CN110190914A - Shielding device for aircraft anti-jamming satellite receiver test - Google Patents
Shielding device for aircraft anti-jamming satellite receiver test Download PDFInfo
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- CN110190914A CN110190914A CN201810494474.4A CN201810494474A CN110190914A CN 110190914 A CN110190914 A CN 110190914A CN 201810494474 A CN201810494474 A CN 201810494474A CN 110190914 A CN110190914 A CN 110190914A
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- 238000012360 testing method Methods 0.000 title claims abstract description 68
- 238000012544 monitoring process Methods 0.000 claims abstract description 50
- 239000002184 metal Substances 0.000 claims description 13
- 230000010287 polarization Effects 0.000 claims description 2
- 238000012423 maintenance Methods 0.000 abstract description 3
- 238000010998 test method Methods 0.000 abstract description 3
- 238000010276 construction Methods 0.000 abstract 1
- 238000000034 method Methods 0.000 description 9
- 230000007613 environmental effect Effects 0.000 description 4
- 238000012986 modification Methods 0.000 description 3
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- 239000011358 absorbing material Substances 0.000 description 2
- 238000004364 calculation method Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000013024 troubleshooting Methods 0.000 description 2
- 230000014509 gene expression Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000011056 performance test Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Classifications
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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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- Aviation & Aerospace Engineering (AREA)
- General Physics & Mathematics (AREA)
- Monitoring And Testing Of Transmission In General (AREA)
- Shielding Devices Or Components To Electric Or Magnetic Fields (AREA)
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Abstract
本发明提供了一种用于飞行器抗干扰卫星接收机测试的屏蔽装置，该屏蔽装置包括壳体、天线罩、吸波层、发射天线组和监测接收天线，壳体、天线罩以及飞行器壳体共同形成封闭腔体，吸波层设置在壳体的内表面，吸波层用于吸收壳体内部的反射电波，发射天线组设置在天线罩上，发射天线组用于向抗干扰卫星接收机发射测试信号，监测接收天线设置在天线罩上且与抗干扰卫星接收机的接收天线平行设置，监测接收天线用于接收发射天线组发射的测试信号并将接收到的测试信号输出至外部以用于外部实时监测。应用本发明的技术方案，以解决现有技术中接收机测试方法无法为抗干扰接收机建立相对干净的无线测试环境以及占地面积大、造价和维护成本高的技术问题。
The invention provides a shielding device for aircraft anti-jamming satellite receiver testing, the shielding device includes a housing, a radome, a wave-absorbing layer, a transmitting antenna group and a monitoring receiving antenna, the housing, the radome and the aircraft housing Together form a closed cavity, the wave-absorbing layer is set on the inner surface of the shell, the wave-absorbing layer is used to absorb the reflected radio waves inside the shell, the transmitting antenna group is set on the radome, and the transmitting antenna group is used to send anti-jamming satellite receivers The test signal is transmitted, the monitoring receiving antenna is arranged on the radome and arranged in parallel with the receiving antenna of the anti-jamming satellite receiver, and the monitoring receiving antenna is used to receive the test signal transmitted by the transmitting antenna group and output the received test signal to the outside for use External real-time monitoring. The technical scheme of the present invention is applied to solve the technical problems that the receiver test method in the prior art cannot establish a relatively clean wireless test environment for the anti-jamming receiver, occupies a large area, and has high construction and maintenance costs.
Description
技术领域technical field
本发明涉及卫星导航接收机测试技术领域，尤其涉及一种用于飞行器抗干扰卫星接收机测试的屏蔽装置。The invention relates to the technical field of satellite navigation receiver testing, in particular to a shielding device for aircraft anti-jamming satellite receiver testing.
背景技术Background technique
抗干扰卫星接收机测试通常需要以无线屏蔽暗室、卫星导航信号模拟源等专业设备作为测试环境支撑，整个测试环境中需要无线电波屏蔽暗室模拟电波开阔场，而无线电波屏蔽暗室具有占地面积大、造价和维护成本高等缺点。The anti-jamming satellite receiver test usually needs professional equipment such as wireless shielding chamber and satellite navigation signal simulation source as the test environment support. In the whole test environment, a radio wave shielding chamber is required to simulate the radio wave open field, and the radio wave shielding chamber has a large area. , high cost and maintenance costs.
在产品地面测试时，需要对抗干扰卫星接收机进行测试与检测，为了有效屏蔽其他信号，需要在测试过程中为抗干扰卫星接收机建立相对干净的无线测试环境。目前常用的室内开放式测试方法会导致卫星导航信号不可控(如多径信号)，因此采用传统的室内开放式测试方法已无法满足产品测试需求。During the ground test of the product, the anti-jamming satellite receiver needs to be tested and detected. In order to effectively shield other signals, it is necessary to establish a relatively clean wireless test environment for the anti-jamming satellite receiver during the test process. The currently commonly used indoor open test method will lead to uncontrollable satellite navigation signals (such as multipath signals), so the traditional indoor open test method can no longer meet the product testing requirements.
发明内容Contents of the invention
本发明提供了一种用于飞行器抗干扰卫星接收机测试的屏蔽装置，能够解决现有技术中接收机测试方法无法为抗干扰接收机建立相对干净的无线测试环境以及占地面积大、造价和维护成本高的技术问题。The invention provides a shielding device for aircraft anti-jamming satellite receiver testing, which can solve the problems of the receiver testing method in the prior art that cannot establish a relatively clean wireless test environment for the anti-jamming receiver and the large footprint, cost and Technical issues with high maintenance costs.
