CN217767339U

CN217767339U - Machine case of airborne small computer

Info

Publication number: CN217767339U
Application number: CN202221324166.5U
Authority: CN
Inventors: 丁瑞翔; 华种; 叶懋刚; 雷波; 徐超亮; 王思学
Original assignee: CETC 52 Research Institute
Current assignee: CETC 52 Research Institute
Priority date: 2022-05-30
Filing date: 2022-05-30
Publication date: 2022-11-08
Anticipated expiration: 2032-05-30

Abstract

The utility model discloses a machine carries small-size computer's quick-witted case, including quick-witted case body, mainboard, expansion board and navigation picture peg, wherein: the chassis body comprises a front panel and a rear panel which are arranged oppositely, a first side panel and a second side panel which are arranged oppositely, and a cover panel and a bottom panel which are arranged oppositely, wherein each panel forms a hexahedral structure chassis with a cavity. The main board and the expansion board are directly and electrically connected with the aviation plugboard for data transmission, and then the data on the aviation plugboard is transmitted with other equipment on the airplane through the aviation socket, so that the design can discriminate the real-time data of the airplane in the flying process and make a quick response, and the efficiency of processing the real-time data is improved; the whole design of this machine case is guaranteeing under the safe prerequisite, improves heat dispersion greatly, simultaneously, and machine incasement portion overall arrangement is compact, and the structure is few, accords with the miniaturized, the lightweight requirement of airborne computer, and environmental suitability is strong, convenient maintenance.

Description

Machine case of airborne small computer

Technical Field

The utility model belongs to airborne computer field, concretely relates to machine case of airborne small-size computer.

Background

During the flight of an aircraft, flight parameters play a decisive role in the safety of the aircraft, so that a computer is required to make a quick response to the real-time data which affect the safety. Meanwhile, for non-real-time data, the computer can delay processing according to actual conditions. With the rapid development of military aircrafts, the requirements on miniaturization and light weight are higher and higher. The fuel consumption of the aircraft is closely related to the weight of the aircraft, and how to reduce the weight of airborne equipment is the key for improving the endurance capacity of the aircraft. Along with the development of small unmanned aerial vehicles such as reconnaissance unmanned aerial vehicle, also stricter to airborne equipment's miniaturization requirement.

In the prior art, all board cards in a computer used by an airplane are connected with a passive backboard through a socket, signals are transmitted to a navigation plug board through the passive backboard, and then the signals are transmitted to other equipment on the airplane through the navigation plug board. According to the hardware architecture, each board card needs to interact with the passive backboard firstly and then transmit the data to the aviation plug board, and the response speed of the data is low. Simultaneously, passive backplate and rather than the integrated circuit board of pegging graft all need the cold drawing structure to consolidate and dispel the heat, lead to whole machine size can't further reduce, and integrated circuit board cold drawing and passive backplate reinforced structure will also lead to the increase of complete machine weight, and the mainboard of current computer makes independent module, its heat dissipation chip is with heat transfer to the cold drawing structure on earlier, again through the cold drawing structure with heat transfer to quick-witted case, and the cold drawing and the contact surface of quick-witted case will increase the thermal resistance of chip to quick-witted case surface, make the heat dissipation of chip more difficult.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to solve the problem of proposing in the background art, propose a machine case of airborne small-size computer.

In order to achieve the above purpose, the utility model adopts the following technical scheme:

the utility model provides a machine case of machine carries small-size computer, including quick-witted case body, mainboard, expansion board and navigation picture peg, wherein:

the chassis body comprises a front panel and a rear panel which are arranged oppositely, a first side panel and a second side panel which are arranged oppositely, and a cover panel and a bottom panel which are arranged oppositely, wherein each panel forms a hexahedral structure with a cavity.

The mainboard is installed in the inside wall of first side panel.

And an expansion plate mounted on the inner side wall of the second side panel.

The aviation flashboard is arranged on the inner side wall of the front panel and is electrically connected with the main board and the expansion board respectively.

Preferably, the outer side walls of the first side panel, the second side panel and the cover panel are provided with radiating fins.

Preferably, the case of the on-board small computer further includes a power panel mounted to an inner sidewall of the rear panel.

