CN115370746A - Dynamic sealing structure of airborne pod - Google Patents
Dynamic sealing structure of airborne pod Download PDFInfo
- Publication number
- CN115370746A CN115370746A CN202210949076.3A CN202210949076A CN115370746A CN 115370746 A CN115370746 A CN 115370746A CN 202210949076 A CN202210949076 A CN 202210949076A CN 115370746 A CN115370746 A CN 115370746A
- Authority
- CN
- China
- Prior art keywords
- screw
- nacelle
- optical system
- cabin body
- dynamic seal
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000007789 sealing Methods 0.000 title abstract description 11
- 230000003287 optical effect Effects 0.000 claims abstract description 38
- 230000035939 shock Effects 0.000 claims abstract description 26
- 238000010521 absorption reaction Methods 0.000 claims abstract description 19
- 238000009434 installation Methods 0.000 claims abstract description 6
- 239000002184 metal Substances 0.000 claims description 4
- 230000000712 assembly Effects 0.000 claims 2
- 238000000429 assembly Methods 0.000 claims 2
- 238000006073 displacement reaction Methods 0.000 abstract description 4
- 238000000034 method Methods 0.000 abstract description 4
- 238000012423 maintenance Methods 0.000 abstract description 2
- 238000013016 damping Methods 0.000 abstract 1
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
- F16J15/32—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings
- F16J15/3268—Mounting of sealing rings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
- F16J15/32—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings
- F16J15/3204—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings with at least one lip
- F16J15/3224—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings with at least one lip capable of accommodating changes in distances or misalignment between the surfaces, e.g. able to compensate for defaults of eccentricity or angular deviations
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
- F16J15/32—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings
- F16J15/3284—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings characterised by their structure; Selection of materials
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention relates to the field of mechanical seal design, in particular to a dynamic seal structure of an airborne pod; the nacelle main machine comprises an upper nacelle body, a middle nacelle body, a lower nacelle body, a shock absorption seat, an optical system and a screw assembly. According to the invention, the nacelle host adopts a form of combining the sub-nacelle body and the dynamic seal assembly, so that on one hand, the installation and later-stage maintenance and debugging of the internal structure are facilitated, and on the other hand, the installation of the dynamic seal assembly is facilitated; the dynamic sealing component is arranged, so that the problem of the whole machine air tightness of the conventional airborne nacelle is solved, and meanwhile, the dynamic sealing component can effectively eliminate the difference of the displacement generated by the optical system through the damping seat in the use process, so that the air tightness and the stability of the whole airborne nacelle are ensured.
Description
Technical Field
The invention relates to the field of mechanical seal design, in particular to a dynamic seal structure of an airborne pod.
Background
Airborne pods are the main functional assembly of an aircraft performing surveillance, reconnaissance, filming and other tasks, and are usually mounted on the exterior of the aircraft in order to increase the field of view of the pod. The airtightness of the nacelle is directly related to the performance index of the nacelle when performing the flight mission. In the conventional structure design of the onboard pod, the problem of the sealing structure is generally solved by increasing the size of the pod, so that the overall size and mass of the pod are increased, and the light weight and the miniaturization of the onboard pod are seriously restricted. Therefore, a sealing structure and a mounting method which are beneficial to the miniaturization and the light weight of the airborne pod are urgently needed.
Disclosure of Invention
The invention aims to provide a dynamic sealing structure of an airborne pod, which aims to solve the problem of integral air tightness of the airborne pod.
In order to achieve the purpose, the technical scheme of the invention is as follows:
the utility model provides a dynamic seal structure of airborne nacelle, includes nacelle host computer and dynamic seal subassembly, the nacelle host computer includes the cabin body, well cabin body, lower cabin body, shock attenuation seat, optical system and screw subassembly, all through screw subassembly fixed connection between the cabin body and the well cabin body, between well cabin body and the lower cabin body, the upper end of shock attenuation seat passes through screw subassembly fixed connection in well cabin body inner wall below, the lower extreme of shock attenuation seat passes through screw subassembly and lower cabin body inner wall and dynamic seal subassembly fixed connection, the inner chamber installation optical system of shock attenuation seat, just pass through screw subassembly fixed connection between shock attenuation seat and the optical system, the upper end of optical system passes through screw subassembly fixed connection on well cabin body inner wall, optical system is T type structure, is located optical system's step position passes through screw subassembly fixed connection dynamic seal subassembly.
