CN214356627U - Unmanned aerial vehicle engine compartment and aircraft - Google Patents
Unmanned aerial vehicle engine compartment and aircraft Download PDFInfo
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- CN214356627U CN214356627U CN202120545231.6U CN202120545231U CN214356627U CN 214356627 U CN214356627 U CN 214356627U CN 202120545231 U CN202120545231 U CN 202120545231U CN 214356627 U CN214356627 U CN 214356627U
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Abstract
The utility model provides an unmanned aerial vehicle engine compartment and aircraft relates to unmanned air vehicle technique field, include: a nacelle body and a thermal insulation member; the nacelle body has a housing chamber for housing the engine body, and a heat insulating member is provided on the engine body, the heat insulating member being configured to block heat generated by the engine body from being transferred into the nacelle body. Through set up thermal-insulated component in the engine main part that is located cabin main part holding intracavity, utilize thermal-insulated component to avoid the heat transfer that the engine produced to the cabin main part internal, effectively prevent the heat from influencing the intensity of cabin main part and the normal work of other electrical components in the cabin main part, the adoption of having alleviated existence among the prior art sets up the aerodynamic drag that the cooling opening can increase unmanned aerial vehicle on unmanned aerial vehicle organism surface, and then influences the technical problem of unmanned aerial vehicle technical index's performance.
Description
Technical Field
The utility model belongs to the technical field of the unmanned air vehicle technique and specifically relates to an unmanned aerial vehicle engine compartment and aircraft are related to.
Background
At present, the applications and the types of military unmanned aerial vehicles are gradually increased, the functions of the military unmanned aerial vehicles comprise that tactical support roles such as target aircraft, communication, reconnaissance, battlefield evaluation and the like want electronic countermeasure and fire fighting expansion, and the space of a mission is transited to middle-high altitude and beyond visual range.
Along with the improvement of military unmanned aerial vehicle performance index requirement, need the high thrust engine, must face engine compartment high temperature problem. When the conventional engine works, the exhaust temperature of the tail nozzle is generally 650-850 ℃, and if heat insulation measures are not taken, the temperature in the engine compartment can reach 300-400 ℃, which influences the structural strength and rigidity of the engine compartment of the unmanned aerial vehicle and the normal work of electronic equipment in the engine compartment. Therefore, the problem of engine compartment heat insulation is very important, and a cooling opening is generally arranged on the unmanned aerial vehicle body for forced cooling.
However, the cooling opening exposes unmanned aerial vehicle organism surface, can increase unmanned aerial vehicle's aerodynamic drag, and then influences unmanned aerial vehicle technical index's performance.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an unmanned aerial vehicle engine compartment and aircraft to having alleviated the adoption that exists among the prior art and having offered the aerodynamic drag that the cooling hole can increase unmanned aerial vehicle on unmanned aerial vehicle organism surface, and then the technical problem who influences unmanned aerial vehicle technical indicator's performance.
In a first aspect, the utility model provides an unmanned aerial vehicle engine compartment, include: a nacelle body and a thermal insulation member;
the nacelle body has a receiving cavity for placing an engine body, and the heat insulation member is disposed on the engine body and configured to block heat generated by the engine body from being transferred into the nacelle body.
In an alternative embodiment of the method of the present invention,
the insulation member comprises an insulation layer;
the tail of the engine main body is provided with a spray pipe, and the thermal insulation layer is wrapped on the surface of the spray pipe.
In an alternative embodiment of the method of the present invention,
the thermal insulation layer is made of aerogel thermal insulation materials.
In an alternative embodiment of the method of the present invention,
the insulation member further comprises a fixing member;
the fixing piece is connected with the heat insulation layer, and the fixing piece is configured to fix the heat insulation layer on the spray pipe.
In an alternative embodiment of the method of the present invention,
the fixing piece is arranged to be a heat insulation wrapping layer, and the heat insulation wrapping layer wraps the outer surface of the heat insulation layer.
In an alternative embodiment of the method of the present invention,
the heat insulation wrapping layer is made of glass fiber adhesive tape.
