CN110190914B - Shielding device for testing anti-interference satellite receiver of aircraft - Google Patents
Shielding device for testing anti-interference satellite receiver of aircraft Download PDFInfo
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- CN110190914B CN110190914B CN201810494474.4A CN201810494474A CN110190914B CN 110190914 B CN110190914 B CN 110190914B CN 201810494474 A CN201810494474 A CN 201810494474A CN 110190914 B CN110190914 B CN 110190914B
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B17/00—Monitoring; Testing
- H04B17/0082—Monitoring; Testing using service channels; using auxiliary channels
- H04B17/0087—Monitoring; Testing using service channels; using auxiliary channels using auxiliary channels or channel simulators
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B17/00—Monitoring; Testing
- H04B17/20—Monitoring; Testing of receivers
- H04B17/29—Performance testing
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/1851—Systems using a satellite or space-based relay
- H04B7/18519—Operations control, administration or maintenance
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K9/00—Screening of apparatus or components against electric or magnetic fields
- H05K9/0007—Casings
- H05K9/006—Casings specially adapted for signal processing applications, e.g. CATV, tuner, antennas amplifier
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- Computer Networks & Wireless Communication (AREA)
- Electromagnetism (AREA)
- Astronomy & Astrophysics (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Physics & Mathematics (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Shielding Devices Or Components To Electric Or Magnetic Fields (AREA)
- Details Of Aerials (AREA)
- Monitoring And Testing Of Transmission In General (AREA)
Abstract
The invention provides a shielding device for testing an anti-interference satellite receiver of an aircraft, which comprises a shell, an antenna cover, a wave absorbing layer, a transmitting antenna group and a monitoring receiving antenna, wherein the shell, the antenna cover and the aircraft shell form a closed cavity together, the wave absorbing layer is arranged on the inner surface of the shell and is used for absorbing reflected electric waves inside the shell, the transmitting antenna group is arranged on the antenna cover, the transmitting antenna group is used for transmitting a test signal to the anti-interference satellite receiver, the monitoring receiving antenna is arranged on the antenna cover and is parallel to the receiving antenna of the anti-interference satellite receiver, and the monitoring receiving antenna is used for receiving the test signal transmitted by the transmitting antenna group and outputting the received test signal to the outside for external real-time monitoring. The technical scheme of the invention is applied to solve the technical problems that the receiver testing method in the prior art cannot establish a relatively clean wireless testing environment for the anti-interference receiver, and has large occupied area and high manufacturing cost and maintenance cost.
Description
Technical Field
The invention relates to the technical field of satellite navigation receiver testing, in particular to a shielding device for testing an anti-interference satellite receiver of an aircraft.
Background
The anti-interference satellite receiver test usually needs to use professional equipment such as a wireless shielding darkroom, a satellite navigation signal simulation source and the like as test environment support, the whole test environment needs a radio wave shielding darkroom to simulate a radio wave open field, and the radio wave shielding darkroom has the defects of large occupied area, high manufacturing cost, high maintenance cost and the like.
When the product is tested on the ground, the anti-interference satellite receiver needs to be tested and detected, and in order to effectively shield other signals, a relatively clean wireless test environment needs to be established for the anti-interference satellite receiver in the test process. Currently, a commonly used indoor open type test method can cause uncontrollable satellite navigation signals (such as multipath signals), so that the product test requirements cannot be met by adopting the traditional indoor open type test method.
Disclosure of Invention
The invention provides a shielding device for testing an anti-interference satellite receiver of an aircraft, which can solve the technical problems that a relatively clean wireless testing environment cannot be established for the anti-interference receiver in the prior art, the occupied area is large, and the manufacturing cost and the maintenance cost are high.
The invention provides a shielding device for testing an anti-interference satellite receiver of an aircraft, wherein the anti-interference satellite receiver is arranged in a shell of the aircraft, and the shielding device comprises: the aircraft comprises a shell and an antenna housing, wherein the shell is provided with an accommodating cavity with two open ends, the antenna housing is arranged at a first open end of the shell and extends towards a second open end of the shell, the second open end of the shell is attached to the aircraft shell, and the shell, the antenna housing and the aircraft shell form a closed cavity together; the wave absorbing layer is arranged on the inner surface of the shell and is used for absorbing reflected electric waves inside the shell; the transmitting antenna group is arranged on the antenna cover and used for transmitting a test signal to the anti-interference satellite receiver; the monitoring receiving antenna is arranged on the antenna cover and is parallel to the receiving antenna of the anti-interference satellite receiver, and the monitoring receiving antenna is used for receiving the test signal transmitted by the transmitting antenna group and outputting the received test signal to the outside for external real-time monitoring.