Specifically, the dynamic seal subassembly includes and pushes up the outer lane, goes up outer inner circle, soft rubber sleeve, pushes down the inner circle and pushes down the outer lane, it is the metal ring to go up to press the outer lane, go up outer inner circle, push down the inner circle and push down the outer lane and make, first through-hole has all been seted up to the upper end of going up to press the outer lane, going up outer inner circle, soft rubber sleeve, and wear to establish outer inner circle, soft rubber sleeve's upper end, go up to press the outer lane and optical system's step position fixed connection in proper order through the screw subassembly, the lower extreme of soft rubber sleeve, push down the inner circle, push down the outer lane and the shock mount all seted up the second through-hole, wear to establish in proper order through the screw subassembly and push down the lower extreme of inner circle, soft rubber sleeve, push down the outer lane, shock mount and cabin body fixed connection down.
Specifically, the screw subassembly includes screw, flat pad and bullet pad, the screw thread end of screw is connected with flat pad of bullet in proper order.
Specifically, the top of the upper cabin body is fixedly connected with a lifting lug.
Specifically, the lower end of the optical system extends to the outside along the lower end of the lower cabin body.
The invention has the beneficial effects that:
(1) According to the invention, the nacelle host adopts a form of combining the sub-nacelle body with the dynamic seal assembly, so that the installation and later maintenance and debugging of an internal structure are facilitated on one hand, and the installation of the dynamic seal assembly is facilitated on the other hand;
(2) The dynamic sealing assembly is arranged, so that the problem of the whole machine air tightness of the conventional airborne nacelle is solved, the optical system generates displacement through the shock absorption seat in the using process, and the dynamic sealing assembly can effectively eliminate the displacement, so that the air tightness and the stability of the whole airborne nacelle are ensured.
Drawings
FIG. 1 is a schematic view of a nacelle body according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a dynamic seal assembly according to an embodiment of the present invention.
Reference numerals are as follows: 1.0-01 parts of upper cabin body, 1.0-02 parts of middle cabin body, 1.0-03 parts of lower cabin body, 1.0-04 parts of shock-absorbing seat, 1.0-05 parts of screw component, 2.0 parts of optical system, 3.0 parts of dynamic seal component, 4.0 parts of lifting lug, 3.0-01 parts of upper pressing outer ring, 3.0-02 parts of upper outer inner ring, 3.0-03 parts of soft rubber sleeve, 3.0-04 parts of lower pressing inner ring and 3.0-05 parts of lower pressing outer ring.
Detailed Description
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. All other embodiments, which can be obtained by a person skilled in the art without making any creative effort based on the embodiments in the present invention, belong to the protection scope of the present invention.
Referring to the attached drawings 1-2, the dynamic seal structure of the onboard pod comprises a pod host and a dynamic seal assembly 3.0, wherein the pod host comprises an upper pod body 1.0-01, a middle pod body 1.0-02, a lower pod body 1.0-03, shock absorption seats 1.0-04, an optical system 2.0 and a screw assembly 1.0-05, the upper pod body 1.0-01 and the middle pod body 1.0-02, the middle pod body 1.0-02 and the lower pod body 1.0-03 are fixedly connected through the screw assembly 1.0-05, the upper end of the shock absorption seat 1.0-04 is fixedly connected below the inner wall of the middle pod body 1.0-02 through the screw assembly 1.0-05, the lower end of the shock absorption seat 1.0-04 is fixedly connected with the inner wall of the lower cabin body 1.0-03 and the dynamic seal assembly 3.0 through a screw assembly 1.0-05, an optical system 2.0 is installed in an inner cavity of the shock absorption seat 1.0-04, the shock absorption seat 1.0-04 is fixedly connected with the optical system 2.0 through a screw assembly 1.0-05, the upper end of the optical system 2.0 is fixedly connected to the inner wall of the middle cabin body 1.0-02 through a screw assembly 1.0-05, the optical system 2.0 is of a T-shaped structure, and the dynamic seal assembly 3.0 is fixedly connected to the step position of the optical system 2.0 through the screw assembly 1.0-05.
