KR20150006736A - Method for testing and evaluating for smart skin - Google Patents

Method for testing and evaluating for smart skin Download PDF

Info

Publication number
KR20150006736A
KR20150006736A KR20130080559A KR20130080559A KR20150006736A KR 20150006736 A KR20150006736 A KR 20150006736A KR 20130080559 A KR20130080559 A KR 20130080559A KR 20130080559 A KR20130080559 A KR 20130080559A KR 20150006736 A KR20150006736 A KR 20150006736A
Authority
KR
South Korea
Prior art keywords
test
smart skin
antenna
confirming
strength
Prior art date
Application number
KR20130080559A
Other languages
Korean (ko)
Inventor
김민성
박찬익
전승문
Original Assignee
국방과학연구소
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 국방과학연구소 filed Critical 국방과학연구소
Priority to KR20130080559A priority Critical patent/KR20150006736A/en
Publication of KR20150006736A publication Critical patent/KR20150006736A/en

Links

Images

Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
    • G01D21/00—Measuring or testing not otherwise provided for
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N3/20—Investigating strength properties of solid materials by application of mechanical stress by applying steady bending forces
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N3/24—Investigating strength properties of solid materials by application of mechanical stress by applying steady shearing forces
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N3/30—Investigating strength properties of solid materials by application of mechanical stress by applying a single impulsive force, e.g. by falling weight
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N3/32—Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
    • G01R29/00—Arrangements for measuring or indicating electric quantities not covered by groups G01R19/00 - G01R27/00
    • G01R29/08—Measuring electromagnetic field characteristics
    • G01R29/10—Radiation diagrams of antennas

Landscapes

  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Health & Medical Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Chemical & Material Sciences (AREA)
  • Analytical Chemistry (AREA)
  • Biochemistry (AREA)
  • General Health & Medical Sciences (AREA)
  • Immunology (AREA)
  • Pathology (AREA)
  • Electromagnetism (AREA)
  • Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)

Abstract

The smart skin test evaluation method according to an exemplary embodiment of the present invention is a method of evaluating structural strength of an aircraft body and an antenna performance test that verifies whether the smart skin satisfies structural requirements and antenna requirements of an antenna function Wherein the structural strength test includes a tensile load test for confirming the tensile strength of the smart skin, a shear load test for confirming the shear strength of the smart skin, a bending load for confirming the bending strength of the smart skin A fatigue load test for confirming the fatigue strength of the smart skin, a structural deformation antenna test for confirming antenna performance at a structural deformation, and an impact load test for confirming the impact strength of the smart skin.

Description

[0001] METHOD FOR TESTING AND EVALUATING FOR SMART SKIN [0002]

One embodiment of the present invention relates to a test evaluation method applicable to the development of a smart skin structure that forms the appearance of an aircraft.

Several protruding antennas in the aircraft have disadvantages that increase the radar cross section (RCS). If necessary, additional protruding antennas are required to be attached during design, and design changes May become inevitable, and this may result in an extension of the development period. To solve this problem, the smart skin is an antenna that is inserted with the same surface as the airframe.

The smart skin is integrally formed on the exterior of the aircraft and has the advantage of reducing the laser detection area because there is no protruding part. Despite these advantages, there is a manufacturing problem in that the antenna material deforms at the curing temperature of the composite material constituting the smart skin. Also, the carbon fiber reinforced composite material used for supporting the external load has a problem that the antenna performance is degraded as a whole because the RF signal can not be blocked unlike the metal material used in the conventional antenna.

Since SmartSkin must perform both the structural role and the antenna role simultaneously, two functions must be evaluated at the same time in development. In addition, it is necessary to confirm the change of the antenna function after supporting the structural load to the limit point. You should check if there is a change in the function of the antenna when there is strain due to the structural load. All these functional tests must be carried out with one specimen.

On the other hand, a fixture capable of adding loads to deform the antenna is required, and a fixture is usually made of a metal material so that a load can be added to the specimen without deforming the fixture with a minimum weight. However, in the case of smart skins, metallic jig affects antenna performance, so metallic materials can not be used as jig.

