CN216133350U - Flight control computer and aircraft - Google Patents

Abstract

The application relates to a flight control computer and an aircraft. The flight control computer comprises a first circuit board and a second circuit board which are arranged in a layered mode, wherein the first circuit board is used for configuring a flight control circuit, and the second circuit board is used for configuring an inertia control circuit; the first circuit board is mounted on a bottom plate, a support is mounted on the bottom plate, a fixing plate is mounted on the support, and the second circuit board is mounted on the fixing plate; and a damping structure is arranged between the support and the fixing plate. The scheme that this application provided sets up through making first circuit board and second circuit board layering to make flight control module and inertia control module set up independently mutually, and then reduce cost of maintenance, and, can effectively cushion the vibrations between support and the fixed plate through shock-absorbing structure, make flight control module and inertia control module's installation more stable, thereby improved the security of aircraft.

Description

Flight control computer and aircraft

Technical Field

The application relates to the technical field of aircrafts, in particular to a flight control computer and an aircraft.

Background

The flight control computer is the core part of the aircraft and plays a decisive role in the performance and safety of the aircraft.

In the related art, the flight control computer generally centralizes the inertia control module and the flight control module on the same circuit board, the aircraft can shake during flight, and the shake of the aircraft can cause the circuit board provided with the inertia control module and the flight control module to shake along with the circuit board, so that the flight control circuit or the inertia control circuit is easily damaged, and the safety of the whole aircraft is reduced; in addition, if the flight control circuit is damaged or the inertia control circuit is damaged, the whole circuit board needs to be replaced, and the maintenance cost is high.

SUMMERY OF THE UTILITY MODEL

In order to solve or partially solve the problems existing in the related art, the application provides a flight control computer and an aircraft, wherein the flight control computer can realize the damping effect of a flight control module and an inertia control module of the flight control computer, and the safety of the aircraft is improved.

The present application provides in a first aspect a flight control computer comprising:

the flight control system comprises a first circuit board and a second circuit board which are arranged in a layered mode, wherein the first circuit board is used for configuring a flight control circuit, and the second circuit board is used for configuring an inertia control circuit;

the first circuit board is mounted on a bottom plate, a support is mounted on the bottom plate, a fixing plate is mounted on the support, and the second circuit board is mounted on the fixing plate;

and a damping structure is arranged between the support and the fixing plate.

In one embodiment, the shock-absorbing structure includes a plurality of cushion posts, and the mount is connected to the fixing plate through the plurality of cushion posts.

In one embodiment, the device further comprises a protective cover fixed on the fixing plate;

the protective cover and the fixing plate jointly define an accommodating space, and the second circuit board is arranged in the accommodating space.

In an embodiment, a flexible filling layer is further disposed in the accommodating space, and the flexible filling layer is used for filling a space between the second circuit board and the protective cover.

In one embodiment, the protective cover further comprises a top cover and a side plate connected between the top cover and the bottom plate, and a buffer layer is arranged between the top wall of the protective cover and the top cover.

In one embodiment, the support is connected to the bottom plate through a screw, and a damping gasket is sleeved on the screw and used for buffering the vibration between the support and the bottom plate; and/or

The first circuit board pass through the screw connect in the bottom plate, the cover is equipped with the shock attenuation gasket on the screw, the shock attenuation gasket is used for buffering first circuit board with vibrations between the bottom plate.

In one embodiment, the first circuit board and the second circuit board are connected by a flexible flat cable.

In one embodiment, the material of the flexible filling layer and/or the buffer layer comprises a sponge.

In one embodiment, the first circuit board and the second circuit board are arranged in layers along a longitudinal direction;

the plurality of buffer posts are connected between the support and the fixing plate in a longitudinal direction.

A second aspect of the application provides an aircraft comprising a flight control computer as described above.

The technical scheme provided by the application can comprise the following beneficial effects:

the flight control computer provided by the embodiment of the application comprises a first circuit board and a second circuit board which are arranged in a layered mode, wherein the first circuit board is used for configuring a flight control circuit, and the second circuit board is used for configuring an inertia control circuit; the first circuit board is mounted on a bottom plate, a support is mounted on the bottom plate, a fixing plate is mounted on the support, and the second circuit board is mounted on the fixing plate; the shock-absorbing structure is arranged between the support and the fixed plate, the first circuit board and the second circuit board are arranged in a layered mode, the flight control module and the inertia control module are prevented from being arranged on the same circuit board, maintenance cost is reduced, vibration between the support and the fixed plate can be effectively buffered through the shock-absorbing structure after the layers are arranged, the installation of the flight control module and the inertia control module is further stable, and safety of an aircraft is improved.