本发明提供了一种用于飞行器抗干扰卫星接收机测试的屏蔽装置，抗干扰卫星接收机设置在飞行器壳体内，屏蔽装置包括：壳体和天线罩，壳体具有两端开口的容纳腔，天线罩设置在壳体的第一开口端且朝向壳体的第二开口端延伸，壳体的第二开口端与飞行器壳体相贴合，壳体、天线罩以及飞行器壳体共同形成封闭腔体；吸波层，吸波层设置在壳体的内表面，吸波层用于吸收壳体内部的反射电波；发射天线组，发射天线组设置在天线罩上，发射天线组用于向抗干扰卫星接收机发射测试信号；监测接收天线，监测接收天线设置在天线罩上且与抗干扰卫星接收机的接收天线平行设置，监测接收天线用于接收发射天线组发射的测试信号并将接收到的测试信号输出至外部以用于外部实时监测。The invention provides a shielding device for testing an aircraft's anti-jamming satellite receiver. The anti-jamming satellite receiver is arranged in an aircraft casing. The shielding device includes: a casing and a radome, and the casing has a receiving cavity with openings at both ends. The radome is arranged at the first opening end of the housing and extends toward the second opening end of the housing, the second opening end of the housing fits the aircraft housing, and the housing, the radome and the aircraft housing together form a closed cavity body; absorbing layer, the absorbing layer is set on the inner surface of the shell, and the absorbing layer is used to absorb the reflected radio waves inside the shell; the transmitting antenna group, the transmitting antenna group is arranged on the radome, and the transmitting antenna group is used to resist The interference satellite receiver transmits test signals; the monitoring receiving antenna is arranged on the radome and is arranged in parallel with the receiving antenna of the anti-jamming satellite receiver, and the monitoring receiving antenna is used to receive the test signal emitted by the transmitting antenna group and receive The test signal is output to the outside for external real-time monitoring.
进一步地，测试信号包括导航信号和干扰信号，发射天线组包括导航信号发射天线和干扰信号发射天线，导航信号发射天线设置在抗干扰卫星接收机的正上方以用于向抗干扰卫星接收机发射导航信号，干扰信号发射天线与导航信号发射天线间隔设置，干扰信号发射天线用于向抗干扰卫星接收机发射干扰信号。Further, the test signal includes a navigation signal and an interference signal, and the transmitting antenna group includes a navigation signal transmitting antenna and an interference signal transmitting antenna, and the navigation signal transmitting antenna is arranged directly above the anti-jamming satellite receiver for transmitting to the anti-jamming satellite receiver The navigation signal, the interference signal transmitting antenna and the navigation signal transmitting antenna are arranged at intervals, and the interference signal transmitting antenna is used to transmit the interference signal to the anti-jamming satellite receiver.
进一步地，天线罩包括天线罩盖体和天线罩主体，天线罩盖体设置在壳体的第一开口端，监测接收天线的一端设置在天线罩盖体上，监测接收天线的另一端设置在天线罩主体上。Further, the radome includes a radome cover and a radome main body, the radome cover is arranged on the first opening end of the casing, one end of the monitoring receiving antenna is arranged on the radome cover, and the other end of the monitoring receiving antenna is arranged on the on the main body of the radome.
进一步地，屏蔽装置还包括金属弹性屏蔽条，金属弹性屏蔽条设置在壳体的第二开口端与飞行器壳体之间，金属弹性屏蔽条用于实现屏蔽装置与飞行器壳体之间的紧密连接、减小空腔谐振与反射以及防止飞行器壳体受损伤。Further, the shielding device also includes a metal elastic shielding strip, the metal elastic shielding strip is arranged between the second opening end of the casing and the aircraft casing, and the metal elastic shielding strip is used to realize the tight connection between the shielding device and the aircraft casing , Reduce cavity resonance and reflection and prevent damage to the aircraft shell.
进一步地，飞行器壳体为圆柱形结构，壳体的第二开口端由依次连接的第一弧形边、第一直线边、第二弧形边以及第二直线边组成，第一直线边和第二直线边平行设置，第一弧形边和第二弧形边平行设置，第一弧形边和第二弧形边的弧形半径均与飞行器壳体的半径相同。Further, the aircraft casing is a cylindrical structure, and the second open end of the casing is composed of a first arc-shaped side, a first straight-line side, a second arc-shaped side and a second straight-line side connected in sequence, and the first straight-line The side is arranged parallel to the second straight side, the first arc-shaped side is arranged parallel to the second arc-shaped side, and the arc radii of the first arc-shaped side and the second arc-shaped side are the same as the radius of the aircraft shell.
进一步地，屏蔽装置还包括固定绑带，固定绑带的一端与第一直线边连接，固定绑带的另一端绕过飞行器壳体与第二直线边连接，固定绑带用于将屏蔽装置与飞行器壳体相固定。Further, the shielding device also includes a fixed strap, one end of the fixed strap is connected to the first straight side, and the other end of the fixed strap is connected to the second straight side around the aircraft shell, and the fixed strap is used to connect the shielding device to the second straight side. Fixed with the aircraft shell.
进一步地，天线罩盖体与飞行器壳体之间的最小距离大于15cm。Further, the minimum distance between the radome cover and the aircraft shell is greater than 15cm.
进一步地，屏蔽装置还包括第一支撑梁、第二支撑梁和固定杆组，第一支撑梁通过固定杆组与第二支撑梁连接，壳体罩设在第一支撑梁、第二支撑梁和固定杆组外侧。Further, the shielding device also includes a first support beam, a second support beam and a fixed rod group, the first support beam is connected to the second support beam through the fixed rod group, and the housing cover is arranged on the first support beam, the second support beam and the outside of the fixed rod set.
进一步地，监测接收天线包括圆形极化宽温天线。Further, the monitoring receiving antenna includes a circularly polarized wide temperature antenna.
进一步地，屏蔽装置还包括把手，把手设置在天线罩盖体上。Further, the shielding device further includes a handle, and the handle is arranged on the radome cover.
