CN212163750U

CN212163750U - Shielding extension metal mesh for aircraft window

Info

Publication number: CN212163750U
Application number: CN202020983683.8U
Authority: CN
Inventors: 何康
Original assignee: Jiangsu Kinson New Material Co ltd
Current assignee: Jiangsu Kinson New Material Co ltd
Priority date: 2020-06-03
Filing date: 2020-06-03
Publication date: 2020-12-15
Anticipated expiration: 2030-06-03

Abstract

The utility model relates to the technical field of aviation, specifically disclose a shielding extension metal mesh for aircraft window, including window and shielding net, the shielding net comprises first braided wire, second braided wire and silica gel heat conduction stick; the inner sides of the first braided wire and the second braided wire are fixedly connected with connecting blocks, and six connecting blocks are annularly arranged; the inner sides of the first braided wire and the second braided wire are fixedly connected with reinforcing sleeves, and the outer sides of the reinforcing sleeves are fixedly connected with heat conducting wires at equal intervals; the utility model discloses a constant head tank that sets up and the location bolt that sets up can be when using, can be convenient protect the window department of setting, and through the shielding net that sets up, can be favorable to reducing the influence of the window department difference in temperature to the window, and the silica gel heat conduction stick of setting can utilize the heater strip in the shielding net that sets up when using, conducts the heat, is favorable to the use of device.

Description

Shielding extension metal mesh for aircraft window

Technical Field

The utility model relates to an aviation technical field specifically is an airborne vehicle window is with shielding extension metal mesh.

Background

The aircraft can carry out controllable flight in the atmosphere. Any aircraft must generate lift greater than its own weight in order to be able to ascend into the air. Aircraft can be divided into two main categories according to the principle of generating lift: lighter-than-air aircraft and heavier-than-air aircraft. The former is lifted off by air static buoyancy; the latter is lifted off against its own weight by aerodynamic force.

In the using state of the aircraft, the temperature in the high air is relatively low because the oxygen in the high air is thinner, the icing phenomenon can occur on the surface of the aircraft under the condition of strong convection, the use of the aircraft is seriously influenced, and the window of the aircraft can be greatly damaged when the temperature difference is strong, so that the shielding expanded metal mesh for the window of the aircraft is provided.

SUMMERY OF THE UTILITY MODEL

The utility model provides a not enough to prior art, the utility model provides an aircraft window is with shielding extension metal mesh possesses and can protect window glass on the aircraft when using, avoids the too big phenomenon that appears glass damage of the difference in temperature, and can not influence the normal use of aircraft window, has solved current device when using, to not having the problem of better protection with aircraft window department.

The utility model discloses a shielding extension metal mesh for aircraft window, including window and shielding net, the shielding net comprises first braided wire, second braided wire and silica gel heat conduction stick; the inner sides of the first braided wire and the second braided wire are fixedly connected with connecting blocks, and six connecting blocks are annularly arranged; the inner sides of the first braided wire and the second braided wire are fixedly connected with reinforcing sleeves, the outer sides of the reinforcing sleeves are fixedly connected with heat conducting wires at equal intervals, and the tops of the heat conducting wires are fixedly connected with the bottoms of the connecting blocks; the silica gel heat conducting rod is positioned in the middle of the inner sides of the first braided wire and the second braided wire and is fixedly connected with the inner sides of the first braided wire and the second braided wire; first braided wire and second braided wire twine each other and weave, the department fixedly connected with silica gel setpoint is woven in the winding of first braided wire and second braided wire, just the silica gel setpoint closely laminates with the surface of window, through the silica gel setpoint that sets up, can carry out the adaptation with the window that sets up, is favorable to the connection of shielding net to use.

The utility model discloses an aircraft window is with shielding extension metal mesh, circular through-hole has been seted up to the inboard equidistance of reinforcement cover wherein, the circular through-hole fixedly connected with metal wire of department of reinforcement cover, the metal wire links to each other with the reinforcement cover is fixed, through the metal wire that sets up, has given the ductility of shielding net, is favorable to the extension of shielding net to use.

The utility model discloses an aircraft window is with shielding extension metal mesh, wherein reinforce the inboard mid-mounting of cover and have the heater strip, the heater strip closely laminates with the inner wall both sides that reinforce the cover, through the heater strip that sets up, can be connected the adaptation with the reinforcement cover that sets up, is favorable to the heat conduction of heater strip.

The utility model discloses an aircraft window extends metal mesh with shielding, wherein two aluminium alloy strip is installed to the inboard of heat conduction silk, aluminium alloy strip's the outside closely laminates with the reinforcement cover, can cooperate the metal wire that sets up through the aluminium alloy strip that sets up, has further strengthened the ductility of shielding net.