In an alternative embodiment of the method of the present invention,
the unmanned aerial vehicle engine compartment further comprises a connecting member;
the engine main body is connected to the nacelle main body by the connecting member.
In an alternative embodiment of the method of the present invention,
the unmanned aerial vehicle engine compartment further comprises an engine cover;
the engine cover is arranged in the accommodating cavity, and the engine cover is configured to wrap the engine main body.
In an alternative embodiment of the method of the present invention,
the engine cover is connected with the nacelle body by screws.
In a second aspect, the present invention provides an aircraft, including an unmanned aerial vehicle engine compartment.
The utility model provides a pair of unmanned aerial vehicle engine compartment, include: a nacelle body and a thermal insulation member; the nacelle body has a housing chamber for housing the engine body, and a heat insulating member is provided on the engine body, the heat insulating member being configured to block heat generated by the engine body from being transferred into the nacelle body. Through set up thermal-insulated component in the engine main part that is located cabin main part holding intracavity, utilize thermal-insulated component to avoid the heat transfer that the engine produced to the cabin main part internal, effectively prevent the heat from influencing the intensity of cabin main part and the normal work of other electrical components in the cabin main part, the adoption of having alleviated existence among the prior art sets up the aerodynamic drag that the cooling opening can increase unmanned aerial vehicle on unmanned aerial vehicle organism surface, and then influences the technical problem of unmanned aerial vehicle technical index's performance.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the technical solutions in the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is the embodiment of the utility model provides an unmanned aerial vehicle engine cabin's overall structure schematic diagram.
Icon: 100-a nacelle body; 110-an engine body; 200-an insulating member; 210-a thermally insulating layer; 220-heat insulating wrapping layer; 300-a connecting member; 400-engine hood.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention, as generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate the position or positional relationship based on the position or positional relationship shown in the drawings, or the position or positional relationship which is usually placed when the product of the present invention is used, and are only for convenience of description and simplification of the description, but do not indicate or imply that the device or element referred to must have a specific position, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.
Furthermore, the terms "horizontal", "vertical", "overhang" and the like do not imply that the components are required to be absolutely horizontal or overhang, but may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Some embodiments of the present invention will be described in detail below with reference to the accompanying drawings. The embodiments described below and the features of the embodiments can be combined with each other without conflict.
As shown in fig. 1, the present embodiment provides an unmanned aerial vehicle engine compartment, including: a nacelle body 100 and a thermal insulation member 200; the nacelle body 100 has a receiving cavity for placing the engine body 110, and the heat insulating member 200 is disposed on the engine body 110, the heat insulating member 200 being configured to block heat generated by the engine body 110 from being transferred into the nacelle body 100.
Specifically, a containing cavity is arranged in the nacelle body 100, the engine body 110 is placed in the containing cavity, the heat insulation member 200 is arranged on the engine body 110, the heat insulation member 200 insulates heat transfer between the engine body 110 and the nacelle body 100, heat generated when the engine body 110 works is prevented from being transferred to the nacelle body 100, and the situation that the structural strength and rigidity are affected due to overhigh temperature of the nacelle body 100 and normal use of other electronic equipment in the nacelle body 100 are effectively prevented.
The embodiment provides an unmanned aerial vehicle engine compartment includes: a nacelle body 100 and a thermal insulation member 200; the nacelle body 100 has a receiving cavity for placing the engine body 110, and the heat insulating member 200 is provided on the engine, the heat insulating member 200 being configured to block heat generated from the engine from being transferred into the nacelle body 100. Through set up thermal-insulated component 200 on the engine main part 110 that is located cabin main part 100 holding intracavity, utilize thermal-insulated component 200 to avoid in the heat transfer that the engine produced arrives cabin main part 100, effectively prevent other electrical components's in heat influence cabin main part 100 intensity and the cabin main part 100 normal work, the adoption of having alleviated existence among the prior art sets up the aerodynamic drag that the cooling opening can increase unmanned aerial vehicle on unmanned aerial vehicle organism surface, and then influences the technical problem of unmanned aerial vehicle technical index's performance.