It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the application.

Drawings

The foregoing and other objects, features and advantages of the application will be apparent from the following more particular descriptions of exemplary embodiments of the application, as illustrated in the accompanying drawings wherein like reference numbers generally represent like parts throughout the exemplary embodiments of the application.

FIG. 1 is a schematic structural diagram of a flight control computer according to an embodiment of the present disclosure;

FIG. 2 is an exploded view of the flight control computer of FIG. 1;

FIG. 3 is an enlarged partial schematic view of FIG. 1 at A;

FIG. 4 is a schematic view of a portion of the enlarged structure at B in FIG. 1;

fig. 5 is a schematic structural diagram of a flight control computer according to another embodiment of the present application.

Reference numerals:

a flight control computer 10; a first circuit board 100; a second circuit board 200; a base plate 300; a shock-absorbing structure 400; a flexible flat cable 500; a shock-absorbing pad 600; a top cover 700; a side plate 800; a bolt 900; an aviation plug 110; a mounting hole 201; a support 210; a leg 211; a support plane 212; a screw 213; a fixing plate 220; a protective cover 230; a side wall 231; a top wall 232; a flexible filler layer 240; a buffer layer 250; a connecting column 310; a buffer column 410; a screw hole 701; a through hole 801; heat dissipation holes 802.

Detailed Description

Embodiments of the present application will be described in more detail below with reference to the accompanying drawings. While embodiments of the present application are illustrated in the accompanying drawings, it should be understood that the present application may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.

It should be understood that although the terms "first," "second," "third," etc. may be used herein to describe various information, these information should not be limited to these terms. These terms are only used to distinguish one type of information from another. For example, first information may also be referred to as second information, and similarly, second information may also be referred to as first information, without departing from the scope of the present application. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present application, "a plurality" means two or more unless specifically limited otherwise.

In the description of the present application, it is to be understood that the terms "length," "width," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientation or positional relationship indicated in the drawings for convenience in describing the present application and for simplicity in description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed in a particular orientation, and be operated in a particular manner, and are not to be considered limiting of the present application.

Unless expressly stated or limited otherwise, the terms "mounted," "connected," "secured," and the like are intended to be inclusive and mean that, for example, they may be fixedly connected or detachably connected or integrally formed; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.

In the related art, the flight control computer generally concentrates the inertia control module and the flight control module on the same circuit board, the aircraft can shake during flying, the shake of the aircraft can lead to the circuit board provided with the inertia control module and the flight control module to shake along with the circuit board, and then the damage of the flight control circuit or the inertia control circuit is easily caused, so that the safety of the whole aircraft is reduced.

The technical solutions of the embodiments of the present application are described in detail below with reference to the accompanying drawings.

FIG. 1 is a schematic structural diagram of a flight control computer according to an embodiment of the present disclosure; FIG. 2 is an exploded view of the flight control computer of FIG. 1.

Referring to fig. 1-2 together, a flight control computer 10 according to an embodiment of the present application includes: the flight control system comprises a first circuit board 100 and a second circuit board 200 which are arranged in a layered mode, wherein the first circuit board 100 is used for configuring a flight control circuit, and the second circuit board 200 is used for configuring an inertia control circuit; the first circuit board 100 is mounted on the base plate 300, the base plate 300 is mounted with the support 210, the support 210 is mounted with the fixing plate 220, and the fixing plate 220 is mounted with the second circuit board 200; be equipped with shock-absorbing structure 400 between support 210 and the fixed plate 220, through making first circuit board 100 and the setting of second circuit board 200 layering to avoid flight control module and inertia control module to set up in same circuit board, and then reduce cost of maintenance, and, can effectively cushion the vibrations between support 210 and the fixed plate 220 through shock-absorbing structure 400 after the layering sets up, make flight control module and inertia control module's installation more stable, thereby improved the security of aircraft.