The utility model discloses an aircraft window is with shielding extension metal mesh, wherein circular through-hole and fixedly connected with aircraft glass have been seted up in the front of window, the constant head tank has been seted up to the outside equidistance of window, it has the location bolt to peg graft in the inboard of constant head tank, the outside of location bolt links to each other with the shielding net is fixed, just the shielding net is located aircraft glass's top, through the location bolt that sets up and the constant head tank that sets up, can be more convenient make the shielding net of setting be connected with the window.

The beneficial effects are as follows:

1. the utility model discloses a constant head tank that sets up and the location bolt that sets up can be when using, can be convenient protect the window department of setting, and through the shielding net that sets up, can be favorable to reducing the influence of the window department difference in temperature to the window, and the silica gel heat conduction stick of setting can utilize the heater strip in the shielding net that sets up when using, conducts the heat, is favorable to the use of device.

2. The utility model discloses a heater strip that the heat conduction silk that sets up can cooperate the setting conducts the heat that produces in the heater strip, is favorable to the normal use of device, and the reinforced cover that sets up is woven with the combination of the metal wire of setting, can give the ductility of braided wire and No. two braided wires when built-up connection for the shielding net of setting can possess more stable connected mode.

Drawings

The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the application and together with the description serve to explain the application and not to limit the application. In the drawings:

FIG. 1 is a schematic view of a front view structure of a window according to the present invention;

FIG. 2 is an enlarged schematic view of the structure at A of FIG. 1 according to the present invention;

FIG. 3 is a schematic structural view of the first braided wire in front view;

fig. 4 is the schematic view of the winding combination structure of the first braided wire, the second braided wire and the silica gel heat conducting rod of the present invention.

In the figure: 01. a window; 02. positioning a groove; 03. positioning a bolt; 04. a shielding mesh; 05. locating points of silica gel; 06. a first braided wire; 07. a second braided wire; 08. connecting blocks; 09. reinforcing the sleeve; 10. a metal wire; 11. aluminum alloy strips; 12. a silica gel heat conducting rod; 13. heating wires; 14. and (4) heat-conducting wires.

Detailed Description

In the following description, for purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the present invention. It should be understood, however, that these implementation details should not be used to limit the invention. That is, in some embodiments of the invention, details of these implementations are not necessary. In addition, some conventional structures and components are shown in simplified schematic form in the drawings.

In addition, the descriptions related to "first", "second", etc. in the present invention are only for description purposes, not specifically referring to the order or sequence, and are not intended to limit the present invention, but only to distinguish the components or operations described in the same technical terms, and are not to be construed as indicating or implying any relative importance or implicit indication of the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In addition, the technical solutions in the embodiments may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, the combination of the technical solutions should not be considered to exist, and is not within the protection scope of the present invention.

Referring to fig. 1-4, the shielding expanded metal mesh for the aircraft window of the present invention includes a window 01 and a shielding mesh 04, wherein the shielding mesh 04 is composed of a first braided wire 06, a second braided wire 07 and a silica gel heat conducting rod 12;

the inner sides of the first braided wire 06 and the second braided wire 07 are fixedly connected with connecting blocks 08, and six connecting blocks 08 are annularly arranged;

the inner sides of the first braided wire 06 and the second braided wire 07 are fixedly connected with reinforcing sleeves 09, the outer sides of the reinforcing sleeves 09 are fixedly connected with heat conducting wires 14 at equal intervals, and the tops of the heat conducting wires 14 are fixedly connected with the bottoms of the connecting blocks 08;

the silica gel heat conducting rod 12 is positioned in the middle of the inner sides of the first braided wire 06 and the second braided wire 07 and is fixedly connected with the inner sides of the first braided wire 06 and the second braided wire 07;

first braided wire 06 and second braided wire 07 intertwine with each other and weave, and the department fixedly connected with silica gel setpoint 05 is woven in the winding of first braided wire 06 and second braided wire 07, and the surface of silica gel setpoint 05 and window 01 closely laminates, through the silica gel setpoint 05 that sets up, can carry out the adaptation with the window 01 that sets up, is favorable to the connection of shielding net 04 to be used.

Circular through-holes are formed in the inner side of the reinforcing sleeve 09 at equal intervals, metal wires 10 are fixedly connected to the circular through-holes of the reinforcing sleeve 09, the metal wires 10 are fixedly connected with the reinforcing sleeve 09, and the shielding net 04 is endowed with ductility through the arranged metal wires 10, so that the shielding net 04 is favorable for being used in an extending mode.