On the basis of the above embodiment, in an alternative implementation, the heat insulation member 200 in the engine compartment of the unmanned aerial vehicle provided by the present embodiment includes a heat insulation layer 210; the tail of the engine body 110 is provided with a spray pipe, and the thermal insulation layer 210 is wrapped on the surface of the spray pipe.
Specifically, the tail portion of the engine main body 110 is provided with a spray pipe capable of dissipating heat, the thermal insulation layer 210 is wrapped on the outer surface of the spray pipe, and the thermal insulation layer 210 prevents heat transmission from the surface of the spray pipe of the engine main body 110 and prevents heat generated by the engine main body 110 from being transmitted from the surface of the spray pipe to the nacelle main body 100.
In an alternative embodiment, the material of the insulation layer 210 is aerogel insulation.
Specifically, the thermal insulation layer 210 is made of thermal insulation material and aerogel, and when most of the solvent is removed from the gel, the liquid content in the gel is much less than the solid content, or the space network structure of the gel is filled with gas, and the appearance is solid, i.e. the aerogel. Aerogel composite melamine sponge aerogel blanket has the characteristics of softness, easy cutting, small density, fire prevention and flame retardance, environmental protection and the like, can replace traditional flexible heat-insulating materials with poor heat-insulating property, such as glass fiber products, asbestos heat-insulating felts, silicate fiber products and the like, the air holes of the aerogel are nano-scale air holes, the aerogel has extremely low density, the air holes in the aerogel tend to be infinite, each air hole wall has the effect of a heat-shielding plate, therefore, the effect of approaching infinite heat-shielding plates is generated, the heat radiation is minimized, and preferably, the heat-insulating layer 210 is made of an aerogel heat-insulating material.
The unmanned aerial vehicle engine cabin that this embodiment provided, through set up insulating layer 210 on the spray tube at engine main part 110 afterbody, insulating layer 210 adopts the aerogel material that thermal-insulated effect is more, avoids on the heat transfer cabin main part 100 in the spray tube at engine main part 110 afterbody, protects cabin main part 100 and the normal use of the interior electronic equipment of cabin main part 100.
On the basis of the above embodiment, in an optional implementation manner, the heat insulation member 200 in the engine compartment of the unmanned aerial vehicle provided by the present embodiment further includes a fixing piece; a fastener is coupled to the insulation 210, the fastener configured to secure the insulation 210 to the lance.
Specifically, in order to fix the heat insulation layer 210 to the nozzle at the rear of the engine body 110, a fixing member is provided on the outer surface of the heat insulation layer 210, and the fixing member is attached to the surface of the heat insulation layer 210, so that the heat insulation layer 210 is fixed to the nozzle at the rear of the engine body 110.
In an alternative embodiment, the fastener is provided as an insulating wrap 220, the insulating wrap 220 wrapping around the outer surface of the insulating layer 210.
Specifically, the fixing member is provided as an insulation cover 220, and the insulation cover 220 is wound around the outer surface of the insulation layer 210 to fix the insulation layer 210 to the nozzle at the rear of the engine body 110.
In an alternative embodiment, the insulating wrap 220 is provided as fiberglass tape.
Specifically, the heat-insulating wrapping layer 220 is specifically configured as a glass fiber adhesive tape, which has the characteristics of high temperature resistance, corrosion resistance and the like, and preferably, the heat-insulating wrapping layer 220 is a glass fiber adhesive tape.
In an alternative embodiment, the drone nacelle further comprises a connecting member 300; the engine body 110 is connected to the nacelle body 100 by a connecting member 300.
Specifically, in order to fix the engine body 110 in the nacelle body 100, the connecting member 300 is provided, one end of the connecting member 300 is connected to the nacelle body 100, and the other end is connected to the engine body 110, the connecting member 300 is specifically provided as a connecting bolt, a bolt hole is provided in the engine body 110, and the engine body 110 is fixed in the nacelle body 100 by the engagement of the connecting member 300 and the bolt hole.
