CN115911856A - Shape-preserving skin radar structure based on radio frequency microsystem - Google Patents

Abstract

The invention relates to the technical field of radio frequency detection and aircraft skin, and discloses a conformal skin radar structure based on a radio frequency micro-system. The special-shaped outer electromagnetic wave-transmitting protective skin and the special-shaped array surface based on the radio frequency micro-system are integrally designed, on the basis of ensuring the electrical property, the shape-preserving design of the special-shaped outer electromagnetic wave-transmitting protective skin and the airplane skin is realized, the installation position of radar equipment on an airplane platform is expanded, and the special-shaped outer electromagnetic wave-transmitting protective skin is simple and compact in structure, light in weight, easy to process and low in manufacturing cost; and through the arrangement of the filling part, the electromagnetic performance of the special-shaped combined array surface is improved while the installation stability of the shape-preserving covering and the special-shaped array surface is ensured.

Description

Shape-preserving skin radar structure based on radio frequency microsystem

Technical Field

The invention relates to the technical field of radio frequency detection and aircraft skin, in particular to a conformal skin radar structure based on a radio frequency microsystem.

Background

The technical development of the radio frequency micro system pushes the radio frequency sensor to develop towards miniaturization and modularization, and the sensor and the surface of the machine body are conformal and can bear load and develop into the key point and the difficulty point of the current research facing to the detection requirement of the intelligent skin under the distributed full-machine layout of the future operation platform.

Through published documents and data research, the so-called conformal radio frequency sensor and the body only involves the fusion of an antenna radiation layer (passive part) which is a few millimeters outermost of the sensor and the body, and the T/R component, the radio frequency conversion, the digital processing and the like are not included. However, under the constraint of development of chips, materials and integrated circuits, the current radio frequency/digital hybrid circuit under the background of airborne application cannot achieve skin and flexibility, and the current advanced light and thin radar is generally formed by splicing and arraying radio frequency microsystem modules which are standardized, modularized and planar and have the thickness of tens of millimeters according to needs, and can only meet the requirement of assembling a skin covering cover of a plane body, such as the positions of the side surface of a nose of a stealth fighter plane and the like, so that the application range and the layout position of the stealth fighter plane are greatly limited.

Disclosure of Invention

In view of the above, the invention provides a conformal skin radar structure based on a radio frequency micro-system, so as to realize an integrated special-shaped structure of a conformal skin and a planar radar array, and solve a series of problems of pneumatic shape preservation, strength/heat protection, electromagnetic wave transmission, inter-array mutual coupling inhibition and the like of an ultrathin combined array.

A conformal skin radar structure based on a radio frequency micro-system comprises a plurality of planar arrays based on the radio frequency micro-system, wherein the planar arrays are subjected to skinning assembly between the arrays according to the curvature requirement of the skin of an airplane to form a special-shaped array surface; a shape-preserving skin is attached to the surface of the special-shaped array surface and comprises an outer electromagnetic wave-transparent protective skin, a filling part is arranged on one side surface, attached to the special-shaped array surface, of the protective skin, and the filling part is inserted into a splicing seam between adjacent planar arrays.

Further, the protective skin and the filling part of the conformal skin are fixed at the contact part of the irregular array surface or the splicing seam by adopting electromagnetic glue.

Furthermore, the protective skin is subjected to semi-curing and pressing by a single layer or multiple layers of high-frequency microwave dielectric materials through electromagnetic glue and is attached to the aircraft skin in a conformal mode.

Further, the filling part is made of a high-frequency microwave dielectric material.

Further, the filling part is of an inverted sawtooth structure.

Further, smoothing treatment is carried out on the protective skin and the binding surface.

Compared with the prior art, the invention has the beneficial effects that:

1. the conformal skin radar structure based on the radio frequency microsystem can realize conformal bearing of the radio frequency sensor and the fuselage skin in a compact space, and solves the problem of high symbiosis conformal shape of the physical fuselage skin and the electromagnetic sensor skin in an airborne environment.

2. The array has good electromagnetic performance, firstly, the multilayer medium on the surface of the array loads an external electromagnetic wave-transparent protective skin, and the array also has good wave-transparent performance in a microwave band besides the protective characteristic, and better electromagnetic matching is obtained through the optimized design of the multilayer medium, so that lower loss is realized; in addition, the mutual coupling effect between the arrays is effectively inhibited by filling the inverted sawtooth medium below the splicing seams of the cavities between the arrays, and compared with the condition without the inverted sawtooth medium, the antenna side lobe is improved by about 4-5 dB.

3. The combined array surface based on the radio frequency micro-system multi-ultrathin radar is conformal to the skin of the airplane.

4. Good maintainability can adopt semi-solid pressfitting technology, and multilayer high frequency microwave dielectric material has advantages such as easily tailorring, concatenation are convenient, later stage dismouting is maintained simply.