应用本发明的技术方案，提供了一种用于飞行器抗干扰卫星接收机测试的屏蔽装置，该屏蔽装置可为已经安装在飞行器壳体内的接收机在产品检测时提供接收机模拟的电波开阔场，屏蔽真实环境中的电波杂波信号。同时，该屏蔽装置内部设置有监测接收天线，其能够实时监测内部模拟的开阔场中的无线电波信号，并能够同步输出到外部监测设备上进行实时计算与环境监测，为飞行器接收机提供一种可控的无线测试环境。因此，本发明的屏蔽装置相对于现有技术而言，其能够在不改变任何产品结构的前提下，通过增加本发明的屏蔽装置即可实现抗干扰卫星接收机的测试。本发明的屏蔽装置使用及维护方便、结构轻巧，在满足被测产品的测试需求的同时，降低了接收机测试对场地的要求。此外，本发明的实现方法安全可靠，经济灵活，易于实现，短期内能够在产品测试中具备工程应用条件。Applying the technical solution of the present invention, a shielding device for aircraft anti-jamming satellite receiver testing is provided, the shielding device can provide a receiver simulated radio wave open field for the receiver installed in the aircraft shell during product testing , to shield the radio clutter signal in the real environment. At the same time, the shielding device is equipped with a monitoring receiving antenna, which can monitor the radio wave signal in the internal simulated open field in real time, and can synchronously output to the external monitoring equipment for real-time calculation and environmental monitoring, providing an aircraft receiver. Controlled wireless test environment. Therefore, compared with the prior art, the shielding device of the present invention can realize the anti-jamming satellite receiver test by adding the shielding device of the present invention without changing any product structure. The shielding device of the invention is convenient to use and maintain, and has a light and handy structure, and while meeting the test requirements of the tested product, it reduces the requirements for the receiver test site. In addition, the implementation method of the invention is safe, reliable, economical and flexible, easy to implement, and can meet engineering application conditions in product testing in a short period of time.
附图说明Description of drawings
所包括的附图用来提供对本发明实施例的进一步的理解，其构成了说明书的一部分，用于例示本发明的实施例，并与文字描述一起来阐释本发明的原理。显而易见地，下面描述中的附图仅仅是本发明的一些实施例，对于本领域普通技术人员来讲，在不付出创造性劳动的前提下，还可以根据这些附图获得其他的附图。The accompanying drawings are included to provide further understanding of the embodiments of the invention, and constitute a part of the specification, are used to illustrate the embodiments of the invention, and together with the description, explain the principle of the invention. Apparently, the drawings in the following description are only some embodiments of the present invention, and those skilled in the art can obtain other drawings according to these drawings without creative efforts.
图1示出了根据本发明的具体实施例提供的用于飞行器抗干扰卫星接收机测试的屏蔽装置的结构组成示意图；Fig. 1 shows the structural composition schematic diagram of the shielding device for aircraft anti-jamming satellite receiver test provided according to a specific embodiment of the present invention;
图2示出了根据本发明的具体实施例提供的用于飞行器抗干扰卫星接收机测试的屏蔽装置的应用结构示意图；Fig. 2 shows the application structure schematic diagram of the shielding device for aircraft anti-jamming satellite receiver test provided according to a specific embodiment of the present invention;
图3示出了根据本发明的具体实施例提供的用于飞行器抗干扰卫星接收机测试的屏蔽装置的俯视图；Fig. 3 shows the top view of the shielding device for aircraft anti-jamming satellite receiver test provided according to a specific embodiment of the present invention;
图4示出了图3中用于飞行器抗干扰卫星接收机测试的屏蔽装置的左视图；Fig. 4 shows the left side view of the shielding device used for aircraft anti-jamming satellite receiver test among Fig. 3;
图5示出了图3中用于飞行器抗干扰卫星接收机测试的屏蔽装置的主视图。FIG. 5 shows a front view of the shielding device used in the test of the aircraft anti-jamming satellite receiver in FIG. 3 .
其中，上述附图包括以下附图标记：Wherein, the above-mentioned accompanying drawings include the following reference signs:
10、壳体；11、第一壳体；12、第二壳体；20、吸波层；30、发射天线组；40、监测接收天线；50、天线罩盖体；60、金属弹性屏蔽条；70、固定绑带；80、第一支撑梁；90、第二支撑梁；91、第一直线杆；92、第一弧形杆；93、第二直线杆；94、第二弧形杆；100、固定杆组；110、把手；120、天线连接器；121、一号发射天线连接器；122、二号发射天线连接器；123、三号发射天线连接器；124、四号发射天线连接器；125、五号发射天线连接器；126、六号发射天线连接器；127、监测接收天线连接器；128、导航信号发射天线连接器；130、天线固定螺钉；140、固定螺栓卡扣；150、绑带卡扣；160、飞行器壳体。10. Shell; 11. First shell; 12. Second shell; 20. Absorbing layer; 30. Transmitting antenna group; 40. Monitoring receiving antenna; 50. Radome cover; 60. Metal elastic shielding strip ; 70, fixed strap; 80, the first support beam; 90, the second support beam; 91, the first straight bar; 92, the first arc bar; 93, the second straight bar; 94, the second arc Rod; 100, fixed pole group; 110, handle; 120, antenna connector; 121, No. 1 transmitting antenna connector; 122, No. 2 transmitting antenna connector; 123, No. 3 transmitting antenna connector; 124, No. 4 transmitting Antenna connector; 125. No. 5 transmitting antenna connector; 126. No. 6 transmitting antenna connector; 127. Monitoring receiving antenna connector; 128. Navigation signal transmitting antenna connector; 130. Antenna fixing screw; 140. Fixing bolt clip Buckle; 150, strap buckle; 160, aircraft shell.