Furthermore, the test signal comprises a navigation signal and an interference signal, the transmitting antenna group comprises a navigation signal transmitting antenna and an interference signal transmitting antenna, the navigation signal transmitting antenna is arranged right above the anti-interference satellite receiver and used for transmitting the navigation signal to the anti-interference satellite receiver, the interference signal transmitting antenna and the navigation signal transmitting antenna are arranged at intervals, and the interference signal transmitting antenna is used for transmitting the interference signal to the anti-interference satellite receiver.
Further, the antenna house includes antenna house lid and antenna house main part, and the antenna house lid sets up the first open end at the casing, and monitoring receiving antenna's one end sets up on the antenna house lid, and monitoring receiving antenna's the other end sets up in the antenna house main part.
Furthermore, the shielding device further comprises a metal elastic shielding strip, the metal elastic shielding strip is arranged between the second opening end of the shell and the aircraft shell, and the metal elastic shielding strip is used for realizing tight connection between the shielding device and the aircraft shell, reducing cavity resonance and reflection and preventing the aircraft shell from being damaged.
Further, the aircraft casing is cylindrical structure, and the second open end of casing comprises first arc limit, first sharp limit, second arc limit and the sharp limit of second that connects gradually, and first sharp limit and the sharp limit parallel arrangement of second, first arc limit and second arc limit parallel arrangement, the arc radius on first arc limit and second arc limit all is the same with the radius of aircraft casing.
Furthermore, the shielding device further comprises a fixing bandage, one end of the fixing bandage is connected with the first straight line edge, the other end of the fixing bandage bypasses the aircraft shell and is connected with the second straight line edge, and the fixing bandage is used for fixing the shielding device and the aircraft shell.
Further, the minimum distance between the radome cover and the aircraft casing is greater than 15 cm.
Furthermore, the shielding device further comprises a first supporting beam, a second supporting beam and a fixing rod group, the first supporting beam is connected with the second supporting beam through the fixing rod group, and the shell is covered outside the first supporting beam, the second supporting beam and the fixing rod group.
Further, the monitoring receiving antenna comprises a circular polarization wide-temperature antenna.
Further, the shielding device further comprises a handle, and the handle is arranged on the antenna housing cover body.
The technical scheme of the invention provides the shielding device for testing the anti-interference satellite receiver of the aircraft, and the shielding device can provide a radio wave open field simulated by the receiver when the receiver is installed in the aircraft shell is used for product detection, and shield the radio wave clutter signals in the real environment. Meanwhile, the monitoring receiving antenna is arranged inside the shielding device, can monitor radio wave signals in an internally simulated open field in real time, can synchronously output the radio wave signals to external monitoring equipment for real-time calculation and environment monitoring, and provides a controllable wireless testing environment for an aircraft receiver. Therefore, compared with the prior art, the shielding device can realize the test of the anti-interference satellite receiver by adding the shielding device of the invention on the premise of not changing the structure of any product. The shielding device is convenient to use and maintain, has a light structure, meets the test requirements of tested products, and reduces the requirements of receiver tests on sites. In addition, the implementation method of the invention is safe, reliable, economic, flexible and easy to implement, and can have engineering application conditions in product testing in a short period.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
FIG. 1 is a schematic structural composition diagram of a shielding device for aircraft anti-interference satellite receiver testing, provided according to a specific embodiment of the invention;
FIG. 2 is a schematic diagram illustrating an application structure of a shielding apparatus for testing an aircraft anti-interference satellite receiver, according to an embodiment of the present invention;
FIG. 3 illustrates a top view of a shielding apparatus for aircraft tamper resistant satellite receiver testing provided in accordance with a specific embodiment of the present invention;
FIG. 4 shows a left side view of the shielding device of FIG. 3 for aircraft tamper resistant satellite receiver testing;
fig. 5 shows a front view of the shielding device for the aircraft anti-jamming satellite receiver test in fig. 3.