In an alternative embodiment, the unmanned aerial vehicle engine compartment further comprises an engine cover 400; the engine cover 400 is disposed in the accommodating cavity, and the engine cover 400 is configured to wrap the engine main body 110.
Specifically, the engine cover 400 is provided in the housing chamber in the nacelle body 100, the engine cover 400 covers the engine body 110, and the engine body 110 is wrapped in the engine cover 400 to insulate heat and insulate sound from the engine.
In an alternative embodiment, the bonnet 400 is attached to the nacelle body 100 by screws.
Specifically, the engine cover 400 may be fixed to the nacelle body 100 by screws, or the engine cover 400 may be fixed to the nacelle body 100 by bolts, rivets, or the like.
According to the engine compartment of the unmanned aerial vehicle provided by the embodiment, the heat insulation layer 210 is fixedly wrapped on the surface of the engine main body 110 through the arrangement of the fixing piece, so that heat generated by the engine main body 110 is prevented from being transferred to the engine compartment main body 100; by providing the engine cover 400 in the nacelle body 100, the engine body 110 is wrapped with the engine cover 400, and a heat and sound insulating effect is achieved.
The aircraft provided by the embodiment comprises an unmanned aerial vehicle engine cabin.
Since the technical effect of the aircraft provided by this embodiment is the same as that of the above-mentioned unmanned aerial vehicle engine nacelle, it is not repeated here.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention.
Claims (10)
1. An unmanned aerial vehicle engine compartment, comprising: a nacelle body (100) and a heat insulation member (200);
the nacelle body (100) is provided with a containing cavity for placing an engine body (110), the heat insulation component (200) is arranged on the engine body (110), and the heat insulation component (200) is configured to block heat generated by the engine body (110) from being transferred into the nacelle body (100).
2. The unmanned aerial vehicle engine compartment of claim 1,
the insulation member (200) comprises an insulation layer (210);
the tail part of the engine main body (110) is provided with a spray pipe, and the thermal insulation layer (210) is wrapped on the surface of the spray pipe.
3. The unmanned aerial vehicle engine nacelle of claim 2,
the thermal insulation layer (210) is made of aerogel thermal insulation material.
4. The unmanned aerial vehicle engine compartment of claim 3,
the insulation member (200) further comprises a fixing member;
the fixture is coupled to the insulating layer (210), the fixture configured to secure the insulating layer (210) to the lance.
5. The unmanned aerial vehicle engine compartment of claim 4,
the fixing piece is arranged to be an insulating wrapping layer (220), and the insulating wrapping layer (220) wraps the outer surface of the insulating layer (210).
6. The unmanned aerial vehicle engine compartment of claim 5,
the heat insulation wrapping layer (220) is made of glass fiber adhesive tape.
7. The unmanned aerial vehicle engine compartment of claim 1,
the unmanned aerial vehicle engine nacelle further comprises a connecting member (300);
the engine main body (110) is connected to the nacelle main body (100) by the connecting member (300).
8. The unmanned aerial vehicle engine compartment of claim 1,
the unmanned aerial vehicle engine compartment further comprises an engine cover (400);
the engine cover (400) is arranged in the accommodating cavity, and the engine cover (400) is configured to wrap the engine main body (110).
9. The unmanned aerial vehicle engine compartment of claim 8,
the hood (400) is connected to the nacelle body (100) by screws.
10. An aircraft, characterized in that it comprises a drone nacelle according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120545231.6U CN214356627U (en) | 2021-03-16 | 2021-03-16 | Unmanned aerial vehicle engine compartment and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120545231.6U CN214356627U (en) | 2021-03-16 | 2021-03-16 | Unmanned aerial vehicle engine compartment and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214356627U true CN214356627U (en) | 2021-10-08 |
Family
ID=77973070
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120545231.6U Active CN214356627U (en) | 2021-03-16 | 2021-03-16 | Unmanned aerial vehicle engine compartment and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214356627U (en) |
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2021
- 2021-03-16 CN CN202120545231.6U patent/CN214356627U/en active Active
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