具体实施方式Detailed ways
需要说明的是，在不冲突的情况下，本申请中的实施例及实施例中的特征可以相互组合。下面将结合本发明实施例中的附图，对本发明实施例中的技术方案进行清楚、完整地描述，显然，所描述的实施例仅仅是本发明一部分实施例，而不是全部的实施例。以下对至少一个示例性实施例的描述实际上仅仅是说明性的，决不作为对本发明及其应用或使用的任何限制。基于本发明中的实施例，本领域普通技术人员在没有作出创造性劳动前提下所获得的所有其他实施例，都属于本发明保护的范围。It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. The following description of at least one exemplary embodiment is merely illustrative in nature and in no way taken as limiting the invention, its application or uses. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.
需要注意的是，这里所使用的术语仅是为了描述具体实施方式，而非意图限制根据本申请的示例性实施方式。如在这里所使用的，除非上下文另外明确指出，否则单数形式也意图包括复数形式，此外，还应当理解的是，当在本说明书中使用术语“包含”和/或“包括”时，其指明存在特征、步骤、操作、器件、组件和/或它们的组合。It should be noted that the terminology used here is only for describing specific implementations, and is not intended to limit the exemplary implementations according to the present application. As used herein, unless the context clearly dictates otherwise, the singular is intended to include the plural, and it should also be understood that when the terms "comprising" and/or "comprising" are used in this specification, they mean There are features, steps, operations, means, components and/or combinations thereof.
除非另外具体说明，否则在这些实施例中阐述的部件和步骤的相对布置、数字表达式和数值不限制本发明的范围。同时，应当明白，为了便于描述，附图中所示出的各个部分的尺寸并不是按照实际的比例关系绘制的。对于相关领域普通技术人员已知的技术、方法和设备可能不作详细讨论，但在适当情况下，所述技术、方法和设备应当被视为授权说明书的一部分。在这里示出和讨论的所有示例中，任何具体值应被解释为仅仅是示例性的，而不是作为限制。因此，示例性实施例的其它示例可以具有不同的值。应注意到：相似的标号和字母在下面的附图中表示类似项，因此，一旦某一项在一个附图中被定义，则在随后的附图中不需要对其进行进一步讨论。The relative arrangements of components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. At the same time, it should be understood that, for the convenience of description, the sizes of the various parts shown in the drawings are not drawn according to the actual proportional relationship. Techniques, methods and devices known to those of ordinary skill in the relevant art may not be discussed in detail, but where appropriate, such techniques, methods and devices should be considered part of the Authorized Specification. In all examples shown and discussed herein, any specific values should be construed as exemplary only, and not as limitations. Therefore, other examples of the exemplary embodiment may have different values. It should be noted that like numerals and letters denote like items in the following figures, therefore, once an item is defined in one figure, it does not require further discussion in subsequent figures.
如图1至图5所示，根据本发明的具体实施例提供了一种用于飞行器抗干扰卫星接收机测试的屏蔽装置，抗干扰卫星接收机设置在飞行器壳体160内，该屏蔽装置包括壳体10、天线罩、吸波层20、发射天线组30和监测接收天线40，壳体10具有两端开口的容纳腔，天线罩设置在壳体10的第一开口端且朝向壳体10的第二开口端延伸，壳体10的第二开口端与飞行器壳体相贴合，壳体10、天线罩以及飞行器壳体共同形成封闭腔体，吸波层20设置在壳体10的内表面，吸波层20用于吸收壳体10内部的反射电波，发射天线组30设置在天线罩上，发射天线组30用于向抗干扰卫星接收机发射测试信号，监测接收天线40设置在天线罩上且与抗干扰卫星接收机的接收天线平行设置，监测接收天线40用于接收发射天线组30发射的测试信号并将接收到的测试信号输出至外部以用于外部实时监测。As shown in Figures 1 to 5, a specific embodiment of the present invention provides a shielding device for aircraft anti-jamming satellite receiver testing, the anti-jamming satellite receiver is arranged in the aircraft housing 160, the shielding device includes The housing 10, the radome, the absorbing layer 20, the transmitting antenna group 30 and the monitoring receiving antenna 40, the housing 10 has an accommodating cavity with openings at both ends, the radome is arranged at the first opening end of the housing 10 and faces the housing 10 The second opening end of the housing 10 is extended, and the second opening end of the housing 10 is attached to the aircraft housing. The housing 10, the radome and the aircraft housing jointly form a closed cavity, and the wave-absorbing layer 20 is arranged in the housing 10. On the surface, the wave-absorbing layer 20 is used to absorb the reflected radio waves inside the casing 10, the transmitting antenna group 30 is arranged on the radome, the transmitting antenna group 30 is used to transmit test signals to the anti-jamming satellite receiver, and the monitoring receiving antenna 40 is arranged on the antenna On the cover and parallel to the receiving antenna of the anti-interference satellite receiver, the monitoring receiving antenna 40 is used to receive the test signal emitted by the transmitting antenna group 30 and output the received test signal to the outside for external real-time monitoring.