Preferably, the case of the onboard small computer further comprises at least one aviation socket, and the aviation socket is connected with the aviation plug board and penetrates through the front panel.

Preferably, a first high-speed connector, a second high-speed connector and a third high-speed connector are sequentially arranged on the main board, the expansion board and the navigation plug board, and the third high-speed connector is correspondingly connected with the first high-speed connector and the second high-speed connector respectively and is used for realizing that the navigation plug board is electrically connected with the main board and the expansion board respectively.

Preferably, the aviation plug board comprises a first flexible portion, a second flexible portion, a first rigid portion and two second rigid portions, each flexible portion is a cable, two ends of each flexible portion are respectively connected with the first rigid portion and the second rigid portion, the first rigid portion is respectively connected with the front panel and the aviation socket, and the third high-speed connector is mounted on the second rigid portion.

Compared with the prior art, the beneficial effects of the utility model are that:

1. the main board and the expansion board are directly and electrically connected with the aviation plugboard to transmit data, and then the data on the aviation plugboard is transmitted with other equipment on the airplane through the aviation socket, so that the design can discriminate real-time data of the airplane in the flying process and make quick response, and the efficiency of processing the real-time data is improved;

2. the whole design of this machine case improves heat dispersion greatly under the prerequisite of guaranteeing safety, and simultaneously, the inside overall arrangement of machine case is compact, and the structure is few, accords with the requirement of machine-borne computer miniaturization, lightweight, and environmental suitability is strong, convenient maintenance.

Drawings

Fig. 1 is a schematic view of the overall structure of the case of the onboard small computer of the present invention;

FIG. 2 is a schematic view of the case of the onboard small computer of the present invention with the cover panel removed;

FIG. 3 is a schematic view of the case of the onboard small computer according to the present invention;

FIG. 4 is a schematic structural view of the main board of the present invention;

fig. 5 is a schematic structural view of the expansion board of the present invention;

fig. 6 is a schematic structural view of the aviation plug board of the present invention;

FIG. 7 is a schematic view of the case of the onboard small computer according to the present invention;

fig. 8 is a block diagram of the case of the onboard small computer according to the present invention.

Description of reference numerals: 1. a chassis body; 11. a front panel; 12. a rear panel; 13. a first side panel; 14. a second side panel; 15. a cover panel; 16. a bottom panel; 2. a main board; 3. an expansion board; 4. an aviation plug board; 41. a first flexible portion; 42. a second flexible portion; 43. a first rigid portion; 44. a second rigid portion; 5. an aviation socket; 6. a heat dissipating blade; 7. a first high-speed connector; 8. a power panel; 9. a second high speed connector; 10. and a third high-speed connector.

Detailed Description

The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only a part of the embodiments of the present application, and not all of the embodiments. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments in the present application without making any creative effort belong to the protection scope of the present application.

It will be understood that when an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may also be present. Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used in the description of the present application herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the application.

As shown in fig. 1 to 8, a chassis of an airborne small computer includes a chassis body 1, a main board 2, an expansion board 3, and an aviation plug board 4, wherein:

the chassis body 1 includes a front panel 11 and a rear panel 12 disposed opposite to each other, a first side panel 13 and a second side panel 14 disposed opposite to each other, and a cover panel 15 and a bottom panel 16 disposed opposite to each other, each of which forms a hexahedral structure with a cavity.

The main board 2 is mounted on the inner side wall of the first side board 13.

The extension plate 3 is attached to the inner side wall of the second side plate 14.

And the aviation plug board 4 is arranged on the inner side wall of the front panel 11 and is respectively and electrically connected with the main board 2 and the expansion board 3.

Specifically, taking fig. 1 as an example, the front panel 11 is located at the front side of the rear panel 12, the first side panel 13 is located at the left side of the second side panel 14, the cover panel 15 is located above the bottom panel 16, two panels in each contact are fixedly connected through screws, the main board 2 is fixedly installed on the inner side wall of the first side panel 13, the expansion board 3 is fixedly installed on the inner side wall of the second side panel 14, and the navigation board 4 is fixedly installed on the inner side wall of the front panel 11, which are only convenient for description and are not limited to specific orientations. The internal space of the case of the airborne small computer is very compact, the airborne miniaturization requirement can be met, the entire case is designed in a sealed mode, the case has good resistance to sand dust, can be used in a desert environment, and is strong in environmental adaptability.

