CN115620425B

CN115620425B - High overload aircraft recorder

Info

Publication number: CN115620425B
Application number: CN202211572794.XA
Authority: CN
Inventors: 付元
Original assignee: Hunan Gaozhi Technology Co ltd
Current assignee: Hunan Gaozhi Technology Co ltd
Priority date: 2022-12-08
Filing date: 2022-12-08
Publication date: 2023-04-28
Anticipated expiration: 2042-12-08
Also published as: CN115620425A

Abstract

The present application relates to a high overload aircraft recorder including a circuit core board for collecting and backing up data of an aircraft. The inner shell forms an integrated and fixedly connected inner core body through the electrical pouring sealant pouring and sealing the circuit core board. The middle shell is provided with a polytetrafluoroethylene pad on the first buffer pad on one side of the middle shell where the middle cover opening is arranged on one side of the inner core body in the vertical direction, and the middle cover opening is closed by the polytetrafluoroethylene pad. The shell body is provided with a second buffer pad on two sides in the vertical direction of the middle core body respectively, epoxy pouring sealant is poured on the periphery of the middle core body, an outer cover opening is formed in one side in the vertical direction of the middle core body, the outer cover body is used for sealing the outer cover opening and fixedly connected with the shell body, the outer cover body is provided with a data pre-reading opening and a plugging piece, and the plugging piece is used for plugging the data pre-reading opening. And each body is provided with a lead hole for penetrating the data wire of the circuit core board. The protective performance is high.

Description

High overload aircraft recorder

Technical Field

The application relates to the technical field of data recording equipment, in particular to a high overload aircraft recorder.

Background

With the continuous development of aircraft technology, the data recorder is commonly used for backup recording of flight data of a test aircraft, has high scientific research value, and is especially used in application scenes without telemetry signals or with unsmooth reception of telemetry signals. In the case of high overload and continuous overload, etc., the data logger is often damaged or broken when dropped on the ground, resulting in that the data in the data logger cannot be effectively read or recovered. Although various protection designs are adopted by various traditional recorders applied to the aircraft, in the process of realizing the invention, the inventor discovers that the protection technology adopted by the traditional aircraft recorder still has the technical problem of poor protection performance under the condition of high overload.

Disclosure of Invention

Based on this, it is necessary to provide a high overload aircraft recorder in view of the above technical problems.

In order to achieve the above object, the embodiment of the present invention adopts the following technical scheme:

the utility model provides a high overload aircraft record appearance, includes circuit core, inner shell, well casing, well lid, outer casing and outer lid, and circuit core is used for gathering and backing up the data of aircraft;

the circuit core board is connected with the inner shell through screws and is fixed in the inner shell through column pads, the inner shell is used for encapsulating the circuit core board through electric pouring sealant, and an inner core body which is integrally and fixedly connected with the circuit core board is formed;

the middle shell is used for accommodating the inner core body, the two sides of the middle shell in the vertical direction of the inner core body are provided with first buffer pads, the periphery of the inner core body is filled with silicon rubber, the middle shell is provided with a middle cover opening on one side of the inner core body in the vertical direction, the first buffer pads on the side where the middle cover opening is located are provided with polytetrafluoroethylene pads, the middle cover opening is sealed by the polytetrafluoroethylene pads, and the middle cover body is mechanically connected with the middle shell to form a middle core body;

the outer shell is used for accommodating the middle core body, the two sides of the middle core body in the vertical direction are respectively provided with a second buffer pad, the periphery of the middle core body is filled with epoxy pouring sealant, one side of the outer shell in the vertical direction of the middle core body is provided with an outer cover opening, the outer cover opening is sealed by the outer cover body and is fixedly connected with the outer shell, the outer cover body is provided with a data pre-reading opening and a plugging piece, and the plugging piece is used for plugging the data pre-reading opening;

and the inner shell, the middle shell and the outer shell are respectively provided with a lead hole, the lead holes are used for penetrating the data wires of the circuit core board, the data wires comprise a pre-reading wire and a backup transmission wire, the connectors of the pre-reading wire are arranged at the data pre-reading port, and the backup transmission wire is used for connecting the data acquisition source of the aircraft.

In one embodiment, the inner housing is an aluminum alloy housing.

In one embodiment, the middle shell is a high strength alloy steel shell and the middle cover is a high strength alloy steel cover.

