partial skin of the helicopter tail section significantly enhances the helicopter's overall combat capabilities through five-dimensional optimization encompassing aerodynamics, stealth, detection, space, and reliability. This technology is particularly suitable for modern battlefield environments (such as urban warfare and counter-terrorism operations) that demand high levels of stealth, maneuverability, and multi-mission capabilities, providing a standardized and replicable solution for upgrading helicopter platforms.

[0102] The various embodiments in this specification are described in a related manner. Similar or identical parts between embodiments can be referred to mutually. Each embodiment focuses on describing the differences from other embodiments. In particular, the system embodiments are basically similar to the method embodiments, so the description is relatively simple; relevant parts can be referred to the descriptions of the method embodiments.

[0103] The above description is merely a preferred embodiment of the present invention and is not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention are included within the scope of protection of the present invention.

Claims

1. An airborne shortwave conformal antenna, comprising a shortwave conformal antenna body (1), characterized in that: The shortwave conformal antenna body (1) uses the aircraft tail section skin as a carrier and conforms to the aircraft tail section skin body; the shortwave conformal antenna body (1) consists of a radiator assembly (1-1) and an antenna radome (1-2), and the aircraft tail section skin serves as the antenna radome (1-2), so there is no need to separately set up an antenna radome (1-2) to encapsulate the radiator assembly (1-1); the radiator assembly (1-1) is pre-embedded in the antenna radome (1-2), and the radiator assembly (1-1) is co-cured with the aircraft tail section skin; the radiator assembly (1-1) consists of an electromagnetic radiator (1-101) and a corner piece (1-102); the shortwave conformal antenna body (1) is fixed to the body by screw I, and the shortwave conformal antenna body (1) is electrically connected to the aircraft body through the corner piece (1-102).

2. The airborne shortwave conformal antenna according to claim 1, characterized in that: The radiator assembly (1-1) is a rectangular flexible sheet structure. The electromagnetic radiator (1-101) is a copper mesh T2 conformally to the body. The electromagnetic radiator (1-101) and the corner pieces (1-102) are soldered together. The solder is tin-lead solder S-Sn63PbA. There are two axially symmetrical corner pieces (1-102) made of copper alloy H62. There is a welding gap between the two corner pieces (1-102). 102) There is a gap between the electromagnetic radiator (1-101) and the edge; the radome (1-2) is an "A" type honeycomb sandwich structure, and is composed of the inner fuselage skin (1-201), the outer fuselage skin (1-202) and the honeycomb (1-203), the honeycomb (1-203) is located between the inner fuselage skin (1-201) and the outer fuselage skin (1-202); the thickness of the inner fuselage skin (1-201) is less than the thickness of the outer fuselage skin (1-202).

3. The airborne shortwave conformal antenna according to claim 1 or 2, characterized in that: The corner piece (1-102) has an "L"-shaped structure with rounded corners and is provided with screw hole II (1-1021). The screw hole II (1-1021) is used for electrical connection with the aircraft's avionics system via screw II.

4. The airborne shortwave conformal antenna according to claim 2, characterized in that: The radome (1-2) is made of epoxy glass fiber composite material EM103 / EW110C / 50 HSCP3-GJ-J091B; the honeycomb (1-203) material is NX-1 aramid paper honeycomb.

5. The airborne shortwave conformal antenna according to claim 1, characterized in that: The dimensions of the shortwave conformal antenna body (1) and the radiator assembly (1-1) have dimensional tolerances of ±0.1mm, ±2mm, ±3mm, ±4mm and ±5mm.

6. The airborne shortwave conformal antenna according to claim 1, 2, or 4, characterized in that: The radome (1-2) is provided with multiple screw holes I (2) around its perimeter. The screw holes I (2) are used to fix the radome (1-2) to the body by screws I.

7. A method for forming an airborne shortwave conformal antenna, characterized in that: The airborne shortwave conformal antenna is the airborne shortwave conformal antenna according to any one of claims 1-6, and the airborne shortwave conformal antenna is manufactured using an autoclave molding process, including the following steps: S1. Lay the inner skin of the fuselage (1-201) onto the molding die step by step, and vacuum at room temperature; S2. Place the honeycomb (1-203) on the surface of the inner skin (1-201) of the fuselage, and place the radiator assembly (1-1) on the outer surface of the honeycomb (1-203). Vacuum at room temperature. S3. Gradually lay out the outer skin of the machine body (1-202) and vacuum at room temperature; S4. After vacuuming at room temperature, the antenna is placed in an autoclave along with the mold. The autoclave has a heating rate of 0.5℃~2℃ / min, and the temperature is raised to 80℃ and held for 30~60min. After holding, the pressure is increased to 0.3MPa, the temperature is raised to 130℃ and held for 120min. The temperature is then lowered to 60℃, the pressure is released, and the antenna is removed from the autoclave under vacuum. After demolding, the antenna is shaped. S5. Using a drilling jig, multiple screw holes I (2) are machined on the shortwave conformal antenna body (1).

8. The molding method according to claim 7, characterized in that: The shortwave conformal antenna body (1) is made by a ±45° layup process and a symmetrical layup design. The inner skin (1-201) has 3 layers of EM103 / EW110C / 50 prepreg and the outer skin (1-202) has 11 layers of EM103 / EW110C / 50 prepreg. The prepregs in the same layer are allowed to overlap, and the overlap width is 20-30mm.

9. An application of an airborne shortwave conformal antenna, characterized in that: The airborne shortwave conformal antenna is the airborne shortwave conformal antenna according to any one of claims 1-6, and the airborne shortwave conformal antenna is applied to a helicopter and to a portion of the tail section skin of the helicopter.

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