CN213414241U - High-speed aircraft outward vision camera heat protection device - Google Patents
High-speed aircraft outward vision camera heat protection device Download PDFInfo
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- CN213414241U CN213414241U CN202021548406.0U CN202021548406U CN213414241U CN 213414241 U CN213414241 U CN 213414241U CN 202021548406 U CN202021548406 U CN 202021548406U CN 213414241 U CN213414241 U CN 213414241U
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Abstract
The utility model discloses a high-speed aircraft outward vision camera heat protector includes the aircraft bulkhead, the speculum protective housing, external perspective glass, the speculum fixed pin, the speculum, built-in perspective glass, the camera support, the camera shock absorber, the camera is sealed to fill up, camera cable and electric connector, the speculum protective housing is installed in aircraft cabin outside, external perspective glass fixes in the speculum protective housing, two speculum fixed pins are installed respectively inside the speculum protective housing, be used for installing the speculum, one side of speculum reflection light is towards external perspective glass, built-in perspective glass installs at the aircraft bulkhead. The utility model discloses at aircraft cabin outside assembly's size, it is littleer to install the mode at the aircraft outside than direct camera, and the pneumatic heating volume that consequently produces is littleer, and is littleer to the influence of the pneumatic appearance of aircraft.
Description
Technical Field
The utility model relates to a high-speed aircraft outward vision camera heat protector belongs to the structure heat protection technical field.
Background
During the execution of a mission of an aircraft, it is sometimes necessary to photograph changes in the state of the outer surface of the aircraft fuselage and the external environment. In the process of high-speed flight of the aircraft, the outer surface of the cabin wall of the aircraft is rubbed with air at high speed to generate pneumatic heating, so that the temperature of the outer surface of the fuselage of the aircraft is very high and can reach hundreds to thousands of degrees centigrade. The maximum temperature of electronic components in the camera, which can normally work, is 125 ℃, which is far lower than the environmental temperature in the flight process, so that the camera needs to be thermally protected, and the working environmental temperature of the camera is kept within an allowable range.
There are two conventional ways of thermal protection:
one is to install the camera outside the aircraft, wrap up the thermal insulation material, such as quartz wool or heat insulating tile etc. around the camera, place the translucent quartz glass in the front end of the lens, slow down the heat to the camera conduction, the shortcoming of this kind of mode is that the volume of placing the extravehicular subassembly is great, and is great to the influence of aircraft appearance, makes the pneumatic characteristic of aircraft take place great change, in addition in order to maintain the operating temperature of camera, needs to use thicker thermal insulation material, and the increase of material volume leads to the pneumatic heating capacity increase on the contrary.
The other working principle is similar to that of an endoscope, a camera is installed in an aircraft cabin, a small-sized lens is independently placed outside the cabin, the lens is connected with the camera through a flexible optical fiber, heat insulation materials are wrapped around the lens, and transparent quartz glass is placed at the front end of the lens.
SUMMERY OF THE UTILITY MODEL
The utility model provides a technical problem be: the defects of the prior art are overcome, the high-speed aircraft outward-looking camera thermal protection device is provided, and the device has the characteristics of reducing the working environment temperature of the outward-looking camera and influencing the pneumatic appearance of the aircraft.
