CN103545594B - A kind of hypersonic aircraft telemetry antenna window erecting device - Google Patents
A kind of hypersonic aircraft telemetry antenna window erecting device Download PDFInfo
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- CN103545594B CN103545594B CN201310460808.3A CN201310460808A CN103545594B CN 103545594 B CN103545594 B CN 103545594B CN 201310460808 A CN201310460808 A CN 201310460808A CN 103545594 B CN103545594 B CN 103545594B
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- 229920001971 elastomer Polymers 0.000 claims abstract description 13
- 239000011152 fibreglass Substances 0.000 claims abstract description 9
- 229920002379 silicone rubber Polymers 0.000 claims abstract description 4
- 239000000463 material Substances 0.000 claims description 4
- 238000009413 insulation Methods 0.000 abstract description 12
- 238000009434 installation Methods 0.000 abstract description 9
- 238000010586 diagram Methods 0.000 description 7
- 238000005259 measurement Methods 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000010453 quartz Substances 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 1
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Abstract
一种高超声速飞行器遥测天线窗安装装置，包括蒙皮、天线窗、天线、隔热垫片、橡胶垫片、天线盒、安装螺钉；天线盒为方形盒体，固连于蒙皮内表面，橡胶垫片为方框形状，置于天线盒底部，天线有一阶梯形平板，下有接线柱，天线置于天线盒内，接线柱穿过天线盒底部的通孔与电缆相连，隔热垫片为方框形状，套接于天线阶梯形平板上，天线窗为方体，内设有阶梯形凹腔，天线窗阶梯形凹腔与天线有一阶梯形平板形状相适应，天线窗套接于天线上；天线窗、玻璃钢垫片、天线、天线盒四角设有安装孔，用安装螺钉拧紧；所述橡胶垫片为硅橡胶材质，所述隔热垫片为玻璃钢垫片。
A hypersonic aircraft telemetry antenna window installation device, including skin, antenna window, antenna, heat insulation gasket, rubber gasket, antenna box, mounting screws; the antenna box is a square box, fixed on the inner surface of the skin, The rubber gasket is in the shape of a square frame and is placed at the bottom of the antenna box. The antenna has a ladder-shaped flat plate with binding posts underneath. The antenna is placed in the antenna box. The binding posts pass through the through holes at the bottom of the antenna box and are connected to the cable. The heat insulation gasket It is in the shape of a square frame and is socketed on the antenna stepped plate. The antenna window is a square body with a stepped concave cavity inside. The stepped concave cavity of the antenna window is adapted to the shape of the antenna with a stepped flat plate. Above; the four corners of the antenna window, fiberglass gasket, antenna, and antenna box are provided with mounting holes, which are tightened with mounting screws; the rubber gasket is made of silicon rubber, and the heat insulation gasket is made of fiberglass gasket.
Description
技术领域technical field
本发明涉及航天飞行器技术领域，具体涉及高超声速飞行器天线窗安装装置。The invention relates to the technical field of aerospace vehicles, in particular to a hypersonic vehicle antenna window installation device.
背景技术Background technique
在航空飞行试验中，主要通过遥测天线实现将测控数据时时传输回地面测控设备的功能，为保证天线正常工作，需要对其进行保护处理，增加天线窗。天线窗为石英材质，具有透波和隔热功能，天线窗为脆性材质，受到冲击载荷容易损坏，需要进行减振处理。In the aviation flight test, the function of transmitting the measurement and control data back to the ground measurement and control equipment is mainly realized through the telemetry antenna. In order to ensure the normal operation of the antenna, it is necessary to protect it and increase the antenna window. The antenna window is made of quartz material, which has the functions of wave transmission and heat insulation. The antenna window is made of brittle material, which is easily damaged by impact load and needs to be damped.
发明内容Contents of the invention
为解决遥测天线窗安装可靠性的要求，本发明提出了一种高超声速飞行器天线窗安装装置。In order to solve the requirements for the installation reliability of the telemetry antenna window, the present invention proposes a hypersonic vehicle antenna window installation device.