The flight control module can also be called as an FCMU module, and is used for accurately measuring and calculating information such as a course angle, a pitch angle and a position of the aircraft so as to improve the stability and maneuverability of the aircraft and improve the task execution capacity.

The inertial control module can also be called an IMU module, i.e., an inertial measurement unit module, and can calculate the attitude of the aircraft through the inertial measurement unit module so as to control the attitude of the aircraft.

In the related art, the flight control computer 10 generally arranges the inertia control module and the flight control module on the same circuit board in a centralized manner, and thus the safety and reliability are low. This application will dispose flight control circuit's first circuit board 100 and dispose inertia control circuit's second circuit board 200 mutually independent setting, avoids first circuit board 100 and second circuit board 200 to set up in same circuit board, and then can reduce cost of maintenance, effectively promotes inertia control module and flight control module's security and reliability. Further, when the aircraft shakes, the shock between the support 210 and the fixing plate 220 is relieved through the shock absorption structure 400, so that the shock on the second circuit board 200 is relieved, the inertia control module is further effectively protected, and the safety of the aircraft is improved.

Fig. 3 is a partially enlarged schematic view of a portion a in fig. 1.

Referring to fig. 1 to 3 together, in some embodiments, the shock absorbing structure 400 includes a plurality of buffer posts 410, and the support 210 and the fixing plate 220 are connected by the plurality of buffer posts 410. Through the buffer column 410 arranged between the support 210 and the fixing plate 220, the vibration of the support 210 and the fixing plate 220 is damped and buffered to avoid the interference between the first circuit board and the second circuit board, and the vibration of the first circuit board 100 and the second circuit board 200 can be slowed down, so that the inertia control module is effectively protected.

In this embodiment, the support 210 has a support leg 211 and a support plane 212, the support 210 is mounted on the base plate 300 through the support leg 211, the mounting holes 201 are respectively opened at corresponding positions between the support plane 212 and the fixing plate 220, and both ends of the buffer column 410 are respectively fixed in the mounting holes 201 on the support 210 and the fixing plate 220, so that the support 210 and the fixing plate 220 are connected through the buffer column 410. Wherein, the fixed plate 220 can be a square flat plate, and a buffering column 410 is respectively arranged at the four corners adjacent to the square flat plate, so that the fixed plate 220 can be stably supported by the four buffering columns 410, and further the installation stability of the second circuit board 200 can be improved.

In some embodiments, the damping pillar 410 may be made of a rubber material, but is not limited to a rubber material, and may also be other structures having a damping function, such as a spring.

In one embodiment, the first circuit board 100 and the second circuit board 200 may be arranged in layers in a longitudinal direction; a plurality of buffer posts 410 are connected between the bracket 210 and the fixing plate 220 in a longitudinal direction. The fixing plate 220 is longitudinally supported by the plurality of buffer posts 410, so that a separated suspension shock absorption structure is formed between the second circuit board 200 and the first circuit board 100, and the shock resistance of the flight control computer 10 is more effectively improved.

In one embodiment, the first circuit board 100 and the second circuit board 200 are connected by a flexible flat cable 500. The flexible flat cable 500 has good flexibility, and the first circuit board 100 and the second circuit board 200 which are separated from each other are electrically connected through the flexible flat cable 500, so that the first circuit board 100 and the second circuit board 200 can keep better electrical connection stability.

Fig. 4 is a partially enlarged schematic view of a portion B in fig. 1.

Referring to fig. 1, fig. 2 and fig. 4, in an embodiment, the support 210 is detachably connected to the base plate 300, for example, the support 210 may be connected to the base plate 300 by a screw 213, and a damping washer 600 is sleeved on the screw 213, and the damping washer 600 can effectively reduce the vibration frequency of the support 210, so that the installation of the inertia control module is more stable.

In some embodiments, the bottom plate 300 is provided with a plurality of connecting columns 310, the support base 210 is provided with a plurality of connecting holes opposite to the connecting columns 310, and a plurality of screws 213 are respectively threaded to the connecting columns 310 after penetrating through the shock absorbing pad 600 and the connecting holes. It is to be understood that the manner of coupling the holder 210 and the base plate 300 is not limited thereto.

In one embodiment, the first circuit board 100 is connected to the base plate 300 through a screw 213, and a shock absorbing pad 600 is sleeved on the screw 213, and the shock absorbing pad 600 is used for buffering the shock between the first circuit board 100 and the base plate 300.