应用此种配置方式，提供了一种用于飞行器抗干扰卫星接收机测试的屏蔽装置，该屏蔽装置可为已经安装在飞行器壳体内的接收机在产品检测时提供接收机模拟的电波开阔场，屏蔽真实环境中的电波杂波信号。同时，该屏蔽装置内部设置有监测接收天线，其能够实时监测内部模拟的开阔场中的无线电波信号，并能够同步输出到外部监测设备上进行实时计算与环境监测，为飞行器接收机提供一种可控的无线测试环境。因此，本发明的屏蔽装置相对于现有技术而言，其能够在不改变任何产品结构的前提下，通过增加本发明的屏蔽装置即可实现接收机的测试。本发明的屏蔽装置使用及维护方便、结构轻巧，在满足被测产品的测试需求的同时，降低了接收机测试对场地的要求。此外，本发明的实现方法安全可靠，经济灵活，易于实现，短期内能够在产品测试中具备工程应用条件。Using this configuration method, a shielding device for aircraft anti-jamming satellite receiver testing is provided. The shielding device can provide an open field of radio waves simulated by the receiver during product testing for the receiver already installed in the aircraft shell. Shield the radio clutter signal in the real environment. At the same time, the shielding device is equipped with a monitoring receiving antenna, which can monitor the radio wave signal in the internal simulated open field in real time, and can synchronously output to the external monitoring equipment for real-time calculation and environmental monitoring, providing an aircraft receiver. Controlled wireless test environment. Therefore, compared with the prior art, the shielding device of the present invention can realize receiver testing by adding the shielding device of the present invention without changing any product structure. The shielding device of the invention is convenient to use and maintain, and has a light and handy structure, and while meeting the test requirements of the tested product, it reduces the requirements for the receiver test site. In addition, the implementation method of the invention is safe, reliable, economical and flexible, easy to implement, and can meet engineering application conditions in product testing in a short period of time.
进一步地，在本发明中，为了能够同时测试抗干扰卫星接收机接收导航信号及抗干扰的性能，可将发射天线组30配置为包括导航信号发射天线和干扰信号发射天线，导航信号发射天线设置在抗干扰卫星接收机的正上方以用于向抗干扰卫星接收机发射导航信号，干扰信号发射天线与导航信号发射天线间隔设置，干扰信号发射天线用于向抗干扰卫星接收机发射干扰信号。Further, in the present invention, in order to be able to test the anti-interference satellite receiver to receive navigation signals and anti-jamming performance simultaneously, the transmitting antenna group 30 can be configured to include a navigation signal transmitting antenna and an interference signal transmitting antenna, and the navigation signal transmitting antenna is set Directly above the anti-jamming satellite receiver, it is used to transmit navigation signals to the anti-jamming satellite receiver. The jamming signal transmitting antenna and the navigation signal transmitting antenna are arranged at intervals, and the jamming signal transmitting antenna is used to transmit jamming signals to the anti-jamming satellite receiver.
如图3所示，作为本发明的一个具体实施例，发射天线组30通过天线连接器120设置在天线罩上，发射天线组30包括七个发射天线，其中，一号发射天线通过一号发射天线连接器121连接在天线罩上，二号发射天线通过二号发射天线连接器122连接在天线罩上，三号发射天线通过三号发射天线连接器123连接在天线罩上，四号发射天线通过四号发射天线连接器124连接在天线罩上，五号发射天线通过五号发射天线连接器125连接在天线罩上，六号发射天线通过六号发射天线连接器126，导航信号发射天线通过导航信号发射天线连接器128连接在天线罩上，导航信号发射天线用于向抗干扰卫星接收机发射导航信号，监测接收天线40通过监测接收天线连接器127连接在天线罩上，监测接收天线40用于接收发射天线组30发射的信号并将其输出至外部监测设备。其中，发射天线组30作为屏蔽装置的信号输入口，根据抗干扰卫星接收机接收天线的位置安装发射天线，以使导航信号发射天线设置在抗干扰卫星接收机的正上方。As shown in Figure 3, as a specific embodiment of the present invention, the transmitting antenna group 30 is arranged on the radome through the antenna connector 120, and the transmitting antenna group 30 includes seven transmitting antennas, wherein the No. The antenna connector 121 is connected on the radome, the No. 2 transmitting antenna is connected on the radome by the No. 2 transmitting antenna connector 122, the No. 3 transmitting antenna is connected on the radome by the No. 3 transmitting antenna connector 123, and the No. 4 transmitting antenna The No. 4 transmitting antenna connector 124 is connected to the radome, the No. 5 transmitting antenna is connected to the radome through the No. 5 transmitting antenna connector 125, the No. 6 transmitting antenna is connected to the No. 6 transmitting antenna connector 126, and the navigation signal transmitting antenna passes through the No. 5 transmitting antenna connector 125. Navigation signal transmitting antenna connector 128 is connected on the radome, and navigation signal transmitting antenna is used for transmitting navigation signal to anti-jamming satellite receiver, and monitoring receiving antenna 40 is connected on the radome by monitoring receiving antenna connector 127, and monitoring receiving antenna 40 It is used to receive the signal transmitted by the transmitting antenna group 30 and output it to the external monitoring equipment. Wherein, the transmitting antenna group 30 is used as the signal input port of the shielding device, and the transmitting antenna is installed according to the position of the receiving antenna of the anti-jamming satellite receiver, so that the navigation signal transmitting antenna is arranged directly above the anti-jamming satellite receiver.