一种高超声速飞行器遥测天线窗安装装置，包括蒙皮、天线窗、天线、隔热垫片、橡胶垫片、天线盒、安装螺钉；天线盒为方形盒体，固连于蒙皮内表面，橡胶垫片为方框形状，置于天线盒底部，天线有一阶梯形平板，下有接线柱，天线置于天线盒内，接线柱穿过天线盒底部的通孔与电缆相连，隔热垫片为方框形状，套接于天线阶梯形平板上，天线窗为方体，内设有阶梯形凹腔，天线窗阶梯形凹腔与天线有一阶梯形平板形状相适应，天线窗套接于天线上；天线窗、玻璃钢垫片、天线、天线盒四角设有安装孔，用安装螺钉拧紧；所述橡胶垫片为硅橡胶材质，所述隔热垫片为玻璃钢垫片。A hypersonic aircraft telemetry antenna window installation device, including skin, antenna window, antenna, heat insulation gasket, rubber gasket, antenna box, mounting screws; the antenna box is a square box body, fixed on the inner surface of the skin, The rubber gasket is in the shape of a square frame and placed at the bottom of the antenna box. The antenna has a ladder-shaped flat plate with binding posts underneath. The antenna is placed in the antenna box. The binding posts pass through the through holes at the bottom of the antenna box to connect with the cables. The heat insulation gasket It is in the shape of a square frame and is socketed on the antenna ladder-shaped plate. The antenna window is a square body with a ladder-shaped concave cavity inside. Above; the four corners of the antenna window, fiberglass gasket, antenna, and antenna box are provided with mounting holes, which are tightened with mounting screws; the rubber gasket is made of silicon rubber, and the heat insulation gasket is made of fiberglass gasket.
本发明橡胶垫片为硅橡胶材质，自身形变量大，能够在收到冲击时通过自身的受压变形，降低对天线窗的冲击。隔热垫片为玻璃钢垫片，玻璃钢材料具有很好的隔热作用，将玻璃钢垫片套接于天线上，可以很好的隔绝外部的热量，保护天线。本发明结构简单、安全可靠、成本低、加工周期短，适用于航天飞行器遥测天线窗的隔热、密封、减振。The rubber gasket of the present invention is made of silicon rubber, has a large amount of deformation itself, and can reduce the impact on the antenna window through its own compression deformation when receiving an impact. The heat insulation gasket is a fiberglass gasket, and the fiberglass material has a good heat insulation effect. The fiberglass gasket is sleeved on the antenna, which can well insulate the external heat and protect the antenna. The invention has the advantages of simple structure, safety and reliability, low cost and short processing cycle, and is suitable for heat insulation, sealing and vibration reduction of telemetry antenna windows of aerospace vehicles.
附图说明Description of drawings
图1：本发明遥测天线安装整体结构示意图；Figure 1: a schematic diagram of the overall structure of the installation of the telemetry antenna of the present invention;
图2：本发明遥测天线安装示意图；Figure 2: Schematic diagram of the installation of the telemetry antenna of the present invention;
图3：本发明遥测天线窗安装示意图；Figure 3: a schematic diagram of the installation of the telemetry antenna window of the present invention;
图4：本发明遥测天线窗结构示意图；Figure 4: Schematic diagram of the structure of the telemetry antenna window of the present invention;
图5：本发明遥测天线隔热垫片结构示意图；Figure 5: Schematic diagram of the structure of the heat insulation gasket for the telemetry antenna of the present invention;
图6：本发明遥测天线橡胶垫片结构示意图；Figure 6: Schematic diagram of the structure of the telemetry antenna rubber gasket of the present invention;
图7：本发明遥测天线盒结构示意图。Fig. 7: Schematic diagram of the structure of the telemetry antenna box of the present invention.
具体实施方式Detailed ways
下面结合附图对本发明做进一步描述。The present invention will be further described below in conjunction with the accompanying drawings.
一种高超声速飞行器遥测天线窗安装装置，包括蒙皮1、天线窗2、天线3、隔热垫片4、橡胶垫片5、天线盒6、安装螺钉7。如图1、图2、图3所示。A hypersonic vehicle telemetry antenna window installation device, comprising a skin 1, an antenna window 2, an antenna 3, a thermal insulation gasket 4, a rubber gasket 5, an antenna box 6, and a mounting screw 7. As shown in Figure 1, Figure 2, and Figure 3.