Wherein the figures include the following reference numerals:
10. a housing; 11. a first housing; 12. a second housing; 20. a wave-absorbing layer; 30. a transmitting antenna group; 40. monitoring a receiving antenna; 50. a radome cover body; 60. a metal elastic shielding strip; 70. fixing a binding band; 80. a first support beam; 90. a second support beam; 91. a first linear rod; 92. a first arcuate bar; 93. a second linear bar; 94. a second arcuate bar; 100. a fixed rod group; 110. a handle; 120. an antenna connector; 121. a first transmitting antenna connector; 122. a second transmitting antenna connector; 123. a third transmitting antenna connector; 124. a fourth transmitting antenna connector; 125. a fifth transmitting antenna connector; 126. a sixth transmitting antenna connector; 127. monitoring a receiving antenna connector; 128. a navigation signal transmitting antenna connector; 130. an antenna fixing screw; 140. fixing a bolt buckle; 150. fastening a binding band; 160. an aircraft housing.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
The relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.
As shown in fig. 1 to 5, according to a specific embodiment of the present invention, there is provided a shielding apparatus for testing an anti-interference satellite receiver of an aircraft, the anti-interference satellite receiver is disposed in an aircraft casing 160, the shielding apparatus includes a casing 10, an antenna cover, a wave-absorbing layer 20, a transmitting antenna group 30 and a monitoring receiving antenna 40, the casing 10 has a receiving cavity with two open ends, the antenna cover is disposed at a first open end of the casing 10 and extends toward a second open end of the casing 10, the second open end of the casing 10 is attached to the aircraft casing, the casing 10, the antenna cover and the aircraft casing together form a closed cavity, the wave-absorbing layer 20 is disposed on an inner surface of the casing 10, the wave-absorbing layer 20 is configured to absorb reflected electric waves inside the casing 10, the transmitting antenna group 30 is disposed on the antenna cover, the transmitting antenna group 30 is configured to transmit a test signal to the anti-interference satellite receiver, the monitoring receiving antenna 40 is arranged on the antenna cover and is arranged in parallel with a receiving antenna of the anti-interference satellite receiver, and the monitoring receiving antenna 40 is used for receiving the test signal transmitted by the transmitting antenna group 30 and outputting the received test signal to the outside for external real-time monitoring.
By applying the configuration mode, the shielding device for the test of the anti-interference satellite receiver of the aircraft is provided, and the shielding device can provide a radio wave open field simulated by the receiver in the aircraft shell during product detection and shield radio wave clutter signals in a real environment. Meanwhile, the monitoring receiving antenna is arranged inside the shielding device, can monitor radio wave signals in an internally simulated open field in real time, can synchronously output the radio wave signals to external monitoring equipment for real-time calculation and environment monitoring, and provides a controllable wireless testing environment for an aircraft receiver. Therefore, compared with the prior art, the shielding device provided by the invention can realize the test of the receiver by adding the shielding device provided by the invention on the premise of not changing any product structure. The shielding device is convenient to use and maintain, has a light structure, meets the test requirements of tested products, and reduces the requirements of receiver tests on sites. In addition, the implementation method of the invention is safe, reliable, economic, flexible and easy to implement, and can have engineering application conditions in product testing in a short period.
Further, in the present invention, in order to simultaneously test the navigation signal receiving performance and the anti-interference performance of the anti-interference satellite receiver, the transmitting antenna group 30 may be configured to include a navigation signal transmitting antenna and an interference signal transmitting antenna, the navigation signal transmitting antenna is disposed right above the anti-interference satellite receiver and is used for transmitting a navigation signal to the anti-interference satellite receiver, the interference signal transmitting antenna and the navigation signal transmitting antenna are disposed at an interval, and the interference signal transmitting antenna is used for transmitting an interference signal to the anti-interference satellite receiver.