A connection hole may be formed in the first circuit board 100, and the screw 213 penetrates the vibration-damping pad 600 and is screwed to the bottom plate 300. The shock-absorbing pad 600 can effectively buffer the shock of the base plate 300 and the first circuit board 100, and reduce the shock frequency of the base plate 300 and the first circuit board 100, so that the installation of the flight control module is more stable, and the safety of the aircraft is improved. The shock absorbing pad 600 may be a rubber pad, or other pad made of shock absorbing and buffering material, and the embodiment is not limited herein.

In some embodiments, flight control computer 10 further includes a protective cover 230 secured to fixed plate 220; the protective cover 230 and the fixing plate 220 together define a receiving space, and the second circuit board 200 is disposed in the receiving space. Further, the protective cover 230 includes a plurality of sidewalls 231 and a top wall 232 connected to the sidewalls 231, the top wall 232 and the fixing plate 220 together define a receiving space, and the protective cover 230 protects the second circuit board 200 in the receiving space. .

In this embodiment, a flexible filling layer 240 is further disposed in the receiving space in the protective cover, and the flexible filling layer 240 is used for filling the space between the second circuit board 200 and the protective cover 230. The flexible filling layer 240 can protect the second circuit board 200 in the accommodating space, so that components in the second circuit board 200 and internal barometer components are not affected by flowing air. In this embodiment, the flexible filling layer 240 and the portion of the second circuit board 200 corresponding to the protruding electronic component are provided with a nesting hole, and after the flexible filling layer 240 is installed on the second circuit board 200, the component on the second circuit board 200 can be embedded into the nesting hole, so that the hollow area in the accommodating space can be effectively reduced, and the influence of air flow on the barometer component on the second circuit board 200 can be further reduced.

In some embodiments, the material of the flexible filling layer 240 includes, but is not limited to, a sponge, and may also be other materials capable of having a buffering capacity, and is not limited herein. Fig. 5 is a schematic structural diagram of a flight control computer according to another embodiment of the present application.

Referring to fig. 5, in some embodiments, the flight control computer 10 further includes a top cover 700 and a side plate 800 connected between the top cover 700 and the bottom plate 300, and a buffer layer 250 is disposed between the top wall 232 of the protective cover 230 and the top cover 700. The top cover 700, the side plates 800 and the bottom plate 300 together form a casing of the flight control computer 10, and the first circuit board 100 and the second circuit board 200 are disposed in the casing. Wherein the first circuit board 100 is connected with a plurality of aviation plugs 110. The buffer layer 250 disposed between the top wall 232 of the protective cover 230 and the top cover 700 can reduce the vibration between the protective cover 230 and the top cover 700, and further reduce the vibration of the fixing plate 220 and the second circuit board 200 on the fixing plate 220, thereby enhancing the protection effect on the second circuit board 200. Further, the side plate 800 is provided with a plurality of heat dissipation holes 802 for dissipating heat of the flight control computer 10.

Further, buffer layer 250 isolates the top of protective cover 230 from top cover 700, avoiding the contact between the top of protective cover 230 and top cover 700, and because of the shock absorption and buffering effect of buffer layer 250, the shock transmitted to buffer column 410 is weakened, thereby improving the shock absorption capability of buffer column 410.

In this embodiment, the bottom plate 300 and the top cover 700 may be square plates, the bottom plate 300 and the top cover 700 are respectively provided with an assembling hole and a screwing hole 701 in an aligned manner, the side plate 800 disposed between the bottom plate 300 and the top cover 700 is correspondingly provided with a through hole 801, the assembling hole and the through hole 801 are sequentially penetrated through by bolts 900 and screwed into the screwing hole 701, so that the bottom plate 300, the side plate 800 and the top cover 700 are connected.

In some embodiments, the material of the buffer layer 250 includes, but is not limited to, sponge, and may also be other materials capable of having a buffering capacity, and is not limited herein.

The flight control computer 10 of this application through with first circuit board 100 and second circuit board 200 layering setting to set up shock-absorbing structure 400 between first circuit board 100 and second circuit board 200, cooperation buffer layer 240 and shock attenuation gasket 600's setting can strengthen flight control module and inertial control module's shock attenuation buffer capacity, thereby has improved the security of aircraft.