天线盒6为方形盒体，如图7所示，固连于蒙皮1内表面，橡胶垫片5为方框形状，如图6所示，置于天线盒6底部，天线3有一阶梯形平板，下有接线柱，天线3置于天线盒6内，接线柱穿过天线盒6底部的通孔与电缆相连，隔热垫片4为方框形状，如图5所示，套接于天线3阶梯形平板上，天线窗2为方体，如图4所示，内设有阶梯形凹腔，天线窗2阶梯形凹腔与天线3有一阶梯形平板形状相适应，天线窗2套接于天线3上。天线窗2、玻璃钢垫片4、天线3、天线盒6四角设有安装孔，用安装螺钉7拧紧。Antenna box 6 is a square box body, as shown in Figure 7, fixedly connected to the inner surface of skin 1, rubber gasket 5 is a square frame shape, as shown in Figure 6, placed at the bottom of antenna box 6, antenna 3 has a stepped There is a flat panel with a binding post below, and the antenna 3 is placed in the antenna box 6. The binding post passes through the through hole at the bottom of the antenna box 6 and is connected to the cable. On the antenna 3 stepped flat plate, the antenna window 2 is a square body, as shown in Figure 4, is provided with a stepped concave cavity, the antenna window 2 stepped concave cavity is adapted to the antenna 3 with a stepped flat plate shape, and the antenna window 2 sets connected to antenna 3. Antenna window 2, fiberglass gasket 4, antenna 3, and antenna box 6 four corners are provided with mounting holes, and are tightened with mounting screws 7.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310460808.3A CN103545594B (en) | 2013-09-30 | 2013-09-30 | A kind of hypersonic aircraft telemetry antenna window erecting device |
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| CN201310460808.3A CN103545594B (en) | 2013-09-30 | 2013-09-30 | A kind of hypersonic aircraft telemetry antenna window erecting device |
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| CN103545594A CN103545594A (en) | 2014-01-29 |
| CN103545594B true CN103545594B (en) | 2015-11-25 |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107364566B (en) * | 2017-06-28 | 2020-01-03 | 湖北航天技术研究院总体设计所 | Heat-proof antenna opening cover combined structure of outdoor detachable antenna |
| CN109216880B (en) * | 2018-09-03 | 2021-07-13 | 北京航天长征飞行器研究所 | An antenna window assembly suitable for long-term aerodynamic thermal environment and its design method |
| CN109546283A (en) * | 2018-10-25 | 2019-03-29 | 江苏云端智能科技有限公司 | A kind of antenna outer connecting device of aircraft |
| CN112960102B (en) * | 2021-03-18 | 2022-12-13 | 上海机电工程研究所 | Aircraft conical cabin integrated equipment installation opening cover and installation method |
| CN114421124B (en) * | 2021-12-08 | 2025-03-14 | 北京机电工程研究所 | Airborne antenna installation structure and high-speed aircraft |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3977004A (en) * | 1975-06-16 | 1976-08-24 | The United States Of America As Represented By The Secretary Of The Navy | Aircraft VLF/LF/MF window antenna receiving system |
| EP0195244A1 (en) * | 1985-02-13 | 1986-09-24 | Grumman Aerospace Corporation | Aircraft skin antenna |
| US4626858A (en) * | 1983-04-01 | 1986-12-02 | Kentron International, Inc. | Antenna system |
| JPH08181518A (en) * | 1994-12-26 | 1996-07-12 | Nec Eng Ltd | Heat resistant antenna |
| EP0989628B1 (en) * | 1998-09-14 | 2003-08-06 | Ace Technology | Patch antenna having flexed ground plate |
| FR2933378B1 (en) * | 2008-07-04 | 2010-08-27 | Airbus France | METHOD OF MOUNTING AN ANTENNA ON AN AIRCRAFT, AND AN AIRCRAFT EQUIPPED WITH AT LEAST ONE ANTENNA MOUNTED FOLLOWING SAID METHOD |
| CN202817189U (en) * | 2012-09-26 | 2013-03-20 | 北京航天长征飞行器研究所 | S-band broadband wide beam aircraft antenna |
-
2013
- 2013-09-30 CN CN201310460808.3A patent/CN103545594B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3977004A (en) * | 1975-06-16 | 1976-08-24 | The United States Of America As Represented By The Secretary Of The Navy | Aircraft VLF/LF/MF window antenna receiving system |
| US4626858A (en) * | 1983-04-01 | 1986-12-02 | Kentron International, Inc. | Antenna system |
| EP0195244A1 (en) * | 1985-02-13 | 1986-09-24 | Grumman Aerospace Corporation | Aircraft skin antenna |
| JPH08181518A (en) * | 1994-12-26 | 1996-07-12 | Nec Eng Ltd | Heat resistant antenna |
| EP0989628B1 (en) * | 1998-09-14 | 2003-08-06 | Ace Technology | Patch antenna having flexed ground plate |
| FR2933378B1 (en) * | 2008-07-04 | 2010-08-27 | Airbus France | METHOD OF MOUNTING AN ANTENNA ON AN AIRCRAFT, AND AN AIRCRAFT EQUIPPED WITH AT LEAST ONE ANTENNA MOUNTED FOLLOWING SAID METHOD |
| CN202817189U (en) * | 2012-09-26 | 2013-03-20 | 北京航天长征飞行器研究所 | S-band broadband wide beam aircraft antenna |
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| CN103545594A (en) | 2014-01-29 |
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