As shown in fig. 3, as an embodiment of the present invention, the transmitting antenna group 30 is disposed on the antenna cover through an antenna connector 120, the transmitting antenna group 30 includes seven transmitting antennas, wherein, a transmitting antenna is connected on the antenna cover through a transmitting antenna connector 121, a transmitting antenna is connected on the antenna cover through a transmitting antenna connector 122, a transmitting antenna is connected on the antenna cover through a transmitting antenna connector 123, a transmitting antenna is connected on the antenna cover through a transmitting antenna connector 124, a transmitting antenna is connected on the antenna cover through a transmitting antenna connector 125, a transmitting antenna is connected on the antenna cover through a transmitting antenna connector 126, a navigation signal transmitting antenna is connected on the antenna cover through a navigation signal transmitting antenna connector 128, a navigation signal transmitting antenna is used for transmitting navigation signals to the anti-interference satellite receiver, the monitoring receiving antenna 40 is connected to the antenna housing through the monitoring receiving antenna connector 127, and the monitoring receiving antenna 40 is used for receiving the signal transmitted by the transmitting antenna group 30 and outputting the signal to an external monitoring device. The transmitting antenna group 30 is used as a signal input port of the shielding device, and a transmitting antenna is installed according to the position of the receiving antenna of the anti-interference satellite receiver, so that the navigation signal transmitting antenna is arranged right above the anti-interference satellite receiver.
Considering signal balance, a transmitting antenna connector 121, a transmitting antenna connector 122, a transmitting antenna connector 123, a transmitting antenna connector 124, a transmitting antenna connector 125 and a transmitting antenna connector 126 are uniformly spaced and annularly arranged on the outer side of a navigation signal transmitting antenna connector 128, the transmitting antenna connector 121, the transmitting antenna connector 122, the transmitting antenna connector 123, the transmitting antenna connector 124, the transmitting antenna connector 125 and the transmitting antenna connector 126 are used for providing interference signals for an anti-interference satellite receiver, so as to test the anti-interference performance of the anti-interference satellite receiver. The signals received by the monitoring receiving antenna 40 are output to an external monitoring device through a cable, the mounting mode of the monitoring receiving antenna is parallel to that of the receiving antenna of the anti-interference satellite receiver, the wireless signals transmitted by the transmitting antenna group 30 are received in the same direction, real-time monitoring is carried out in a test, and when an aircraft fails, failure analysis and troubleshooting can be carried out on the premise that a shielding device is not moved.
Further, in the present invention, as shown in fig. 1, the radome includes a radome cover 50 and a radome body, the radome cover 50 is disposed at the first open end of the housing 10, one end of the monitoring receiving antenna 40 is disposed on the radome cover 50 through the monitoring receiving antenna connector 127, and the other end of the monitoring receiving antenna 40 is disposed on the radome body. The monitoring receiving antenna 40 can receive satellite signals of various frequency points such as GPS, BDS and the like, and can transmit radio wave signals to external monitoring equipment through an output interface of the receiving antenna to realize environment monitoring. As an embodiment of the present invention, the monitoring receiving antenna 40 may adopt a circular polarization wide temperature antenna, which is capable of simultaneously receiving satellite navigation signals in a satellite navigation frequency band. The monitoring receiving antenna 40 is arranged at the middle vacant position of the transmitting antenna on the inner side of the antenna housing, so that the satellite navigation receiver to be detected can be ensured to receive signals, the monitoring receiving antenna 40 can also synchronously receive the signals, and the signals are ensured not to interfere with each other.
In the present invention, as shown in fig. 1, the shielding device further comprises a metal elastic shielding strip 60, the metal elastic shielding strip 60 is disposed between the second open end of the housing 10 and the aircraft housing, and the metal elastic shielding strip 60 is used for achieving tight connection between the shielding device and the aircraft housing, reducing cavity resonance and reflection, and preventing the aircraft housing from being damaged. As an embodiment of the present invention, a metal elastic shielding strip 60 may be provided at the bottom edge of the housing 10 to fix the shielding device to the aircraft housing when the aircraft housing vibrates, and the metal elastic shielding strip 60 can ensure a tight connection with the aircraft housing without damaging the product housing.
Further, in the present invention, the aircraft casing is a cylindrical structure, and in order to reduce the cavity resonance, the second opening end of the casing 10 may be configured to be composed of a first arc-shaped side, a first straight-line side, a second arc-shaped side, and a second straight-line side, which are connected in sequence, the first straight-line side and the second straight-line side are arranged in parallel, the first arc-shaped side and the second arc-shaped side are arranged in parallel, and the arc radii of the first arc-shaped side and the second arc-shaped side are both the same as the radius of the aircraft casing. With this arrangement, when the shielding device is placed on the aircraft casing 160, the second open end of the casing 10 can be in close contact with the aircraft casing 160 of cylindrical configuration, so that a completely closed three-dimensional space can be formed. Meanwhile, the wave absorbing material is fully attached to the surface of the inner wall of the shell 10, so that the reflected electric waves inside the shell can be effectively absorbed, the cavity resonance is effectively reduced, external clutter is shielded, and the reflected electric waves inside are absorbed, thereby providing a wide scene for an anti-interference receiver.