Furthermore, countersunk holes are arranged on the side wall of the upper cabin body 1.0-01, and the upper cabin body 1.0-01 and the middle cabin body 1.0-02 are fixed by screw components 1.0-05; the upper surface and the lower surface of the middle cabin body 1.0-02 are both provided with threaded holes, the threaded holes positioned on the upper surface of the middle cabin body 1.0-02 and the countersunk holes positioned on the upper cabin body 1.0-01 are matched and installed, the middle cabin body 1.0-02 and the upper cabin body 1.0-01 are fixed through screw components 1.0-05, two groups of threaded holes are arranged on the upper surface of the middle cabin body 1.0-02, one group of threaded holes is connected with the lower cabin body 1.0-03 through the screw components 1.0-05, and the other group of threaded holes is connected with the shock-absorbing seat 1.0-04 through the screw components 1.0-05; the inner side of the middle cabin body 1.0-02 is a cavity body, the bottom surface of the inner side of the cavity body is provided with a threaded hole, and the optical system 2.0 is fixed through a screw assembly 1.0-05; the side wall of the lower cabin body 1.0-03 is provided with two groups of counter bores, wherein one group of counter bores is connected with the middle cabin body 1.0-02 through screw components 1.0-05, the other group of counter bores penetrates through the shock absorption seat 1.0-04 through screw components 1.0-05 to be connected with the dynamic seal component 3.0, and the inner side of the lower cabin body 1.0-03 is a cavity body for installing airborne nacelle components; the upper surface of the shock absorption seat 1.0-04 is provided with a through hole which is connected with the middle cabin body 1.0-02 through a screw component 1.0-05, the lower surface of the shock absorption seat 1.0-04 is provided with a through hole which is connected with a dynamic seal component 3.0 through a screw component 1.0-05, the middle side of the shock absorption seat 1.0-04 is provided with a through hole which is connected with an optical system 2.0 through a screw component 1.0-05; the interior of the shock absorption seat 1.0-04 is a cavity used for installing an optical system 2.0; the upper end of an optical system 2.0 is provided with a through hole which is connected with a middle cabin body 1.0-02 through a screw component 1.0-05, a threaded hole is arranged at the step position of the optical system 2.0 and is connected with a dynamic sealing component 3.0 through the screw component 1.0-05, the side wall of the optical system 2.0 is provided with a threaded hole and is connected with a shock absorption seat 1.0-04 through the screw component 1.0-05, and a pod host machine of the device adopts a mode of combining a sub cabin body and the dynamic sealing component 3.0, so that the main structure of the whole airborne pod is convenient to disassemble, assemble and debug. Specifically, the dynamic seal assembly 3.0 comprises an upper pressing outer ring 3.0-01, an upper outer inner ring 3.0-02, a soft rubber sleeve 3.0-03, a lower pressing inner ring 3.0-04 and a lower pressing outer ring 3.0-05, the upper pressing outer ring 3.0-01, the upper outer inner ring 3.0-02, the lower pressing inner ring 3.0-04 and the lower pressing outer ring 3.0-05 are all made of metal rings, the upper ends of the upper pressing outer ring 3.0-01, the upper outer inner ring 3.0-02 and the soft rubber sleeve 3.0-03 are all provided with first through holes, the upper ends of the upper pressing outer ring 3.0-02, the soft rubber sleeve 3.0-03, the upper end of the upper pressing outer ring 3.0-01 and the optical system 2.0 are fixedly connected with the step positions of the screw assembly 1.0-05, the lower end of the soft rubber sleeve 3.0-03, the lower pressing inner ring 3.0-04, the lower pressing outer ring 3.0-05 and the shock absorption seat are all provided with second through holes, the lower end of the soft rubber sleeve 3.0-05, the lower pressing outer ring 3.0-04, the shock absorption seat is fixedly connected with the lower pressing outer ring 3.0-05, the soft rubber sleeve and the soft rubber assembly, and the lower pressing seat 1.0-0-05.