其中，考虑信号平衡，一号发射天线连接器121、二号发射天线连接器122、三号发射天线连接器123、四号发射天线连接器124、五号发射天线连接器125和六号发射天线连接器126均匀间隔且呈环形设置在导航信号发射天线连接器128的外侧，一号发射天线连接器121、二号发射天线连接器122、三号发射天线连接器123、四号发射天线连接器124、五号发射天线连接器125和六号发射天线连接器126用于向抗干扰卫星接收机提供干扰信号，以用于测试抗干扰卫星接收机的抗干扰性能。监测接收天线40接收到的信号经过电缆输出到外部监测设备，其安装方式与抗干扰卫星接收机的接收天线平行，同方向接收发射天线组30发射的无线信号，测试中实时监测，当飞行器出现故障时，可在不移动屏蔽装置的前提下，开展故障分析排查工作。Wherein, considering signal balance, No. 1 transmitting antenna connector 121, No. 2 transmitting antenna connector 122, No. 3 transmitting antenna connector 123, No. 4 transmitting antenna connector 124, No. 5 transmitting antenna connector 125 and No. 6 transmitting antenna The connectors 126 are evenly spaced and arranged in a ring on the outside of the navigation signal transmitting antenna connector 128, the No. 1 transmitting antenna connector 121, the No. 2 transmitting antenna connector 122, the No. 3 transmitting antenna connector 123, and the No. 4 transmitting antenna connector. 124. The fifth transmitting antenna connector 125 and the sixth transmitting antenna connector 126 are used to provide interference signals to the anti-jamming satellite receiver for testing the anti-jamming performance of the anti-jamming satellite receiver. The signal received by the monitoring receiving antenna 40 is output to the external monitoring equipment through the cable. Its installation mode is parallel to the receiving antenna of the anti-jamming satellite receiver, and receives the wireless signal emitted by the transmitting antenna group 30 in the same direction. It is monitored in real time during the test. When the aircraft appears In the event of a fault, fault analysis and troubleshooting can be carried out without moving the shielding device.
进一步地，在本发明中，如图1所示，天线罩包括天线罩盖体50和天线罩主体，天线罩盖体50设置在壳体10的第一开口端，监测接收天线40的一端通过监测接收天线连接器127设置在天线罩盖体50上，监测接收天线40的另一端设置在天线罩主体上。监测接收天线40可接收GPS、BDS等多种频点卫星信号，通过接收天线输出接口可将无线电波信号传递到外部监测设备实现环境监测。作为本发明的一个具体实施例，监测接收天线40可采用圆形极化宽温天线，其能够同时接收卫星导航频段的卫星导航信号。监测接收天线40设置在天线罩内侧的发射天线的中间空缺位置，这样既能保证被测卫星导航接收机能够接收信号而监测接收天线40也能同步接收信号，确保信号不相互干涉。Further, in the present invention, as shown in FIG. 1 , the radome includes a radome cover 50 and a radome main body, the radome cover 50 is arranged at the first opening end of the casing 10, and one end of the monitoring receiving antenna 40 passes through The monitoring receiving antenna connector 127 is arranged on the radome cover body 50, and the other end of the monitoring receiving antenna 40 is arranged on the radome main body. The monitoring receiving antenna 40 can receive satellite signals of multiple frequency points such as GPS and BDS, and the radio wave signal can be transmitted to external monitoring equipment through the output interface of the receiving antenna to realize environmental monitoring. As a specific embodiment of the present invention, the monitoring receiving antenna 40 may adopt a circular polarization wide-temperature antenna, which can simultaneously receive satellite navigation signals in the satellite navigation frequency band. The monitoring receiving antenna 40 is arranged in the middle vacant position of the transmitting antenna inside the radome, which can ensure that the satellite navigation receiver under test can receive signals and the monitoring receiving antenna 40 can also receive signals synchronously, ensuring that the signals do not interfere with each other.
在本发明中，如图1所示，屏蔽装置还包括金属弹性屏蔽条60，金属弹性屏蔽条60设置在壳体10的第二开口端与飞行器壳体之间，金属弹性屏蔽条60用于实现屏蔽装置与飞行器壳体之间的紧密连接、减小空腔谐振与反射以及防止飞行器壳体受损伤。作为本发明的一个具体实施例，金属弹性屏蔽条60可设置在壳体10的底部边缘，当飞行器壳体振动时将屏蔽装置固定在飞行器壳体上，金属弹性屏蔽条60能够保证与飞行器壳体紧密连接并且不损伤产品外壳。In the present invention, as shown in FIG. 1 , the shielding device further includes a metal elastic shielding strip 60, which is arranged between the second open end of the casing 10 and the aircraft casing, and the metal elastic shielding strip 60 is used for The tight connection between the shielding device and the aircraft shell is realized, the cavity resonance and reflection are reduced, and the aircraft shell is prevented from being damaged. As a specific embodiment of the present invention, the metal elastic shielding strip 60 can be arranged on the bottom edge of the casing 10, and when the aircraft casing vibrates, the shielding device is fixed on the aircraft casing, and the metal elastic shielding strip 60 can ensure that it is in contact with the aircraft casing. The body is tightly connected and does not damage the product shell.
进一步地，在本发明中，飞行器壳体为圆柱形结构，为了减小空腔谐振，可将壳体10的第二开口端配置为由依次连接的第一弧形边、第一直线边、第二弧形边以及第二直线边组成，第一直线边和第二直线边平行设置，第一弧形边和第二弧形边平行设置，第一弧形边和第二弧形边的弧形半径均与飞行器壳体的半径相同。应用此种配置方式，当将屏蔽装置放置在飞行器壳体160上时，壳体10的第二开口端能够与圆柱形结构的飞行器壳体160紧密贴合，从而能够形成一个完全封闭的立体空间。同时，在壳体10的内壁表面贴满吸波材料，能够有效吸收壳体内部反射电波，有效减小空腔谐振，屏蔽外部杂波和吸收内部反射电波，从而为抗干扰接收机提供一个开阔场景。Further, in the present invention, the aircraft shell is a cylindrical structure, in order to reduce cavity resonance, the second open end of the shell 10 can be configured as a first arc-shaped side, a first straight line connected in sequence , the second arc-shaped side and the second straight-line side, 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, the first arc-shaped side and the second arc-shaped side The arc radii of the sides are all the same as the radii of the aircraft shell. With this arrangement, when the shielding device is placed on the aircraft shell 160, the second open end of the shell 10 can be closely fitted to the cylindrical aircraft shell 160, thereby forming a completely closed three-dimensional space . At the same time, the surface of the inner wall of the housing 10 is covered with absorbing materials, which can effectively absorb reflected radio waves inside the housing, effectively reduce cavity resonance, shield external clutter and absorb internal reflected radio waves, thereby providing an open space for anti-jamming receivers. Scenes.