The heating wire 13 is installed at the middle part of the inner side of the reinforcing sleeve 09, the heating wire 13 is tightly attached to the two sides of the inner wall of the reinforcing sleeve 09, and the heating wire 13 can be connected with the reinforcing sleeve 09 to be matched with the reinforcing sleeve 09, so that heat conduction of the heating wire 13 is facilitated.

Aluminum alloy strips 11 are installed on the inner sides of the two heat conducting wires 14, the outer sides of the aluminum alloy strips 11 are tightly attached to the reinforcing sleeve 09, and the aluminum alloy strips 11 can be matched with the metal wire 10, so that the ductility of the shielding net 04 is further enhanced.

Circular through-hole and fixedly connected with aircraft glass have been seted up in window 01's front, and constant head tank 02 has been seted up to window 01's the outside equidistance, and the inboard of constant head tank 02 is pegged graft and is had location bolt 03, and the outside of location bolt 03 is fixed continuous with shielding net 04, and shielding net 04 is located aircraft glass's top, through the location bolt 03 of setting and the constant head tank 02 of setting, can be more convenient make the shielding net 04 of setting be connected with window 01.

When using the utility model discloses the time:

firstly, the arranged shielding net 04 can be inserted into a positioning groove 02 at the outer side of the arranged window 01 under the action of the arranged positioning bolt 03, and the arranged shielding net 04 can be stably arranged on the aircraft glass at the window 01;

when the aircraft flies, when encountering strong convection airflow, the glass at the window 01 can be frozen, at the moment, the first braided wire 06 and the second braided wire 07 which form the shielding net 04 are combined, the heat wires 13 and the heat conducting wires 14 are utilized to combine, the heat can be uniformly led into the arranged aluminum alloy strips 11, the heat can be uniformly led into the arranged silica gel heat conducting rods 12 through the conduction action of the aluminum alloy strips 11, therefore, the frozen part of the window 01 of the aircraft can be ablated, and the silica gel positioning points 05 are matched with the arranged silica gel positioning points, so that the arranged shielding net 04 can be stably connected with the arranged window 01 of the aircraft for use.

The above description is only an embodiment of the present invention, and is not intended to limit the present invention. Various modifications and changes may occur to those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the scope of the claims of the present invention.

Claims

1. A screen expanded metal for aircraft windows, comprising a window (01) and a screen (04), characterized in that: the shielding net (04) is composed of a first braided wire (06), a second braided wire (07) and a silica gel heat conducting rod (12);

the inner sides of the first braided wire (06) and the second braided wire (07) are fixedly connected with connecting blocks (08), and six connecting blocks (08) are annularly arranged;

the inner sides of the first braided wire (06) and the second braided wire (07) are fixedly connected with reinforcing sleeves (09), the outer sides of the reinforcing sleeves (09) are fixedly connected with heat conducting wires (14) at equal intervals, and the tops of the heat conducting wires (14) are fixedly connected with the bottoms of the connecting blocks (08);

the silica gel heat conducting rod (12) is positioned in the middle of the inner sides of the first braided wire (06) and the second braided wire (07) and is fixedly connected with the inner sides of the first braided wire (06) and the second braided wire (07);

first braided wire (06) and second braided wire (07) intertwine to weave each other, the winding of first braided wire (06) and second braided wire (07) is woven department fixedly connected with silica gel setpoint (05), just silica gel setpoint (05) closely laminates with the surface of window (01).

2. A screen-extended metal mesh for aircraft windows according to claim 1, characterized in that: circular through holes are formed in the inner side of the reinforcing sleeve (09) at equal intervals, metal wires (10) are fixedly connected to the circular through holes of the reinforcing sleeve (09), and the metal wires (10) are fixedly connected with the reinforcing sleeve (09).

3. A screen-extended metal mesh for aircraft windows according to claim 1, characterized in that: the heating wire (13) is arranged in the middle of the inner side of the reinforcing sleeve (09), and the heating wire (13) is tightly attached to two sides of the inner wall of the reinforcing sleeve (09).

4. A screen-extended metal mesh for aircraft windows according to claim 1, characterized in that: two aluminium alloy strip (11) are installed to the inboard of heat conduction silk (14), the outside and the reinforcing cover (09) of aluminium alloy strip (11) are closely laminated.

5. A screen-extended metal mesh for aircraft windows according to claim 1, characterized in that: circular through-hole and fixedly connected with aircraft glass have been seted up in the front of window (01), constant head tank (02) have been seted up to the outside equidistance of window (01), the inboard of constant head tank (02) is pegged graft and is had location bolt (03), the outside and the shielding net (04) of location bolt (03) are fixed continuous, just shielding net (04) are located aircraft glass's top.