The technical solution of the utility model is that:
a high speed aircraft outward view camera thermal protection device comprising: the device comprises an aircraft bulkhead, a reflector protective shell, external perspective glass, a reflector fixing pin, a reflector, internal perspective glass, a camera bracket, a camera shock absorber, a camera sealing gasket and a camera cable;
the reflector protection shell is arranged outside the aircraft cabin and connected with the cabin wall of the aircraft, and the included angle between the plane provided with the external perspective glass and the cabin wall of the aircraft is A;
the external perspective glass is fixed in the through hole of the reflector protection shell by using high-temperature glue and is flush with the outer surface of the reflector protection shell, and the high-temperature glue can weaken the high-frequency vibration transmitted by the reflector protection shell to the external perspective glass;
the two reflector fixing pins are respectively installed in the reflector protection shell, the reflector is fixed between the two reflector fixing pins, one side of the light reflected by the reflector faces the external perspective glass, and the included angle between the side and the cabin wall of the aircraft is B;
the built-in perspective glass is fixed in the through hole of the cabin wall of the aircraft by using high-temperature glue and is flush with the outer surface of the cabin wall of the aircraft, and the high-temperature glue simultaneously plays a role in weakening high-frequency vibration transmitted by the cabin wall of the aircraft to the built-in perspective glass;
the camera support is fixed on the inner side of the cabin wall of the aircraft, the camera is fixed on the camera support through a camera shock absorber, a lens of the camera faces to the built-in perspective glass, a camera sealing gasket is laid between the camera support and the camera and fixed on one side of the camera support, and a camera cable penetrates through holes of the camera support and the camera sealing gasket and is connected with the camera and equipment in the cabin of the aircraft;
incident light irradiates the reflector through the external perspective glass, and after reflection, the incident light penetrates through the internal perspective glass and irradiates the camera lens of the camera.
Furthermore, the aircraft cabin wall, the reflector protection shell and the camera support are laid by layers through metal and heat insulation materials, and when the inner layer is a metal layer, the outer layer is a heat insulation material layer; when the inner layer is a heat insulation material layer, the outer layer is a metal layer.
Furthermore, the included angle A between the external perspective glass and the cabin wall of the aircraft can be adjusted according to task requirements, and the adjustment range is 0-90 degrees.
Furthermore, the included angle B between the reflector and the cabin wall of the aircraft can be adjusted by adjusting the position of the reflector fixing pin, and the adjustment range is 0-90 degrees.
Furthermore, according to the task requirement, the reflecting mirror can be a plane mirror, a concave mirror or a convex mirror, and different reflecting mirrors can enlarge or reduce the visual field range of the camera for shooting.
Furthermore, the cabin wall of the aircraft, the built-in perspective glass, the camera support and the camera sealing gasket form a sealing space, and through holes for penetrating through camera cables are reserved in the camera support and the camera sealing gasket.
Furthermore, the reflector comprises quartz glass, a reflecting coating and a base,
the reflecting coating is arranged on one side of the quartz glass close to the base, and can be made of aluminum or silver materials according to the requirements of reflecting light rays with different wavelengths in tasks and the environmental temperature; the quartz glass is tightly attached to the base and does not contact with the reflector fixing pin;
the base is connected with the reflector fixing pin, and a movable gap is reserved at the fixing position, so that the quartz glass can be prevented from being broken, heat can be prevented from being conducted to the reflecting coating, and the reflecting performance of the reflecting coating to light rays can be guaranteed.
Further, when the included angle B is smaller than 45 °, the reflector can reflect light rays from the outer surface of the cabin wall of the aircraft to the camera; when the included angle B is equal to 45 degrees, the reflector can reflect light rays parallel to the cabin wall of the aircraft to the camera; when B is greater than 45 °, the mirror may reflect light from the environment outside the aircraft towards the camera.
Furthermore, after the cabin outer components are damaged due to the influence of severe environment, the built-in perspective glass can prevent hot air outside the aircraft cabin from entering the cabin, and the built-in perspective glass plays a role in heat insulation.
Furthermore, after the built-in perspective glass is damaged, the camera support, the camera and the camera sealing gasket can prevent hot air outside the aircraft cabin from entering the cabin, and the camera support plays a role in heat insulation.
The utility model discloses the beneficial effect of content is:
(1) the size of the components of the device outside the aircraft cabin is smaller than that of a mode of directly installing a camera outside the aircraft, so that the generated pneumatic heating quantity is smaller, and the influence on the pneumatic appearance of the aircraft is smaller;
(2) the imaging quality of the device is higher than that of an endoscope mode in which the lens and the camera are respectively placed;
(3) the components of the device installed outside the aircraft cabin comprise metal, heat insulation materials, quartz glass and a reflector, the reflector comprises the quartz glass and a reflection coating, and the highest temperature which can be borne by the materials is far higher than the highest temperature which can be borne by a camera or a lens placed outside the aircraft cabin, so that the requirement on heat protection is lower;
(4) the device has lower cost compared with other camera heat protection devices.