Furthermore, a dynamic seal assembly 3.0 related by the invention is mainly connected with an optical system 2.0 and a cabin body to form the internal seal of the whole cabin body, in the using process of the whole airborne pod, the displacement formed by the vibration of the optical system 2.0 is subjected to shape-eliminating seal by the dynamic seal assembly 3.0, so that the whole airborne pod stably operates, the dynamic seal assembly 3.0 consists of an upper pressing outer ring 3.0-01, an upper outer inner ring 3.0-02, a soft rubber sleeve 3.0-03, a lower pressing inner ring 3.0-04 and a lower pressing outer ring 3.0-05, wherein the upper pressing outer ring 3.0-01, the upper outer ring 3.0-02, the lower pressing inner ring 3.0-04 and the lower pressing outer ring 3.0-05 are all made of metal rings, the upper surface of the upper pressing outer ring 3.0-01 is provided with a group of countersunk holes and a group of through holes, the countersunk holes are connected with the upper pressing inner ring 3.0-02 of the upper outer ring 3.0-03 and the soft rubber sleeve 3.0-03 through holes of the upper pressing outer ring 3.0-03, and the soft rubber sleeve 3.0-05, and the upper pressing outer ring 3.0-01 are sequentially connected with the screw components through holes at the upper end of the soft rubber sleeve, and the upper pressing outer ring 3.0-0-05; the soft rubber sleeve 3.0-03 is manufactured by opening a die, and has good flexibility and environmental adaptability; the lower surface of the lower pressing outer ring 3.0-05 is provided with a group of counter bores and a group of through holes, the counter bores are connected with the lower pressing inner ring 3.0-04 through screw components 1.0-05, meanwhile, the lower end of the soft rubber sleeve 3.0-03, the lower pressing inner ring 3.0-04, the lower pressing outer ring 3.0-05 and the shock absorption seat 1.0-04 are provided with second through holes matched with the through holes on the lower pressing outer ring 3.0-05, and the lower pressing inner ring 3.0-04, the lower end of the soft rubber sleeve 3.0-03, the lower pressing outer ring 3.0-05 and the shock absorption seat 1.0-04 are sequentially arranged through the screw components 1.0-05 and fixedly connected with the lower cabin body 1.0-03.
Specifically, the screw assembly 1.0-05 comprises a screw, a flat pad and an elastic pad, and the threaded end of the screw is connected with the elastic pad and the flat pad in sequence.
Further, the screw assembly 1.0-05 comprises a screw, a flat pad and an elastic pad and is used for connecting and fixing devices.
Specifically, the top of the upper cabin body 1.0-01 is fixedly connected with a lifting lug 4.0.
Furthermore, the lifting lug 4.0 is convenient for subsequent hoisting use or performance debugging.
Specifically, the lower end of the optical system 2.0 extends to the outside along the lower end of the lower chamber 1.0-03.
Further, the optical system 2.0 according to the present invention is a prior art, including but not limited to an onboard pod optical system 2.0 for high-altitude operation in reference to CN103852889A, which is not described herein again, and the present invention is directed to structural features of a dynamic seal structure of an onboard pod.
Finally, the above embodiments are only for illustrating the technical solutions of the present invention and not for limiting, although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that modifications or equivalent substitutions may be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all of them should be covered in the claims of the present invention.
Claims (5)
1. The utility model provides a dynamic seal structure of airborne nacelle, includes nacelle host computer and dynamic seal subassembly, its characterized in that, the nacelle host computer includes the cabin body, well cabin body, lower cabin body, cushion socket, optical system and screw subassembly, all through screw subassembly fixed connection between the cabin body and the well cabin body, between well cabin body and the lower cabin body, the upper end of cushion socket passes through screw subassembly fixed connection in well cabin body inner wall below, the lower extreme of cushion socket passes through screw subassembly and lower cabin body inner wall and dynamic seal subassembly fixed connection, the inner chamber installation optical system of cushion socket, just pass through screw subassembly fixed connection between cushion socket and the optical system, the upper end of optical system passes through screw subassembly fixed connection on well cabin body inner wall, optical system is T type structure, is located the step position of optical system passes through screw subassembly fixed connection dynamic seal subassembly.
2. The dynamic seal structure of the onboard nacelle according to claim 1, wherein the dynamic seal assembly comprises an upper pressing outer ring, an upper outer inner ring, a soft rubber sleeve, a lower pressing inner ring and a lower pressing outer ring, the upper outer inner ring, the lower pressing inner ring and the lower pressing outer ring are all made of metal circular rings, first through holes are formed in the upper ends of the upper pressing outer ring, the upper outer inner ring and the soft rubber sleeve, the upper outer ring, the upper pressing outer ring and the step position of the optical system are fixedly connected through screw assemblies, second through holes are formed in the lower end of the soft rubber sleeve, the lower pressing inner ring, the lower pressing outer ring and the shock absorption seat, and the lower pressing inner ring, the lower pressing outer ring, the shock absorption seat and the lower nacelle body are fixedly connected through screw assemblies.