Further, in the present invention, in order to achieve a reliable connection between the shielding device and the aircraft casing, the shielding device may be configured to further include a fixing strap 70, one end of the fixing strap 70 is connected to the first straight side, the other end of the fixing strap 70 is connected to the second straight side by passing around the aircraft casing, and the fixing strap 70 is used to fix the shielding device to the aircraft casing 160. As an embodiment of the present invention, as shown in fig. 1, a strap buckle 150 is installed at the lower part of the housing 10, and the fixing strap 70 can be connected with the strap buckle 150 on the housing 10 to realize the fixed connection between the shielding device and the aircraft housing 160.
Further, in the present invention, in order to avoid the generation of multipath signals, the minimum distance between the radome cover 50 and the aircraft casing may be set to be greater than 15 cm. Further, in the present invention, in order to improve the structural strength of the shielding apparatus, the shielding apparatus may be configured to further include a first support beam 80, a second support beam 90, and a fixing rod group 100, the first support beam 80 is connected to the second support beam 90 through the fixing rod group 100, and the housing 10 is covered outside the first support beam 80, the second support beam 90, and the fixing rod group 100. As an embodiment of the present invention, the structural shape of the second supporting beam 90 is the same as the structural shape of the second opening end of the housing 10, the second supporting beam 90 is composed of a first straight rod 91, a first arc rod 92, a second straight rod 93 and a second arc rod 94 which are sequentially connected end to end, the first supporting beam 80 is a quadrilateral structure, the fixing rod group 100 is composed of two vertical rods which are arranged in parallel, one of the vertical rods is respectively connected with the first straight rod 91 and the first supporting beam 80, and the other vertical rod is respectively connected with the second straight rod 93 and the first supporting beam 80.
Further, in the present invention, in order to facilitate movement and carrying of the shielding apparatus, the shielding apparatus may be configured to further include a handle 110, and the handle 110 is disposed on the radome cover 50. In addition, in order to facilitate assembly, the housing 10 may be configured to include a first housing 11 and a second housing 12, and the first housing 11 and the second housing 12 are respectively fixedly connected to the fixing bar group 100 to form a housing having a receiving chamber with both ends open.
For a further understanding of the present invention, the shielding device of the present invention is described in detail below with reference to fig. 1 to 5.
As shown in fig. 1 to 5, as an embodiment of the present invention, the shielding apparatus includes a housing 10, an antenna housing, a wave-absorbing layer 20, a transmitting antenna group 30, a monitoring receiving antenna 40, a first supporting beam 80, a second supporting beam 90, a fixing rod group 100, a metal elastic shielding strip 60, a fixing strap 70 and a handle 110, wherein the first supporting beam 80 is connected to the second supporting beam 90 through the fixing rod group 100, and the housing 10 covers the first supporting beam 80, the second supporting beam 90 and the fixing rod group 100 to form a box body with an opening at an upper portion and a lower portion. The radome is disposed at a first open end of the housing 10, and the radome cooperates with the housing 10 to form an open-bottomed box having the same shape as the aircraft housing. The inside of the housing 10 is adhered with a wave-absorbing material in the navigation frequency band for absorbing the internally reflected electric waves. The transmitting antenna group 30 is installed on the upper portion of the antenna housing through an antenna fixing screw 130 and a fixing bolt fastener 140, and is used for transmitting a wireless satellite navigation signal and an interference signal. The monitoring receiving antenna 40 is installed on the inner wall of the radome, and is used for receiving the satellite navigation signal and the interference signal transmitted by the transmitting antenna group 30 and outputting the satellite navigation signal and the interference signal to an external monitoring device.