In addition, the number of specimens is limited due to the size of the budget in general research projects, and it is difficult to carry out the test and the electromagnetic wave test for five or more structural loads with limited one or two specimens.

It is an object of the present invention to provide a smart skin test evaluation method for confirming whether antenna performance can be properly performed.

According to another aspect of the present invention, there is provided a method of evaluating a smart skin test according to an embodiment of the present invention, And a structural strength test for verifying whether or not the smart skin satisfies the condition, wherein the structural strength test includes a tensile load test for confirming the tensile strength of the smart skin, a shear load test for confirming the shear strength of the smart skin, A bending load test for confirming the bending strength of the smart skin, a fatigue load test for confirming the fatigue strength of the smart skin, a structural deformation antenna test for confirming the antenna performance at the time of structural deformation, and the impact strength of the smart skin Lt; RTI ID = 0.0 > and / or < / RTI >

According to one embodiment of the present invention, the antenna performance test is performed after each of the above structural strength tests.

According to one embodiment of the present invention, the impact load test is performed on a separate smart skin.

According to an embodiment of the present invention, the antenna performance test may use at least one of a gain in a smart skin, a voltage standing wave ratio (VSWR), and a radiation pattern using a signal sent from a reference antenna The performance is judged by measurement.

According to one embodiment of the present invention, the antenna performance test is conducted in an anechoic chamber.

According to one embodiment of the present invention, the structural deformation antenna test is performed by measuring a signal level emitted from an originating antenna spaced from a smart skin according to a variation of the smart skin.

According to an embodiment of the present invention, the smart skin includes a radome dome exposed to the outside and having a glass fiber composite material and a metal mesh formed to cover the glass fiber composite material; A support portion coupled to an inner surface of the radar dome portion; And an antenna disposed between the radar dome portion and the support portion, wherein the radar dome portion is formed to have the same curvature as the surface of the aircraft body so as to reduce a radar detection area.

According to one embodiment of the present invention, the support portion is formed by sequentially laminating a honeycomb core, a first metal mesh, a glass fiber composite material, and a second metal mesh.

The smart skin associated with at least one embodiment of the invention configured as described above may be tested for both an antenna function and a structural function.

In addition, such a smart skin test evaluation method can be performed efficiently and economically using the minimum number of test specimens.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a conceptual view showing a skins of an aircraft according to the present invention. FIG.
2 is a rear perspective view of a smart skin associated with an embodiment of the present invention.
3 is an exploded perspective view showing an embodiment of a smart skin having an antenna according to an embodiment of the present invention.
4 is a flow chart illustrating a test and evaluation procedure for the requirements of the present invention;
FIG. 5 is a conceptual view of a test in which a smart skin according to an embodiment of the present invention is fastened to a tensile load test fixture. FIG.
FIG. 6 is a conceptual view of a test in which a smart skin according to an embodiment of the present invention is fastened to a shear load test fixture. FIG.
FIG. 7 is a conceptual view of a test in which a smart skin according to an embodiment of the present invention is fastened to a bending load test fixture. FIG.
FIG. 8 is a conceptual view illustrating a test result obtained by fastening a smart skin to an impact load test fixture according to an embodiment of the present invention. FIG.

Hereinafter, a smart skin test evaluation method according to the present invention will be described in detail with reference to the drawings. The suffix "module" and " part "for the components used in the following description are given or mixed in consideration of ease of specification, and do not have their own meaning or role. In the present specification, the same or similar reference numerals are given to different embodiments in the same or similar configurations. As used herein, the singular forms "a", "an" and "the" include plural referents unless the context clearly dictates otherwise.

FIG. 1 is a conceptual view showing an aircraft skin according to the present invention, and FIG. 2 is a rear perspective view of a smart skin related to an embodiment of the present invention.

FIG. 1 shows skins satisfying the external curvature of an aircraft, and FIG. 2 shows a smart skin related to an embodiment of the present invention.