The above embodiment describes the flight control computer 10 provided in the embodiment of the present application, and accordingly, the present application further provides an embodiment of an aircraft, where the aircraft provided in the embodiment includes the flight control computer 10 described in any of the above embodiments.

The flight control computer 10 of the aircraft provided by the embodiment comprises a first circuit board 100 and a second circuit board 200 which are arranged in a layered manner, wherein the first circuit board 100 is used for configuring a flight control circuit, and the second circuit board 200 is used for configuring an inertia control circuit; the first circuit board 100 is mounted on the base plate 300, the base plate 300 is mounted with the support 210, the support 210 is mounted with the fixing plate 220, and the fixing plate 220 is mounted with the second circuit board 200; a shock-absorbing structure 400 is provided between the support 210 and the fixing plate 220. Through making first circuit board 100 and second circuit board 200 layering setting to make flight control module and inertia control module alternate segregation, and then reduce cost of maintenance, and, can effectively cushion the vibrations between support 210 and the fixed plate 220 through shock-absorbing structure 400 after the layering sets up, make flight control module and inertia control module's installation more stable, thereby improved the security of aircraft.

The aspects of the present application have been described in detail hereinabove with reference to the accompanying drawings. In the above embodiments, the descriptions of the respective embodiments have respective emphasis, and for parts that are not described in detail in a certain embodiment, reference may be made to related descriptions of other embodiments. Those skilled in the art should also appreciate that the acts and modules referred to in the specification are not necessarily required in the present application. In addition, it can be understood that the steps in the method of the embodiment of the present application may be sequentially adjusted, combined, and deleted according to actual needs, and the modules in the device of the embodiment of the present application may be combined, divided, and deleted according to actual needs.

Having described embodiments of the present application, the foregoing description is intended to be exemplary, not exhaustive, and not limited to the disclosed embodiments. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments. The terminology used herein is chosen in order to best explain the principles of the embodiments, the practical application, or improvements made to the technology in the marketplace, or to enable others of ordinary skill in the art to understand the embodiments disclosed herein.

Claims (10)

1. A flight control computer, comprising:

the flight control system comprises a first circuit board and a second circuit board which are arranged in a layered mode, wherein the first circuit board is used for configuring a flight control circuit, and the second circuit board is used for configuring an inertia control circuit;

the first circuit board is mounted on a bottom plate, a support is mounted on the bottom plate, a fixing plate is mounted on the support, and the second circuit board is mounted on the fixing plate;

and a damping structure is arranged between the support and the fixing plate.

2. The flight control computer of claim 1, wherein:

the shock-absorbing structure comprises a plurality of buffer columns, and the support is connected with the fixing plate through the buffer columns.

3. The flight control computer of claim 1, wherein:

the protective cover is fixed on the fixed plate;

the protective cover and the fixing plate jointly define an accommodating space, and the second circuit board is arranged in the accommodating space.

4. The flight control computer of claim 3, wherein:

and a flexible filling layer is further arranged in the accommodating space and used for filling the space between the second circuit board and the protective cover.

5. The flight control computer of claim 4, wherein:

the protective cover further comprises a top cover and a side plate connected between the top cover and the bottom plate, and a buffer layer is arranged between the top wall of the protective cover and the top cover.

6. The flight control computer of claim 1, wherein:

the support is connected to the bottom plate through a screw, a damping gasket is sleeved on the screw and used for buffering vibration between the support and the bottom plate; and/or

The first circuit board pass through the screw connect in the bottom plate, the cover is equipped with the shock attenuation gasket on the screw, the shock attenuation gasket is used for buffering first circuit board with vibrations between the bottom plate.

7. The flight control computer of any one of claims 1-6, wherein:

the first circuit board is connected with the second circuit board through a flexible flat cable.

8. The flight control computer of claim 5, wherein:

the material of the flexible filling layer and/or the buffer layer comprises sponge.

9. The flight control computer of claim 2, wherein:

the first circuit board and the second circuit board are arranged in layers along the longitudinal direction;

the plurality of buffer posts are connected between the support and the fixing plate in a longitudinal direction.

10. An aircraft, characterized in that it comprises a flight control computer according to any one of claims 1 to 9.

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