5. The special-shaped electromagnetic function conformal skin radar structure can meet multiple requirements of safety, protectiveness, skin property, conductivity, reliability, concealment and the like, really realizes integration of a mechanical structure and an electromagnetic function, can be applied to the requirements of various combat platforms such as fighters, transporters and early warning machines on a radio frequency micro-system-based special-shaped array radar, and has wide practical value and application prospect.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.

FIG. 1 is a schematic diagram of an embodiment of a conformal skin installation based on a radio frequency microsystem;

FIG. 2 is a schematic structural diagram of a protective skin and a filling part in the embodiment;

FIG. 3 is a schematic diagram illustrating a multi-layer dielectric material and a pre-cured press-fit of a special-shaped array surface in an embodiment;

FIG. 4 is a direction diagram of the irregular wavefront H =60mm and L =15mm in the embodiment;

FIG. 5 is a covered conformal skin pattern with a wavefront H =60mm and a wavefront L =15mm in an embodiment;

wherein, 1, planar array; 2. a protective skin; 3. a filling section; 4. and (6) splicing seams.

Detailed Description

The embodiments of the present application will be described in detail below with reference to the accompanying drawings.

The following description of the embodiments of the present application is provided by way of specific examples, and other advantages and effects of the present application will be readily apparent to those skilled in the art from the disclosure herein. It should be apparent that the described embodiments are only a few embodiments of the present application, and not all embodiments. The present application is capable of other and different embodiments and its several details are capable of modifications and/or changes in various respects, all without departing from the spirit of the present application. It should be noted that the features in the following embodiments and examples may be combined with each other without conflict. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments in the present application without making any creative effort belong to the protection scope of the present application.

Examples

Referring to fig. 1-5, a conformal skin radar structure based on a radio frequency micro-system comprises a plurality of planar arrays 1 based on the radio frequency micro-system, wherein the planar arrays 1 are subjected to skinning assembly between the arrays according to the curvature requirement of the aircraft skin to form a special-shaped array surface; the special-shaped array surface is provided with a shape-preserving skin in an attached mode, the shape-preserving skin comprises an outer electromagnetic wave-transparent protective skin 2, a filling part 3 is arranged on one side face, attached to the special-shaped array surface, of the protective skin 2, and the filling part 3 is inserted into a splicing seam 4 between adjacent planar arrays 1.

In order to meet the design requirements of onboard skin shape preservation and the like, a splicing seam 4 must exist between the planar array 1 with a certain thickness in the special-shaped array surface and the adjacent planar array 1, so that the aerodynamic and radar antenna radiation characteristics and the like of the airplane are seriously influenced. In the embodiment, the protection skin 2 with wave transmission and protection is attached to the surface of the special-shaped array surface, and the filling part 3 is adopted to fill the splicing seam 4 between the adjacent planar arrays 1, so that the integrated special-shaped structure of the shape-preserving skin and the planar radar array is realized, and a series of problems of pneumatic shape preservation, strength/heat protection, electromagnetic wave transmission, mutual coupling inhibition between arrays and the like of the ultrathin combined array are solved.

The special-shaped array surface in the embodiment is composed of standardized, modularized and generalized radio frequency microsystems, and each radio frequency microsystem comprises a radiation layer, a TR layer, a heat dissipation layer, a radio frequency conversion layer, a digital processing layer, a cover plate layer and the like.

As shown in fig. 2, which illustrates a structure of the conformal skin based on the radio frequency micro-system in this embodiment, the conformal skin includes an outer electromagnetic wave-transparent protective skin 2, which is mainly manufactured by a semi-curing and laminating process of multiple layers of high-frequency microwave dielectric materials through electromagnetic glue, and the bonding surface of the protective skin 2 and the special-shaped array surface is smoothed to realize a conformal design with the aircraft skin.

Referring to fig. 3, the protective skin 2 can be covered by two or three layers of high-frequency microwave dielectric materials according to the shape of the airplane and the mounting structure of the special-shaped array surface, and the protective skin 2 is covered by multiple layers of dielectric materials, so that the maintainability and the mounting convenience of the array surface based on the radio frequency micro system are ensured, and the volume and the weight of the radar structure are reduced. After the special-shaped array surface is installed and fixed, a semi-curing pressing process is adopted, the protective skin 2 and the filling part 3 of the shape-preserving skin are bonded and fixed at the contact part with the special-shaped array surface or the splicing seam 4 by using electromagnetic glue, and the shape-preserving skin is ensured to be bonded and fastened with the special-shaped array surface. For a large fixed-wing aircraft platform with low flying speed, the special-shaped outer electromagnetic wave-transparent protective skin 2 can effectively meet the design constraint condition of the aircraft outer skin. For an aircraft platform with the flight speed of 2-3 Mach, when the aircraft flies in dense atmosphere, the temperature of the aircraft skin rises to about 300 ℃ at most along with the continuous rise of the flight speed under the influence of the heating of high-temperature compressed gas between the shock wave and the aircraft body and the strong friction between the surface of the aircraft body and the air, and the special-shaped outer electromagnetic wave-transmitting protective skin 2 can meet the long-term use requirement under the condition of 300 ℃ through reasonable design and effectively ensures the shape preservation and the stability of the shape-preserving skin.