As shown in FIGS. 1 and 2, the front portion of the smart skin 100 is exposed to the outside of the aircraft, and may be formed to have the same curvature as the curvature of the portion where the smart skin is mounted on the aircraft. The rear portion of the smart skin 100 is a portion located inside the aircraft, and the connector of the antenna and the electronic equipment for the antenna mounted on the aircraft can be connected.

Since the skins have different curvatures depending on the antenna mounting positions of the respective aircraft, the antenna can be arranged in the smart skin so that the design can be changed according to the aircraft outer shape so that the arrangement of the logarithmic periodic slot dipole array antennas is not problematic. In addition, the skins of an aircraft can process the surface of the material that protects the antenna to have the same curvature as the outer shape of the aircraft.

3 is an exploded perspective view showing an embodiment of a smart skin having an antenna according to an embodiment of the present invention.

A smart skin 100 according to an embodiment of the present invention includes a radar dome 110 and a support 120. The antenna 10 may be disposed between the radar dome 110 and the support 120.

The radar dome 110 is located at the outermost portion of the smart skin 100 and has the same outline as the outer surface of the aircraft and includes a first layer 111 and a second layer 112 stacked on the first layer 111 As shown in FIG.

The first layer 111 is formed of a metal mesh protruding from the surface of the aircraft and designed to protect the smart skin 100 and the antenna 10 from external lightning. The second layer 112 may be formed of a glass fiber composite material designed to support the dome and impacts and loads externally applied thereto.

The metal mesh may be electrically connected to a conductive member formed on a surface of an adjacent aircraft body so that a lightning strike toward the aircraft body can flow along the surface of the body.

In addition, the glass fiber composite material is formed such that the fibers contained in the composite material have a predetermined orientation angle. When the fibers are formed to have a certain orientation angle, the fiberglass composite material has a stiffness greater than or equal to a torsional force.

The antenna 10 may be an algebraic periodic dipole array antenna configured to operate in multiple frequency bands as an electronic performance element of the smart skin 100 that replaces an existing aircraft antenna.

The supporting portion 120 is formed for maximizing the electrical performance of the antenna 10 and for the structural role of the smart skin 100. The support portion 120 is recessed toward the inside of the aircraft body in a shape corresponding to the antenna 10 so that a part of the support portion 120 seats the antenna 10. [ The support 120 may include a honeycomb core 121, a first metal mesh 122, a carbon fiber composite material 123, and a second metal mesh 124 stacked in this order.

The honeycomb core disposed in the first layer 121 plays a structural role in increasing the bending stiffness of the smart skin 100. The antenna 10 is formed to secure a space required for the performance of the antenna 10, and may be formed to perform an electronic role by using a Nomex core similar to the dielectric constant of air. Also, a first metal mesh may be formed on the second layer 122. The first metal mesh 122 serves to reflect a radio frequency (RF) signal radiated backward from the antenna 10 forward. That is, the first metal mesh 122 is arranged to always keep the performance of the antenna 10.

The third layer 123 is provided with a carbon fiber-reinforced composite material so as to structurally support a load applied to the smart skin 100. Further, a second metal mesh may be formed on the fourth layer 124. The second metal mesh 124 serves to reflect a radio frequency (RF) signal radiated backward from the antenna 10 forward. That is, the second metal mesh 124 is arranged to always keep the antenna 10 performance. The first metal mesh 122 and the second metal mesh 124 may be formed to include copper.

Hereinafter, a smart skin test evaluation method according to an embodiment of the present invention will be described.

4 is a flow chart illustrating a smart skin test evaluation method and procedure according to an embodiment of the present invention.

In one embodiment of the present invention, two smart skin test pieces were tested and evaluated in order to confirm whether the requirements for antenna performance and structural requirements were met.

The smart skin test evaluation method according to an embodiment of the present invention is for checking whether the structure satisfies both the structure requirement (area B in FIG. 4) and the antenna requirement (area A in FIG. 4) The structural strength test may include a tensile load test (S20) for confirming the tensile strength of the smart skin, a shear load test (S30) for confirming the shear strength of the smart skin, A fatigue load test (S50) for confirming the fatigue strength of the smart skin, a structural deformation antenna test (S60) for confirming antenna performance at the time of structural deformation, And an impact load test (S70) for confirming the impact strength of the skin.