Drawings
FIG. 1 is a side view of a high speed aircraft outward view camera thermal protection device of the present invention;
FIG. 2 is a front view of the thermal protection device of the high-speed aircraft outward-looking camera of the present invention;
FIG. 3 shows the angle B of the camera of the present invention is smaller than 45 degrees;
FIG. 4 shows the camera shooting range of the present invention with the included angle B larger than 45 °;
fig. 5 is a structural view of the reflector of the present invention.
Detailed Description
The present invention is described in further detail below with reference to the attached drawings.
As shown in fig. 1 and 2, the utility model provides a high-speed aircraft outward vision camera heat protector, include: the device comprises an aircraft bulkhead 1, a reflector protective shell 2, an external perspective glass 3, a reflector fixing pin 4, a reflector 5, an internal perspective glass 6, a camera bracket 7, a camera shock absorber 8, a camera 9, a camera sealing gasket 10 and a camera cable 11.
The aircraft bulkhead 1, the reflector protection shell 2 and the camera support 7 are all laid in layers by metal and thermal insulation materials, when the inner layer is a metal layer, the outer layer is a thermal insulation material layer which can be thermal insulation felt or glass fiber reinforced plastic or ceramic; when the inner layer is a heat insulation material layer, the outer layer is a metal layer.
The incident light 12 is irradiated onto the reflector 5 through the external see-through glass 3, and is reflected and then passes through the internal see-through glass 6 to be irradiated into the lens of the camera 9.
The reflector protection shell 2 is connected with the aircraft bulkhead 1 through screws, a metal assembly of the reflector protection shell 2 is provided with a threaded blind hole, the aircraft bulkhead 1 is provided with a through hole at a corresponding position, the screws penetrate through the aircraft bulkhead 1 from the inside of the aircraft and are connected with the reflector protection shell 2, and the reflector protection shell 2 is fixed with the aircraft bulkhead 1. The plane of the reflector protective shell 2 provided with the external perspective glass 3 and the aircraft bulkhead 1 form an included angle A, and the included angle A can be adjusted between 0 degrees and 90 degrees according to task requirements so as to adapt to the appearance of the aircraft.
The mirror protection shell 2 is provided with an external perspective glass 3, and the inner side of the window of the plane of the window is provided with a protruding step for fixing the external perspective glass 3. And high-temperature-resistant glue is smeared between the reflector protective shell 2 and the external perspective glass 3 for bonding and fixing. The whole thickness of speculum protective housing 2 is external perspective glass 3, the outstanding step of speculum protective housing 2, the thickness sum of high temperature glue, makes external perspective glass 3's surface and the surface parallel and level of speculum protective housing 2, does not have the step, avoids producing pneumatic heating. The high-temperature glue also plays a role in weakening the high-frequency vibration conducted by the reflector protective shell 2 to the external perspective glass 3.
Two mirror fixing pins 4 are mounted inside the mirror protective housing 2 by screws. The reflector 5 is fixed between two reflector fixing pins 4 and is connected by screws. The side of the reflector 5 reflecting light rays faces the external perspective glass 3, and the included angle between the reflector and the cabin wall 1 of the aircraft is B. The angle B can be changed by adjusting the position of the two mirror fixing pins 4 and the size of the mirror 5.
The built-in see-through glass 6 is mounted in a fenestration of the aircraft bulkhead 1, which has a protruding step inside for fixing the built-in see-through glass 6. High-temperature-resistant glue is coated between the aircraft bulkhead 1 and the built-in perspective glass 6, and the high-temperature-resistant glue can bear a high-temperature environment. The thickness of the aircraft bulkhead 1 is the sum of the thicknesses of the built-in perspective glass 6, the protruding steps of the aircraft bulkhead 1 and the high-temperature glue, the built-in perspective glass 6 is flush with the outer surface of the aircraft bulkhead 1, no step exists, and pneumatic heating is avoided. The high-temperature glue simultaneously plays a role in weakening the high-frequency vibration transmitted to the built-in perspective glass 6 by the aircraft bulkhead 1.