When the performance test of the anti-interference satellite receiver is carried out, the aircraft does not need to be modified or additionally provided with a test piece, and when the device is used, the shielding device is only slightly covered right above the receiving antenna of the anti-interference satellite receiver of the aircraft and is fixed on the aircraft shell 160 by the fixing bandage 70. At this moment, the lower part of the shielding device is in contact with the aircraft shell 160 to form a completely closed three-dimensional space, so that cavity resonance can be effectively reduced, external clutter is shielded, and internal reflection electric waves are absorbed, thereby providing an open scene for an anti-interference receiver. The shielding device is provided with a monitoring receiving antenna 40 which can receive satellite signals of various frequency points such as GPS, BDS and the like, and radio wave signals can be transmitted to external monitoring equipment through an output interface of a product receiving antenna to realize environment monitoring. When the aircraft breaks down, the fault analysis and troubleshooting can be carried out on the premise of not moving the shielding case. In addition, a handle 110 is mounted on the radome cover 50 of the shielding device, which facilitates the movement and carrying of the shielding device.
The device is a small-sized shielding device with complete structure and reliable work, does not need power supply, has simple and reliable structure, convenient use and convenient carrying, can provide an electric wave open field test environment for an anti-interference satellite receiver, and can meet the requirement of a product test environment. The practical application proves that the shielding device can ensure that the attenuation of the wireless navigation signal in the device is less than 30dB, the shielding performance of the device is more than 35dB, the metal surface reflection is reduced, the test reliability, the credibility and the comprehensiveness are improved, and the requirement of the anti-interference satellite receiver test on the field is reduced.
Spatially relative terms, such as "above … …," "above … …," "above … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial relationship to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" can include both an orientation of "above … …" and "below … …". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
It should be noted that the terms "first", "second", and the like are used to define the components, and are only used for convenience of distinguishing the corresponding components, and the terms have no special meanings unless otherwise stated, and therefore, the scope of the present invention should not be construed as being limited.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. A shield assembly for testing an anti-interference satellite receiver of an aircraft, the anti-interference satellite receiver being disposed within a housing of the aircraft, the shield assembly comprising:
the aircraft comprises a shell (10) and an antenna housing, wherein the shell (10) is provided with an accommodating cavity with two open ends, the antenna housing is arranged at a first open end of the shell (10) and extends towards a second open end of the shell (10), the second open end of the shell (10) is attached to the aircraft shell, and the shell (10), the antenna housing and the aircraft shell jointly form a closed cavity;
the wave absorbing layer (20), the wave absorbing layer (20) is arranged on the inner surface of the shell (10), and the wave absorbing layer (20) is used for absorbing the reflected electric waves inside the shell (10);
the transmitting antenna group (30), the transmitting antenna group (30) is arranged on the antenna cover, and the transmitting antenna group (30) is used for transmitting a test signal to an anti-interference satellite receiver;
the monitoring receiving antenna (40) is arranged on the antenna cover and is parallel to a receiving antenna of the anti-interference satellite receiver, and the monitoring receiving antenna (40) is used for receiving the test signal transmitted by the transmitting antenna group (30) and outputting the received test signal to the outside for external real-time monitoring;
the shielding device further comprises a metal elastic shielding strip (60), wherein the metal elastic shielding strip (60) is arranged between the second opening end of the shell (10) and the aircraft shell, and the metal elastic shielding strip (60) is used for achieving tight connection between the shielding device and the aircraft shell, reducing cavity resonance and reflection and preventing the aircraft shell from being damaged.
2. The shielding device for testing the aircraft antijamming satellite receiver according to claim 1, wherein the test signal comprises a navigation signal and an interference signal, the transmitting antenna group (30) comprises a navigation signal transmitting antenna and an interference signal transmitting antenna, the navigation signal transmitting antenna is arranged right above the antijamming satellite receiver and used for transmitting the navigation signal to the antijamming satellite receiver, the interference signal transmitting antenna is arranged at a distance from the navigation signal transmitting antenna, and the interference signal transmitting antenna is used for transmitting the interference signal to the antijamming satellite receiver.
3. The shielding device for the aircraft antijamming satellite receiver test according to claim 2, wherein the radome includes a radome cover body (50) and a radome main body, the radome cover body (50) is disposed at the first open end of the housing (10), one end of the monitoring receiving antenna (40) is disposed on the radome cover body (50), and the other end of the monitoring receiving antenna (40) is disposed on the radome main body.