The filling part 3 is a lug which can be inserted into the splicing seam 4 between the adjacent planar arrays 1, and the cross section of the lug can be cylindrical or semi-cylindrical, triangular, rectangular, trapezoidal and the like. The filling part 3 in the embodiment selects the inverted sawtooth structure which can completely fill the splicing seam 4 between the adjacent planar arrays 1, the inverted sawtooth structure part is spliced by semi-curing and laminating and bonding modes through coating electromagnetic glue among multiple layers of high-frequency microwave dielectric materials according to the thickness H of the special-shaped array surface module and the length L of the splicing seam 4, and the special-shaped array surface shape structure is used for cutting to prepare one or more groups of inverted sawtooth structures.

The protective skin 2 and the filling part 3 are made of high-frequency microwave dielectric materials which are the same as the surface of the antenna radiation layer, and have the characteristics of low dielectric constant, high elastic modulus, low loss tangent angle and the like, and the single-layer thickness is usually several millimeters. In the embodiment, the single-layer high-frequency microwave dielectric material is uniformly processed and prepared into a pure dielectric material with the thickness of 4mm and double surfaces not covered with metal, the dielectric material has the characteristics of good environmental adaptability, heat resistance, corrosion resistance, easiness in multi-layer splicing, easiness in cutting, easiness in bending and the like, and the mechanical property of the dielectric material is ensured while the requirement on the electromagnetic property is met.

Fig. 4 is a direction diagram when the irregular wavefront H =60mm and L =15mm without the protective skin 2, and fig. 5 is a covered conformal skin direction diagram when the irregular wavefront H =60mm and L =15 mm; comparing the two figures, the covering conformal skin can effectively inhibit the mutual coupling effect between the arrays and improve the antenna side lobe by about 4-5 dB.

The conformal skin radar structure based on the radio frequency micro-system is designed in an integrated mode by utilizing the special-shaped outer electromagnetic wave-transparent protective skin 2 and the special-shaped array surface based on the radio frequency micro-system, and the conformal design with the aircraft skin is realized on the basis of ensuring the electrical performance. The protective skin 2 and the filling part 3 can be synthesized into a multilayer dielectric material by adopting an electromagnetic glue prepreg lamination manufacturing process, can be cut, spliced and combined according to the array surface structure, and are connected with the outer electromagnetic wave-transparent protective skin 2 and the special-shaped array surface by adopting an electromagnetic glue prepreg lamination process, so that the electromagnetic wave-transparent protective skin has the characteristics of easiness in assembly and disassembly, convenience in maintenance and the like. Through medium capping, the conformal skin can effectively improve the directivity coefficient.

In conclusion, the conformal skin radar structure based on the radio frequency micro-system can realize conformal radar structure design on various airplane platforms, expands the installation positions of radar equipment on the airplane platforms, and has the advantages of simple and compact structure, light weight, easy processing and low manufacturing cost; and through the arrangement of the filling part 3, the electromagnetic performance of the special-shaped combined array surface is improved while the installation stability of the shape-preserving covering and the special-shaped array surface is ensured, and the method has high engineering application value.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims (6)

1. A conformal skin radar structure based on a radio frequency micro-system is characterized by comprising a plurality of planar arrays based on the radio frequency micro-system, wherein the planar arrays are subjected to skinning assembly between the arrays according to the curvature requirement of the aircraft skin to form a special-shaped array surface; the special-shaped array surface is provided with a conformal skin in an attached mode, the conformal skin comprises an external electromagnetic wave-transparent protective skin, a filling part is arranged on one side face, attached to the special-shaped array surface, of the protective skin, and the filling part is inserted into a splicing seam between adjacent planar arrays.

2. The radio frequency microsystem-based conformal skin radar configuration as claimed in claim 1, wherein the protective skin and the filling portion of the conformal skin are fixed by electromagnetic glue at a contact position with the irregular array surface or the splicing seam.

3. The radio frequency microsystem-based conformal skin radar configuration as claimed in claim 1, wherein the protective skin is formed by a single layer or multiple layers of high frequency microwave dielectric material through semi-curing and pressing by electromagnetic glue and is attached to the aircraft skin in a conformal mode.

4. The radio frequency microsystem based conformal skin radar configuration of claim 1, wherein the filler portion is made of a high frequency microwave dielectric material.

5. The radio frequency microsystem-based conformal skin radar configuration of claim 1, wherein the filling portion is of an inverted sawtooth structure.

6. The radio frequency microsystem-based conformal skin radar configuration of claim 1, wherein the protective skin and the faying surface are smoothed.

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