The tensile load test (S20), the shear load test (S30), the bending load test (S40), and the fatigue load test (S50), which are the C regions in FIG. 4, When the applied force is removed, the smart skin test piece returns to its original state. On the other hand, since the impact load test (S70) is performed by applying a large impact to the smart skin to cause permanent deformation, the impact load test (S70) preferably uses a test piece different from the test piece used for other structural strength tests .

Further, in the embodiment of the present invention, the antenna performance tests (S11 to S16) are always performed after the respective structural strength tests. The antenna performance test is to check whether there is an abnormality after each structural strength test. At this time, the antenna performance test is performed by measuring at least one of the gain in the smart skin, the voltage standing wave ratio (VSWR), and the radiation pattern using the signal sent from the reference antenna.

In one embodiment of the present invention, a structural deformation antenna test (S60) is performed to confirm the antenna performance when the smart skin structure is deformed, and it is a test for confirming antenna performance while deforming the smart skin test piece to be. At this time, a bending test for checking the magnitude of the structural load necessary for the influence test of the load section antenna should be performed.

Hereinafter, a jig for evaluating a smart skin test according to an embodiment of the present invention and a test evaluation method using the same will be described in detail.

(S30), a bending load test (S40), a fatigue load test (S30), and a fatigue load test (S50). After the structural strength test, the antenna tests S11 to S14 are performed. For the test piece 2, the initial antenna test (S10) is performed, the impact strength test (S70) is performed, and the antenna test (S16) is performed.

Figure 5 shows a smart skin 100 in combination with a tensile test fixture 300. A wedge-shaped flat plate fixture 320 is provided at the upper and lower ends so as to be held by the wedge 330 of the material testing machine, and a load can be applied up and down. The upper and lower edges of the fixture 300 are fastened to the smart skin 100 at predetermined intervals by bolts 340 to transmit a tensile load.

The tensile load test (S20) according to an embodiment of the present invention is performed using the tensile test fixture 300 as described above.

6 illustrates a smart skin 100 coupled with a shear test fixture 400. Referring to FIG. 6, a bush 420 and a pin 420 are disposed at the upper and lower ends of the smart skin 100 so as to be engaged with the wedge plate 410 of the material testing machine. (430), so that the load can be applied up and down. The frame structure connected to the smart skin 100 and the fixture 400 is bolted at regular intervals and a flat plate type wedge plate 410 in which a shear flow at both sides of the diamond shape is connected by the bush 420 and the fins 430, Lt; / RTI > The shear load test S30 according to an embodiment of the present invention is performed using the shear test fixture 400 as described above.

7 shows a smart skin 100 coupled with a bending test fixture 500. Referring to FIG. 7, a smart skin 100 fixed by a lower flat fixture 540 is fixed to an upper flat plate fixture 520 To be pressed by the pressing member 530. For example, a load is applied to the end of the smart skin 100 to transmit a bending load. That is, the smart skin 100 can be supported like a cantilever by the lower flat plate fixture 540. At this time, the maximum value of the bending load applied by the compressive load is less than 1 ton, and the torsional load and the compressive load of the jig 500 itself can be supported. The bending load test (S40) according to an embodiment of the present invention is performed using the bending test fixture (500).

The fatigue load test jig according to the embodiment of the present invention is the same as the jig 300 in the tensile load test and a fatigue test repeated load is applied so that the jig 300 and the bolt 340 are subjected to the fatigue load. The bolt 340 is designed so that a high strength bolt is used to withstand the fatigue load, the load receiving portion is the shaft portion of the bolt 340, and the thread portion is not subjected to the load.