3. The dynamic seal structure of the airborne pod as claimed in any one of claims 1-2, wherein said screw assembly comprises a screw, a flat pad and a spring pad, and the screw end of said screw is connected with the spring pad and the flat pad in turn.
4. The dynamic seal structure of the airborne nacelle according to claim 1, wherein a lifting lug is fixedly connected to the top of the upper nacelle body.
5. The dynamic seal structure of an airborne pod according to claim 1, wherein a lower end of the optical system extends to the outside along a lower end of the lower body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210949076.3A CN115370746B (en) | 2022-08-09 | 2022-08-09 | Dynamic sealing structure of airborne nacelle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210949076.3A CN115370746B (en) | 2022-08-09 | 2022-08-09 | Dynamic sealing structure of airborne nacelle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115370746A true CN115370746A (en) | 2022-11-22 |
| CN115370746B CN115370746B (en) | 2024-06-11 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210949076.3A Active CN115370746B (en) | 2022-08-09 | 2022-08-09 | Dynamic sealing structure of airborne nacelle |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030071170A1 (en) * | 2001-10-15 | 2003-04-17 | Hilbert Andrea A. | Reconfigurable reconnaissance pod system |
| CN200974004Y (en) * | 2006-11-16 | 2007-11-14 | 武汉钢铁(集团)公司 | Flexible sealed shaker dust eliminating machine group |
| CN103318419A (en) * | 2013-05-20 | 2013-09-25 | 西安电子工程研究所 | Seal structure for sleeve connection of pod body and antenna housing of onboard electronic pod |
| US20160068248A1 (en) * | 2014-09-10 | 2016-03-10 | Raytheon Company | Moving conformal window for large aperture optics on aircraft mounted pods |
| CN110871898A (en) * | 2019-11-08 | 2020-03-10 | 武汉华中天经通视科技有限公司 | Temperature measurement type photoelectric pod |
| CN110873187A (en) * | 2018-08-29 | 2020-03-10 | 中国科学院长春光学精密机械与物理研究所 | Sealing vibration damper for airborne photoelectric equipment and airborne photoelectric equipment |
| CN212479996U (en) * | 2020-04-15 | 2021-02-05 | 北京国联康瑞电子技术有限公司 | Bidirectional damping shock absorption base |
| CN216200456U (en) * | 2021-08-12 | 2022-04-05 | 英飞睿(成都)微系统技术有限公司 | Photoelectric pod sealing structure and unmanned aerial vehicle |
-
2022
- 2022-08-09 CN CN202210949076.3A patent/CN115370746B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030071170A1 (en) * | 2001-10-15 | 2003-04-17 | Hilbert Andrea A. | Reconfigurable reconnaissance pod system |
| CN200974004Y (en) * | 2006-11-16 | 2007-11-14 | 武汉钢铁(集团)公司 | Flexible sealed shaker dust eliminating machine group |
| CN103318419A (en) * | 2013-05-20 | 2013-09-25 | 西安电子工程研究所 | Seal structure for sleeve connection of pod body and antenna housing of onboard electronic pod |
| US20160068248A1 (en) * | 2014-09-10 | 2016-03-10 | Raytheon Company | Moving conformal window for large aperture optics on aircraft mounted pods |
| CN110873187A (en) * | 2018-08-29 | 2020-03-10 | 中国科学院长春光学精密机械与物理研究所 | Sealing vibration damper for airborne photoelectric equipment and airborne photoelectric equipment |
| CN110871898A (en) * | 2019-11-08 | 2020-03-10 | 武汉华中天经通视科技有限公司 | Temperature measurement type photoelectric pod |
| CN212479996U (en) * | 2020-04-15 | 2021-02-05 | 北京国联康瑞电子技术有限公司 | Bidirectional damping shock absorption base |
| CN216200456U (en) * | 2021-08-12 | 2022-04-05 | 英飞睿(成都)微系统技术有限公司 | Photoelectric pod sealing structure and unmanned aerial vehicle |
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|---|---|
| CN115370746B (en) | 2024-06-11 |
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