The camera mount 7 is fixed by screws in the aircraft cabin inside the aircraft cabin wall 1, the camera 9 is fixed by screws with a camera damper 8 on the camera mount 7, and the lens of the camera 9 faces the built-in see-through glass 6. A flexible camera sealing gasket 10 is laid between the camera support 7 and the camera 9, the camera sealing gasket 10 is adhered to the camera support 7 through high-temperature glue, through holes are formed in the camera support 7 and the camera sealing gasket 10, a camera cable 11 penetrates through the through holes to connect the camera 9 with internal equipment of the aircraft cabin, and the camera 9 and the camera sealing gasket 10 shield the through holes, so that the aircraft cabin wall 1 and the camera support 7 form a sealed space.
The incident light 12 passes through the external see-through glass 3, irradiates the reflector 5, is reflected, passes through the internal see-through glass 6, and irradiates the lens of the camera 9.
In view of the thermal protection requirements, the aircraft bulkhead 1, the mirror housing 2 and the camera support 7 comprise metal and heat insulating material, are laid in layers, and the stacking sequence of the materials may be different according to the mission requirements.
The included angle B can be adjusted between 0 degree and 90 degrees.
As shown in fig. 1, the angle B is equal to 45 °, the mirror 5 being able to reflect light parallel to the aircraft bulkhead 1 towards the camera, which photographs the corresponding environment.
As shown in fig. 3, the angle B is less than 45 °, the mirror 5 being able to reflect light rays from the outer surface of the aircraft bulkhead 1 towards the camera, which shoots changes in the state of the outer surface of the aircraft bulkhead.
As shown in fig. 4, the angle B is greater than 45 °, the mirror 5 is able to reflect the light of the external environment of the aircraft towards the camera, which shoots the changes of the external environment of the aircraft.
When the reflecting mirror 5 is a plane mirror, the field of view of the camera does not change, and the shape is not distorted.
When the mirror 5 uses a concave mirror, the field of view taken by the camera becomes small, and the shape of the object is distorted.
When the reflecting mirror 5 is a convex mirror, the field of view of the camera becomes large, and the shape of the object is distorted.
After the cabin outer components fall off due to the influence of the harsh environment, the built-in perspective glass 6 ensures the isolation of the cabin interior from the outside, and prevents the hot air flow outside the aircraft cabin from entering the cabin interior. When the built-in perspective glass 6 is broken, the sealed space formed by the camera bracket 7, the camera 9 and the camera sealing gasket 10 can prevent hot air outside the aircraft cabin from entering the interior of the cabin. The camera mount 7 uses a heat insulating material and thus can assume a heat insulating function, and the temperature of the working environment of the camera 9 is not guaranteed.
As shown in fig. 5, the mirror 5 includes a quartz glass 13, a reflection layer 14, and a base 15.
The reflection layer 14 reflects the incident light 12 to the camera 9 on the side of the quartz glass 13 adjacent to the base. Reflective layer 14 may be made of aluminum or silver, for example, according to the reflective requirements of different wavelengths of light and the ambient temperature during the task.
The quartz glass 13 is closely attached to the base 15, and the quartz glass 13 is provided with a through hole and fixed to the base 15 by a screw 16. The quartz glass 13 is not in contact with the mirror fixing pin 4.
The reflector fixing pin 4 is composed of two layers, the top layer is provided with a through hole, the bottom layer is provided with a blind hole with threads, and the diameter of the through hole is larger than that of the blind hole. The base 15 is provided with a through hole, and the diameter of the through hole is larger than that of the bottom blind hole of the reflector fixing pin 4. The mount 15 is placed between the top and bottom layers of the mirror fixing pin 4. The bolt 17 passes through the gasket 18, the spring plate 19, the through hole at the top layer of the reflector fixing pin 4 and the through hole at the base 15 and then is connected with the blind hole at the bottom layer of the reflector fixing pin 4. The screw 17 applies a predetermined torque using a torque wrench. The base 15 has better rigidity, and when the speculum protective housing 2 takes place to warp, the relative position of two speculum fixed pins 4 changes, and speculum fixed pin 4 and base 15 produced relative displacement this moment to reduce the deformation of base 15, reduce the cracked risk of quartz glass 13. The base 15 has good heat insulation capacity, prevents that the heat of reflector protective housing 2 from conducting to reflection layer 14, guarantees reflection layer 14 to the reflective properties of light.