Referring to fig. 8, in the present embodiment, the chassis of the local small computer adopts a hardware architecture without a passive backplane, and the main board 2 integrates chips and sub-cards for processing real-time data of the aircraft, such as those including a CPU, an electronic disk and at least one main board sub-card; the expansion board 3 has integrated thereon chips and daughter cards for processing non-real-time data of the aircraft, such as those chips and daughter cards including at least one expansion board daughter card. It should be noted that the real-time data refers to data that a computer needs to make in time during the flight of the aircraft, such as the pitch angle of the aircraft; non-real-time data refers to data that does not require immediate processing during flight of the aircraft, such as compression or editing of a captured photograph. The hardware architecture enables the main board 2 to discriminate the importance of the data, makes a quick response to the real-time data affecting the security, and completes the processing of the non-real-time data by the expansion board 3 on the premise of not affecting the processing speed of the real-time data. Mainboard 2 and expansion board 3 all are connected with 4 electricity on-board, carry out data transmission.

The structure of the case of the onboard small computer can quickly conduct the heat of all parts (such as chips) with heat dissipation risks in the case body 1 to the surface of the case body 1, and then the heat is dissipated to the air through the wall surface of the case body 1. Such as the main board 2 and the extension board 3, can dissipate heat by being attached to the first side panel 13 and the second side panel 14, respectively.

As shown in fig. 7, when the main board 2 is to be maintained, the first side board 13 is removed; when maintenance is performed on the extension board 3, the second side panel 14 is removed.

In one embodiment, the outer side walls of the first side panel 13, the second side panel 14 and the cover panel 15 are provided with cooling fins 6.

Specifically, for strengthening the heat dissipation, the equal fixedly connected with heat dissipation tooth piece 6 of lateral wall of first side board 13, second side board 14 and cover panel 15, and the quantity of heat dissipation tooth piece 6 is at least one, can set up according to actual need, improves the heat-sinking capability of the quick-witted case of whole machine year microcomputer greatly.

The scheme that the heat dissipation toothed sheet 6 and the wall surface of the case body 1 dissipate heat simultaneously can ensure that the case of the onboard small computer can work normally at a high temperature of 70 ℃ when the power consumption of the case of the onboard small computer is 50-100W, and further shows strong environmental adaptability.

In one embodiment, the housing of the onboard small computer further comprises a power panel 8, and the power panel 8 is mounted on the inner side wall of the rear panel 12.

Specifically, the power board 8 is fixedly installed on the inner side wall of the rear panel 12, and supplies power to the main board 2 and the expansion board 3 through the connection socket.

In one embodiment, the housing of the onboard small computer further comprises at least one aviation socket 5, wherein the aviation socket 5 is connected with the aviation board 4 and penetrates through the front panel 11.

Specifically be, be equipped with the through-hole that corresponds with aviation socket 5 on the front panel 11, aviation socket 5 and 4 fixed connection of aviation plugboard, and pass the through-hole and extend to the outside of front panel 11, be connected aviation plugboard 4 and other equipment electricity on the aircraft through aviation socket 5, carry out data transmission, the quantity of aviation socket 5 can set up according to actual need, if the quantity of aviation socket 5 is three.

In an embodiment, the main board 2, the expansion board 3, and the aviation plug board 4 are sequentially provided with a first high-speed connector 7, a second high-speed connector 9, and a third high-speed connector 10, and the third high-speed connector 10 is correspondingly connected to the first high-speed connector 7 and the second high-speed connector 9, respectively, so as to electrically connect the aviation plug board 4 to the main board 2 and the expansion board 3, respectively.

Specifically, as shown in fig. 7, the first high-speed connector 7, the second high-speed connector 9, and the third high-speed connector 10 are sequentially and correspondingly integrated on the motherboard 2, the expansion board 3, and the aviation plug board 4, and there are two third high-speed connectors 10, which are respectively in butt joint with the first high-speed connector 7 and the second high-speed connector 9, so as to implement data transmission between the aviation plug board 4 and the motherboard 2 and the expansion board 3.