进一步地，在本发明中，为了实现屏蔽装置与飞行器壳体之间的可靠连接，可将屏蔽装置配置为还包括固定绑带70，固定绑带70的一端与第一直线边连接，固定绑带70的另一端绕过飞行器壳体与第二直线边连接，固定绑带70用于将屏蔽装置与飞行器壳体160相固定。作为本发明的一个具体实施例，如图1所示，在壳体10的下部安装设置有绑带卡扣150，固定绑带70可通过与壳体10上的绑带卡扣150连接以实现屏蔽装置与飞行器壳体160之间的固定连接。Further, in the present invention, in order to realize a reliable connection between the shielding device and the aircraft shell, the shielding device can be configured to further include a fixing strap 70, one end of the fixing strap 70 is connected to the first straight edge, and the fixing The other end of the strap 70 goes around the aircraft shell and is connected to the second straight edge, and the fixing strap 70 is used to fix the shielding device to the aircraft shell 160 . As a specific embodiment of the present invention, as shown in FIG. 1, a strap buckle 150 is installed on 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 A fixed connection between the shielding device and the aircraft shell 160 .
此外，在本发明中，为了避免产生多径信号，可将天线罩盖体50与飞行器壳体之间的最小距离设置为大于15cm。进一步地，在本发明中，为了提高屏蔽装置的结构强度，可将屏蔽装置配置为还包括第一支撑梁80、第二支撑梁90和固定杆组100，第一支撑梁80通过固定杆组100与第二支撑梁90连接，壳体10罩设在第一支撑梁80、第二支撑梁90和固定杆组100外侧。作为本发明的一个具体实施例，第二支撑梁90的结构形状与壳体10的第二开口端的结构形状相同，第二支撑梁90由依次首尾连接的第一直线杆91、第一弧形杆92、第二直线杆93和第二弧形杆94组成，第一支撑梁80为四边形结构，固定杆组100由两根平行设置的竖直杆构成，其中一个竖直杆分别与第一直线杆91和第一支撑梁80连接，另一个竖直杆分别与第二直线杆93和第一支撑梁80连接。In addition, in the present invention, in order to avoid generation of multipath signals, the minimum distance between the radome cover 50 and the aircraft shell can be set to be greater than 15 cm. Further, in the present invention, in order to improve the structural strength of the shielding device, the shielding device can be configured to further include a first support beam 80, a second support beam 90 and a fixed rod set 100, and the first support beam 80 passes through the fixed rod set 100 is connected to the second support beam 90 , and the casing 10 is arranged outside the first support beam 80 , the second support beam 90 and the fixed rod set 100 . As a specific embodiment of the present invention, the structural shape of the second support beam 90 is the same as the structural shape of the second open end of the housing 10, and the second support beam 90 is composed of a first straight rod 91 connected end to end in sequence, a first arc shaped bar 92, the second straight bar 93 and the second arc bar 94, the first support beam 80 is a quadrilateral structure, and the fixed bar group 100 is made up of two parallel vertical bars, one of which is connected to the second vertical bar respectively. A linear rod 91 is connected to the first support beam 80 , and another vertical rod is connected to the second linear rod 93 and the first support beam 80 respectively.
进一步地，在本发明中，为了方便屏蔽装置的移动和携带，可将屏蔽装置配置为还包括把手110，把手110设置在天线罩盖体50上。此外，为了方便装配，可将壳体10配置为包括第一壳体11和第二壳体12，第一壳体11和第二壳体12分别与固定杆组100固定连接以形成具有两端开口的容纳腔的壳体。Further, in the present invention, in order to facilitate the movement and portability of the shielding device, the shielding device may be configured to further include a handle 110 disposed on the radome cover 50 . In addition, for the convenience of 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 with the fixing rod set 100 to form a A housing with an open cavity.
为了对本发明有进一步地了解，下面结合图1至图5对本发明的屏蔽装置进行详细的描述。In order to further understand the present invention, the shielding device of the present invention will be described in detail below with reference to FIGS. 1 to 5 .
如图1至图5所示，作为本发明的一个具体实施例，该屏蔽装置包括壳体10、天线罩、吸波层20、发射天线组30、监测接收天线40、第一支撑梁80、第二支撑梁90、固定杆组100、金属弹性屏蔽条60、固定绑带70和把手110，第一支撑梁80通过固定杆组100与第二支撑梁90连接，壳体10罩设在第一支撑梁80、第二支撑梁90和固定杆组100外侧，以形成一个上部和下部均开口的箱体。天线罩设置在壳体10的第一开口端，天线罩与壳体10相配合以形成一个下部开口的箱体，且该箱体的下部开口与飞行器壳体的形状相同。在壳体10的内侧贴满导航频段的吸波材料，以用于吸收内部反射电波。发射天线组30通过天线固定螺钉130和固定螺栓卡扣140安装设置在天线罩的上部，用于发射无线卫星导航信号及干扰信号。监测接收天线40安装设置在天线罩的内壁，用于接收发射天线组30发射的卫星导航信号及干扰信号并输出外部监测设备。As shown in Figures 1 to 5, as a specific embodiment of the present invention, the shielding device includes a housing 10, a radome, a wave-absorbing layer 20, a transmitting antenna group 30, a monitoring receiving antenna 40, a first support beam 80, The second support beam 90, the fixed rod group 100, the metal elastic shielding bar 60, the fixed strap 70 and the handle 110, the first support beam 80 is connected with the second support beam 90 through the fixed rod group 100, and the housing 10 is covered with the second A supporting beam 80, a second supporting beam 90 and the outer side of the fixed rod group 100 are formed to form a box body with both upper and lower openings. The radome is arranged at the first opening end of the casing 10, and the radome cooperates with the casing 10 to form a box with a lower opening, and the lower opening of the box has the same shape as the aircraft casing. The inner side of the housing 10 is covered with wave-absorbing materials in the navigation frequency band for absorbing internally reflected radio waves. The transmitting antenna group 30 is installed on the upper part of the radome through the antenna fixing screw 130 and the fixing bolt buckle 140, and is used for transmitting wireless satellite navigation signals and interference signals. The monitoring receiving antenna 40 is installed on the inner wall of the radome for receiving satellite navigation signals and interference signals emitted by the transmitting antenna group 30 and outputting external monitoring equipment.