One specific example is given below:
the outer layer of the aircraft bulkhead 1 and the reflector protective shell 2 is made of high-temperature alloy steel, the inner layer is paved with a flexible heat insulation felt, the camera support 7 is made of high-temperature alloy steel, the flexible heat insulation felt is paved on one side where the camera 9 is installed, the grade of the high-temperature alloy steel is GH4169 and can bear the temperature of about 700 ℃, the flexible heat insulation felt is made of quartz wool, the main material is silicon dioxide, the heat conductivity coefficient is less than or equal to 0.05W/m.K and can bear the temperature of about 1700.
The external perspective glass 3 and the internal perspective glass 6 are made of quartz glass, and the material is silicon dioxide, and the material can bear about 1700 ℃.
The high-temperature adhesive is selected from model Dq441J-108, has stable state at high temperature and can bear about 500 ℃.
The reflective coating 14 uses silver and is able to withstand approximately 961 c.
The base 15 is made of ceramic material, has strong rigidity and good heat insulation performance, and can bear about 3000 ℃.
The camera gasket 10 is custom made with a model Dq441J-108 high temperature glue, which provides better sealing without affecting the damping performance of the camera damper 8, which can withstand approximately 500 ℃.
The size of this device at aircraft cabin outside subassembly, it is littleer to directly install the mode at the aircraft outside with the camera, and consequently the pneumatics that produces add heat quantity littleer, and is littleer to the influence of aircraft aerodynamic configuration.
The present invention has not been described in detail as is known to those skilled in the art.
Claims (10)
1. A high-speed aircraft outward-looking camera thermal protection device is characterized by comprising: the device comprises an aircraft bulkhead (1), a reflector protective shell (2), external perspective glass (3), a reflector fixing pin (4), a reflector (5), internal perspective glass (6), a camera support (7), a camera shock absorber (8), a camera (9), a camera sealing gasket (10) and a camera cable (11);
the reflector protection shell (2) is arranged outside the aircraft cabin and connected with the aircraft cabin wall (1), and the included angle between the plane provided with the external perspective glass (3) and the aircraft cabin wall (1) is A;
the external perspective glass (3) is fixed in a through hole of the reflector protective shell (2) by using high-temperature glue and is flush with the outer surface of the reflector protective shell (2), and the high-temperature glue simultaneously weakens the high-frequency vibration conducted by the reflector protective shell (2) to the external perspective glass (3);
the two reflector fixing pins (4) are respectively installed inside the reflector protection shell (2), the reflector (5) is fixed between the two reflector fixing pins (4), one side of the reflector (5) reflecting light faces the external perspective glass (3), and the included angle between one side of the reflector (5) reflecting light and the aircraft bulkhead (1) is B;
the built-in perspective glass (6) is fixed in a through hole of the aircraft bulkhead (1) by using high-temperature glue and is flush with the outer surface of the aircraft bulkhead (1), and the high-temperature glue is used for weakening high-frequency vibration conducted by the aircraft bulkhead (1) to the built-in perspective glass (6);
the camera support (7) is fixed on the inner side of an aircraft cabin wall (1), a camera (9) is fixed on the camera support (7) through a camera shock absorber (8), a lens of the camera (9) faces to a built-in perspective glass (6), a camera sealing gasket (10) is laid between the camera support (7) and the camera (9) and fixed on one side of the camera support (7), and a camera cable (11) penetrates through holes of the camera support (7) and the camera sealing gasket (10) to connect the camera (9) and internal equipment of the aircraft cabin;
incident light (12) irradiates the reflector (5) through the external perspective glass (3), and after reflection, the incident light passes through the internal perspective glass (6) and irradiates the lens of the camera (9).