In one embodiment, the aviation board 4 includes a first flexible portion 41, a second flexible portion 42, a first rigid portion 43, and two second rigid portions 44, each flexible portion is a cable, both ends of each flexible portion are respectively connected with the first rigid portion 43 and the second rigid portion 44, the first rigid portion 43 is respectively connected with the front panel 11 and the aviation socket 5, and the third high-speed connector 10 is mounted on the second rigid portion 44.

Specifically, as shown in fig. 6, both ends of each flexible portion are fixedly connected to the first rigid portion 43 and the second rigid portion 44, the aviation socket 5 and the front panel 11 are fixedly connected to the first rigid portion 43, and the third high-speed connector 10 is integrated on the second rigid portion 44. If each flexible part is a cable, the aviation plug board 4 adopts the flexible part, so that the maintenance is convenient.

The main board and the expansion board are directly and electrically connected with the aviation plugboard to transmit data, and then the data on the aviation plugboard is transmitted with other equipment on the airplane through the aviation socket, so that the design can discriminate real-time data of the airplane in the flying process and make quick response, and the efficiency of processing the real-time data is improved; the whole design of this machine case improves heat dispersion greatly under the prerequisite of guaranteeing safety, and simultaneously, the inside overall arrangement of machine case is compact, and the structure is few, accords with the requirement of machine-borne computer miniaturization, lightweight, and environmental suitability is strong, convenient maintenance.

The technical features of the embodiments described above may be arbitrarily combined, and for the sake of brevity, all possible combinations of the technical features in the embodiments described above are not described, but should be considered as being within the scope of the present specification as long as there is no contradiction between the combinations of the technical features.

The above-mentioned embodiments only express the more specific and detailed embodiments described in the present application, but not be construed as limiting the claims. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the concept of the present application, which falls within the scope of protection of the present application. Therefore, the protection scope of the present patent shall be subject to the appended claims.

Claims

1. The utility model provides a machine case of machine carries small-size computer which characterized in that: including quick-witted case body (1), mainboard (2), expansion board (3) and aviation picture peg (4), wherein:

the chassis body (1) comprises a front panel (11) and a rear panel (12) which are oppositely arranged, a first side panel (13) and a second side panel (14) which are oppositely arranged, and a cover panel (15) and a bottom panel (16) which are oppositely arranged, wherein each panel forms a hexahedral structure with a cavity;

the main board (2) is arranged on the inner side wall of the first side panel (13);

the expansion board (3) is arranged on the inner side wall of the second side panel (14);

the aviation flashboard (4) is arranged on the inner side wall of the front panel (11) and is electrically connected with the main board (2) and the expansion board (3) respectively.

2. The case of an on-board small computer as set forth in claim 1, wherein: and the outer side walls of the first side panel (13), the second side panel (14) and the cover panel (15) are provided with radiating fins (6).

3. The case of an on-board small computer as set forth in claim 1, wherein: the case of the airborne small computer further comprises a power panel (8), and the power panel (8) is installed on the inner side wall of the rear panel (12).

4. The case of an on-board small computer as set forth in claim 1, wherein: the case of the airborne small computer further comprises at least one aviation socket (5), wherein the aviation socket (5) is connected with the aviation plugboard (4) and penetrates through the front panel (11).

5. The case of an on-board small computer as set forth in claim 4, wherein: mainboard (2), expansion board (3) and navigation picture peg (4) are gone up and are equipped with first high speed connector (7), second high speed connector (9) and third high speed connector (10) in proper order, just third high speed connector (10) correspond with first high speed connector (7) and second high speed connector (9) respectively and are connected, are used for realizing navigation picture peg (4) respectively with mainboard (2) and expansion board (3) electricity are connected.

6. The case of an on-board small computer as set forth in claim 5, wherein: aviation picture peg (4) include first flexible portion (41), second flexible portion (42), first rigidity portion (43) and two second rigidity portions (44), each the flexible portion is the cable, both ends respectively with first rigidity portion (43) are connected and second rigidity portion (44) are connected, first rigidity portion (43) respectively with front panel (11) and aviation socket (5) are connected, third high speed connector (10) install in on second rigidity portion (44).