在进行抗干扰卫星接收机的性能测试时，不需要对飞行器进行任何改造或额外增加测试件，使用时只需轻轻的罩在飞行器的抗干扰卫星接收机的接收天线的正上方，用固定绑带70把屏蔽装置固定在飞行器壳体160上即可。此时，屏蔽装置下部与飞行器壳体160接触形成一个完全封闭的立体空间，能够有效减小空腔谐振，屏蔽外部杂波和吸收内部反射电波，从而为抗干扰接收机提供一个开阔场景。屏蔽装置配备监测接收天线40可接收GPS、BDS等多种频点卫星信号，通过产品接收天线输出接口可将无线电波信号传递至外部监测设备实现环境监测。当飞行器出现故障时，可在不移动屏蔽罩的前提下，开展故障分析排查工作。此外，在屏蔽装置的在天线罩盖体50上安装有把手110，方便屏蔽装置的移动和携带。When performing the performance test of the anti-jamming satellite receiver, there is no need to make any modifications to the aircraft or add additional test pieces. When using it, it only needs to be lightly covered directly above the receiving antenna of the anti-jamming satellite receiver of the aircraft. The strap 70 is enough to fix the shielding device on the aircraft shell 160 . At this time, the lower part of the shielding device is in contact with the aircraft shell 160 to form a completely closed three-dimensional space, which can effectively reduce cavity resonance, shield external clutter and absorb internal reflected radio waves, thereby providing an open scene for the anti-jamming receiver. The shielding device is equipped with a monitoring receiving antenna 40 that can receive satellite signals of various frequency points such as GPS and BDS. The radio wave signal can be transmitted to external monitoring equipment through the product receiving antenna output interface to realize environmental monitoring. When the aircraft fails, the fault analysis and troubleshooting can be carried out without moving the shield. In addition, a handle 110 is installed on the radome cover body 50 of the shielding device to facilitate the movement and carrying of the shielding device.
本发明的装置是一种结构完整、工作可靠的小型屏蔽装置，该装置无需供电，结构简单可靠、使用方便、便于携带，可为抗干扰卫星接收机提供一个电波开阔场测试环境，能够满足产品测试环境的需要。经过实际应用验证，本发明的屏蔽装置能够保证装置内部的无线导航信号衰减小于30dB，装置的屏蔽性能大于35dB，减小金属表面反射，同时提高了测试可靠性、可信性、全面性，降低了抗干扰卫星接收机测试对场地的要求。The device of the present invention is a small shielding device with complete structure and reliable operation. The device does not need power supply, has a simple and reliable structure, is convenient to use, and is easy to carry. test environment needs. After practical application verification, the shielding device of the present invention can ensure that the attenuation of the wireless navigation signal inside the device is less than 30dB, the shielding performance of the device is greater than 35dB, reduces the reflection of the metal surface, and improves the reliability, credibility and comprehensiveness of the test at the same time, reducing the The site requirements for the anti-jamming satellite receiver test are specified.
为了便于描述，在这里可以使用空间相对术语，如“在……之上”、“在……上方”、“在……上表面”、“上面的”等，用来描述如在图中所示的一个器件或特征与其他器件或特征的空间位置关系。应当理解的是，空间相对术语旨在包含除了器件在图中所描述的方位之外的在使用或操作中的不同方位。例如，如果附图中的器件被倒置，则描述为“在其他器件或构造上方”或“在其他器件或构造之上”的器件之后将被定位为“在其他器件或构造下方”或“在其他器件或构造之下”。因而，示例性术语“在……上方”可以包括“在……上方”和“在……下方”两种方位。该器件也可以其他不同方式定位(旋转90度或处于其他方位)，并且对这里所使用的空间相对描述作出相应解释。For the convenience of description, spatially relative terms may be used here, such as "on ...", "over ...", "on the surface of ...", "above", etc., to describe the The spatial positional relationship between one device or feature shown and other devices or features. 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 the device in the figures is turned over, devices described as "above" or "above" other devices or configurations would then be oriented "beneath" or "above" the other devices or configurations. under other devices or configurations”. Thus, the exemplary term "above" can encompass both an orientation of "above" and "beneath". The device may be otherwise oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptions used herein interpreted accordingly.
此外，需要说明的是，使用“第一”、“第二”等词语来限定零部件，仅仅是为了便于对相应零部件进行区别，如没有另行声明，上述词语并没有特殊含义，因此不能理解为对本发明保护范围的限制。In addition, it should be noted that the use of words such as "first" and "second" to define components is only for the convenience of distinguishing corresponding components. To limit the protection scope of the present invention.
以上所述仅为本发明的优选实施例而已，并不用于限制本发明，对于本领域的技术人员来说，本发明可以有各种更改和变化。凡在本发明的精神和原则之内，所作的任何修改、等同替换、改进等，均应包含在本发明的保护范围之内。The above descriptions are only preferred embodiments of the present invention, and are not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and changes. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included within the protection scope of the present invention.
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