2. The high-speed aircraft outward view camera thermal protection device of claim 1, characterized in that: the aircraft bulkhead (1), the reflector protective shell (2) and the camera support (7) are laid in layers through metal and thermal insulation materials, and when the inner layer is a metal layer, the outer layer is a thermal insulation material layer; when the inner layer is a heat insulation material layer, the outer layer is a metal layer.
3. The high-speed aircraft outward view camera thermal protection device of claim 1, characterized in that: the adjusting range of the included angle A between the external perspective glass (3) and the aircraft bulkhead (1) is 0-90 degrees.
4. The high-speed aircraft outward view camera thermal protection device of claim 1, characterized in that: the included angle B between the reflector (5) and the aircraft bulkhead (1) is adjusted by adjusting the position of the reflector fixing pin (4), and the adjustment range is 0-90 degrees.
5. The high-speed aircraft outward view camera thermal protection device of claim 1, characterized in that: the reflecting mirror (5) is a plane mirror, a concave mirror or a convex mirror so as to enlarge or reduce the visual field range of the camera for shooting.
6. The high-speed aircraft outward view camera thermal protection device of claim 1, characterized in that: the aircraft cabin wall (1), the built-in perspective glass (6), the camera support (7) and the camera sealing gasket (10) form a sealing space, and through holes penetrating through the camera cable (11) are reserved in the camera support (7) and the camera sealing gasket (10).
7. The high-speed aircraft outward view camera thermal protection device of claim 1, characterized in that: the reflector (5) comprises quartz glass (13), a reflective coating (14) and a base (15),
the reflecting coating (14) is arranged on one side, close to the base, of the quartz glass (13), and aluminum or silver materials are used according to requirements for reflecting light rays with different wavelengths in tasks and the ambient temperature; the quartz glass (13) is tightly attached to the base (15), and the quartz glass (13) is not contacted with the reflector fixing pin (4);
the base (15) is connected with the reflector fixing pin (4), a movable gap is reserved at the fixing position, quartz glass (13) is prevented from being broken, heat is prevented from being conducted to the reflecting coating (14), and the reflecting performance of the reflecting coating (14) to light rays is guaranteed.
8. The high-speed aircraft outward view camera thermal protection device of claim 4, characterized in that: when the included angle B is smaller than 45 degrees, the reflector (5) is used for reflecting light rays on the outer surface of the cabin wall of the aircraft to the camera; when the included angle B is equal to 45 degrees, the reflector (5) is used for reflecting light rays parallel to the cabin wall (1) of the aircraft to the camera; when B is greater than 45 DEG, the mirror (5) is used to reflect light from the environment outside the aircraft towards the camera.
9. The high-speed aircraft outward view camera thermal protection device of claim 6, characterized in that: after the cabin outer components are damaged due to the influence of severe environment, the built-in perspective glass (6) is used for preventing hot air outside the aircraft cabin from entering the interior of the cabin, and the built-in perspective glass (6) plays a role in heat insulation.
10. The high-speed aircraft outward view camera thermal protection device of claim 9, characterized in that: when the built-in perspective glass (6) is damaged, the camera support (7), the camera (9) and the camera sealing gasket (10) are used for preventing hot air outside the aircraft cabin from entering the cabin, and the camera support (7) plays a role in heat insulation.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202021548406.0U CN213414241U (en) | 2020-07-30 | 2020-07-30 | High-speed aircraft outward vision camera heat protection device |
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| CN202021548406.0U CN213414241U (en) | 2020-07-30 | 2020-07-30 | High-speed aircraft outward vision camera heat protection device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111907726A (en) * | 2020-07-30 | 2020-11-10 | 中国航天空气动力技术研究院 | High-speed aircraft outward vision camera heat protection device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111907726A (en) * | 2020-07-30 | 2020-11-10 | 中国航天空气动力技术研究院 | High-speed aircraft outward vision camera heat protection device |
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