8 shows the smart skin 100 fixed to the pedestal 620 of the impact test fixture 600. When the fixture 600 securely grasps the smart skin 100, the impact load is free from a dedicated impact load fixture As the impact weight 610 of the round steel ball type using the fall falls, a load of 4 ft-lb and 6 ft-lb is added. In order to prevent the load from being repeatedly added, the impact load unit requires a special fixture and the weight 610 can be adjusted so that it can be hit accurately at the target point of the pedestal 620. For this purpose, a fixing unit 630 for fixing the smart skin 100 is disposed in the impact test fixture 600 according to an embodiment of the present invention to prevent the smart skin 100 from moving. The impact load test (S70) according to an embodiment of the present invention is performed by the impact test fixture (600).

In order to test the electrical performance of the smart skin antenna according to an embodiment of the present invention, an antenna test (S10 to S16) is performed, and the antenna test is performed in an anechoic chamber. More specifically, the reference antenna sends a signal to measure the electrical performance of the smart skin antenna. At this time, by selecting the size of the chamber and the type of the reference antenna according to the antenna frequency range, the performance such as gain, voltage standing wave ratio (VSWR) and radiation pattern is measured. At this time, in order to measure the radiation pattern, that is, the smart skin antenna is measured while rotating in order to test it in all directions.

And, the structural deformation antenna test (S60) is a test to see the influence on the antenna performance while deforming the smart skin. The originating antenna is installed at a height of 2 m on one side and the smart skin is installed on the other side of the same height of 2 m and only the signal level is confirmed through the network analyzer near the originating antenna and smart skin. Since this is not performed in the chamber, it is affected by the external environment. Therefore, the gain, the static standing wave ratio, and the radiation pattern as in the antenna performance test can not be accurately measured, so only the degree of deformation of the transmitted signal is judged. For this purpose, the smart skin is modified from 0 to the maximum range, and the signal is received to check the influence.

After confirming that both the structural requirements (area B in FIG. 4) and the antenna requirement (area A in FIG. 4) are satisfied for the test piece 1 and the test piece 2 as described above, the performance of the smart skin can be evaluated (S80) have.

The above-described smart skin test evaluation method is not limited to the configuration and method of the above-described embodiments, but the embodiments may be modified so that all or some of the embodiments are selectively combined .

It will be apparent to those skilled in the art that the present invention may be embodied in other specific forms without departing from the spirit or essential characteristics thereof.

It is therefore to be understood that the above-described embodiments are illustrative in all aspects and not restrictive. The scope of the present invention is defined by the appended claims rather than the detailed description, and all changes or modifications derived from the meaning and scope of the claims and their equivalents should be interpreted as being included in the scope of the present invention .

Claims (8)

A structural strength test and an antenna performance test for verifying whether the structure of an aircraft fuselage is formed and at the same time satisfies the structural requirements and antenna requirements of a smart skin performing an antenna function,
The structural strength test may include a tensile load test for confirming the tensile strength of the smart skin, a shear load test for confirming the shear strength of the smart skin, a bending load test for confirming the bending strength of the smart skin, A structural strain antenna test for confirming the antenna performance at the time of structural deformation, and an impact load test for confirming the impact strength of the smart skin. The method according to claim 1,
The smart skin test evaluation method in which an antenna performance test is performed after each of the above structural strength tests. 3. The method of claim 2,
In the impact load test,
Wherein the smart skin test is performed on a separate smart skin. The method according to claim 1,
The antenna performance test
Wherein the performance is judged by measuring at least one of a gain in a smart skin, a voltage standing wave ratio (VSWR), and a radiation pattern using a signal sent from a reference antenna. . 5. The method of claim 4,
Wherein the antenna performance test is performed in an anechoic chamber. The method according to claim 1,
In the above-described structural deformation antenna test,
Wherein a smart skin test evaluation method is performed by measuring a signal level emitted from an originating antenna spaced from a smart skin according to a variation of the smart skin. The method according to claim 1,
In the smart skin,
A radome dome portion exposed to the outside and having a glass fiber composite material and a metal mesh formed to cover the glass fiber composite material;
A support portion coupled to an inner surface of the radar dome portion; And
And an antenna disposed between the radar dome portion and the support portion,
Wherein the radar dome portion is formed to have the same curvature as the surface of the aircraft body so as to reduce the radar detection area. 8. The method of claim 7,
The support portion
A honeycomb core, a first metal mesh, a glass fiber composite material, and a second metal mesh are laminated in this order.
KR20130080559A 2013-07-09 2013-07-09 Method for testing and evaluating for smart skin KR20150006736A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
KR20130080559A KR20150006736A (en) 2013-07-09 2013-07-09 Method for testing and evaluating for smart skin