4. The shielding device for the aircraft anti-interference satellite receiver test according to claim 3, wherein the aircraft shell is of a cylindrical structure, the second opening end of the shell (10) is composed of a first arc-shaped edge, a first straight line edge, a second arc-shaped edge and a second straight line edge which are sequentially connected, the first straight line edge and the second straight line edge are arranged in parallel, the first arc-shaped edge and the second arc-shaped edge are arranged in parallel, and the arc radiuses of the first arc-shaped edge and the second arc-shaped edge are the same as the radius of the aircraft shell.
5. The shielding device for testing the aircraft antijam satellite receiver according to claim 4, characterized in that the shielding device further comprises a fixing strap (70), one end of the fixing strap (70) is connected with the first straight edge, the other end of the fixing strap (70) is connected with the second straight edge by passing through the aircraft shell, and the fixing strap (70) is used for fixing the shielding device with the aircraft shell.
6. The shielding device for aircraft antijam satellite receiver testing according to claim 4, characterized in that the minimum distance between the radome cover (50) and the aircraft casing is greater than 15 cm.
7. The shielding device for the aircraft antijamming satellite receiver test according to claim 1, characterized in that the shielding device further comprises a first supporting beam (80), a second supporting beam (90) and a fixing rod set (100), wherein the first supporting beam (80) is connected with the second supporting beam (90) through the fixing rod set (100), and the housing (10) covers the first supporting beam (80), the second supporting beam (90) and the fixing rod set (100).
8. Shielding device for aircraft antijam satellite receiver testing according to claim 1, characterized in that said monitoring reception antenna (40) comprises a circularly polarized wide temperature antenna.
9. The shielding device for aircraft antijamming satellite receiver tests according to claim 3, characterized in that it further comprises a handle (110), said handle (110) being provided on said radome cover (50).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810494474.4A CN110190914B (en) | 2018-05-22 | 2018-05-22 | Shielding device for testing anti-interference satellite receiver of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810494474.4A CN110190914B (en) | 2018-05-22 | 2018-05-22 | Shielding device for testing anti-interference satellite receiver of aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110190914A CN110190914A (en) | 2019-08-30 |
| CN110190914B true CN110190914B (en) | 2021-10-19 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810494474.4A Active CN110190914B (en) | 2018-05-22 | 2018-05-22 | Shielding device for testing anti-interference satellite receiver of aircraft |
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| CN112701474B (en) * | 2020-12-16 | 2022-04-12 | 中国人民解放军91404部队 | Anti-interference shielding device for shipborne microwave omnidirectional antenna |
| CN114024883B (en) * | 2021-11-05 | 2023-11-17 | 江西洪都航空工业集团有限责任公司 | Method, device and system for open-loop parallel testing of multiple products of data link |
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| CN117949741B (en) * | 2024-03-21 | 2024-07-02 | 江苏领创星通卫星通信科技有限公司 | Antenna testing device |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104698474A (en) * | 2015-04-02 | 2015-06-10 | 芜湖航飞科技股份有限公司 | Satellite navigation receiver anti-jamming testing system and method |
| CN204515140U (en) * | 2015-04-10 | 2015-07-29 | 湖南矩阵电子科技有限公司 | A kind of removable in-situ test general shield cover |
| EP3005482A1 (en) * | 2013-09-24 | 2016-04-13 | Northrop Grumman Systems Corporation | Antenna for multiple frequency bands |
| CN206161866U (en) * | 2016-05-18 | 2017-05-10 | 北京自动化控制设备研究所 | Inertia satellite navigation integration anti -interference antenna darkroom |
-
2018
- 2018-05-22 CN CN201810494474.4A patent/CN110190914B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3005482A1 (en) * | 2013-09-24 | 2016-04-13 | Northrop Grumman Systems Corporation | Antenna for multiple frequency bands |
| CN104698474A (en) * | 2015-04-02 | 2015-06-10 | 芜湖航飞科技股份有限公司 | Satellite navigation receiver anti-jamming testing system and method |
| CN204515140U (en) * | 2015-04-10 | 2015-07-29 | 湖南矩阵电子科技有限公司 | A kind of removable in-situ test general shield cover |
| CN206161866U (en) * | 2016-05-18 | 2017-05-10 | 北京自动化控制设备研究所 | Inertia satellite navigation integration anti -interference antenna darkroom |
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