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
KR20130080559A KR20150006736A (en) 2013-07-09 2013-07-09 Method for testing and evaluating for smart skin

Related Child Applications (1)

Application Number Title Priority Date Filing Date
KR1020150051059A Division KR101591301B1 (en) 2015-04-10 2015-04-10 Method for testing and evaluating for smart skin

Publications (1)

Publication Number Publication Date
KR20150006736A true KR20150006736A (en) 2015-01-19

Family

ID=52569977

Family Applications (1)

Application Number Title Priority Date Filing Date
KR20130080559A KR20150006736A (en) 2013-07-09 2013-07-09 Method for testing and evaluating for smart skin

Country Status (1)

Country Link
KR (1) KR20150006736A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109684679A (en) * 2018-12-04 2019-04-26 中国航空工业集团公司西安飞机设计研究所 A kind of dome-shaped reinforcing frame Parameters design for bearing antisymmetry concentrfated load

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109684679A (en) * 2018-12-04 2019-04-26 中国航空工业集团公司西安飞机设计研究所 A kind of dome-shaped reinforcing frame Parameters design for bearing antisymmetry concentrfated load
CN109684679B (en) * 2018-12-04 2023-05-26 中国航空工业集团公司西安飞机设计研究所 Parameter design method for circular arch reinforcement frame bearing antisymmetric concentrated load

Similar Documents

Publication Publication Date Title
US6249261B1 (en) Polymer, composite, direction-finding antenna
US8149177B1 (en) Slotted waveguide antenna stiffened structure
Matsuzaki et al. Antenna/sensor multifunctional composites for the wireless detection of damage
KR101591301B1 (en) Method for testing and evaluating for smart skin
US7446730B2 (en) Radio wave device
Lockyer et al. Conformal load-bearing antenna structures (CLAS): initiative for multiple military and commercial applications
You et al. Microstrip antenna for SAR application with composite sandwich construction: surface-antenna-structure demonstration
Kim et al. Impact damage and antenna performance of conformal load-bearing antenna structures
You et al. Impact behavior of composite antenna array that is conformed around cylindrical bodies
Datashvili et al. Design of a morphing skin using flexible fiber composites for space-reconfigurable reflectors
Xu et al. Simulation and electromagnetic performance of cylindrical two-element microstrip antenna array integrated in 3D woven glass fiber/epoxy composites
CN108984880B (en) Deformation array antenna electrical property quick compensation method based on least square method
KR20150006736A (en) Method for testing and evaluating for smart skin
Li et al. Design and study of a new broadband RCS carbon-glass fiber hybrid metamaterial
Jeon et al. Buckling characteristics of smart skin structures
Lockyer et al. Development of a structurally integrated conformal load-bearing multifunction antenna: overview of the air force smart skin structures technology demonstration program
Salvatus et al. Development of deployable antennas for the diwata-2 microsatellite's amateur radio payload
CN113562157A (en) Aircraft airborne luneberg mounting rack
Virone et al. Broadband array element for the SKA low-frequency aperture array
Khanal et al. A wide-scanning array antenna of connected vertical bowtie elements structurally integrated within an aircraft fuselage
Patil et al. Characterization of standard structural CFRP beam shapes for UAS VHF antenna applications
You et al. Impact behavior and radiation performance of a structurally integrated antenna array conformed around cylindrical bodies
RU2309495C2 (en) Electromagnetic wave absorber
Ha et al. Design optimization of a WR-90 slotted waveguide antenna stiffened structures
Yarza et al. High stability large reflectors for Ka Band

Legal Events

Date Code Title Description
AMND Amendment
E601 Decision to refuse application
AMND Amendment
A107 Divisional application of patent