In one embodiment, the silicone rubber is GD401 silicone rubber.

In one embodiment, the outer shell is an aluminum alloy shell and the outer cover is an aluminum alloy cover.

In one embodiment, the data pre-reading port is a threaded hole and the blocking member is a screw plug.

In one embodiment, the first cushion pad is an aircraft rubber cushion pad of perforated construction.

In one embodiment, the second cushion pad is an aircraft rubber cushion pad of perforated construction.

In one embodiment, each of the lead holes is plugged with poured GD704 silicone rubber.

In one embodiment, the inner housing is a cylindrical or spherical structure.

One of the above technical solutions has the following advantages and beneficial effects:

according to the high overload aircraft recorder, the circuit core plates used for collecting and backing up the data of the aircraft are encapsulated through the electrical pouring sealant, the circuit core plates are integrated into a whole to form an inner layer protection effect, the middle shell and the middle cover are used, the middle layer protection design is carried out by matching the first buffer pad, the poured silicon rubber and the polytetrafluoroethylene pad, and finally the outer shell and the outer cover are adopted, and the outer layer protection design is carried out by matching the second buffer pad and the poured epoxy pouring sealant, so that the recorder can be used on the high overload aircraft under the condition of multiple impact, the outer shell can be allowed to be damaged, the breakage can be carried out to absorb part of energy, the middle shell is allowed to deform, the basic appearance of the recorder is ensured, and the inner core in the middle shell is not deformed. In addition, due to the factors such as buffer pads, glue solution and the like in each protective shell layer, overload energy can be effectively absorbed, peak values of shock impact can be weakened, impact on a circuit core board is greatly reduced, and the purpose that the protective performance of the recorder is high under the condition of high overload is achieved.

Drawings

In order to more clearly illustrate the technical solutions of embodiments or conventional techniques of the present application, the drawings required for the descriptions of the embodiments or conventional techniques will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present application, and other drawings may be obtained according to these drawings without inventive effort for a person of ordinary skill in the art.

FIG. 1 is a schematic diagram of a high overload aircraft recorder in one embodiment;

fig. 2 is a schematic view of a physical section of a high overload aircraft recorder in one embodiment.

Detailed Description

In order to make the objects, technical solutions and advantages of the present application more apparent, the present application will be further described in detail with reference to the accompanying drawings and examples. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the present application.

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 herein in the description of the application is for the purpose of describing particular embodiments only and is not intended to be limiting of the application.

It is noted that reference herein to "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment may be included in at least one embodiment of the invention. The appearances of the phrase in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of other embodiments.

Those skilled in the art will appreciate that the embodiments described herein may be combined with other embodiments. The term "and/or" as used in the present specification and the appended claims refers to any and all possible combinations of one or more of the associated listed items, and includes such combinations.

Embodiments of the present invention will be described in detail below with reference to the attached drawings in the drawings of the embodiments of the present invention.

Referring to fig. 1, in one embodiment, a high overload aircraft recorder 100 is provided that includes a circuit core 11, an inner housing 12, a middle housing 13, a middle cover 14, an outer housing 15, and an outer cover 16. The circuit core board 11 is used to collect and back up data of the aircraft. The circuit core board 11 is connected with the inner shell 12 through screws and is fixed in the inner shell 12 through column pads, and the inner shell 12 is used for encapsulating the circuit core board 11 through electric pouring sealant, so that an integrally and fixedly connected inner core body is formed with the circuit core board 11.

The middle shell 13 is used for accommodating an inner core body, the two sides of the middle shell 13 in the vertical direction of the inner core body are provided with first buffer pads 131, silicone rubber is poured on the periphery of the inner core body, the middle shell 13 is provided with a middle cover opening on one side of the inner core body in the vertical direction, the first buffer pads 131 on the side where the middle cover opening is located are provided with polytetrafluoroethylene pads 132, and the middle cover body 14 is used for sealing the middle cover opening through the polytetrafluoroethylene pads 132 and is mechanically connected with the middle shell 13 to form a middle core body. The outer shell 15 is used for accommodating the middle core, the two sides of the middle core in the vertical direction are respectively provided with a second buffer cushion 151, epoxy pouring sealant is poured on the periphery of the middle core, the outer shell 15 is provided with an outer cover opening on one side of the middle core in the vertical direction, the outer cover 16 is used for sealing the outer cover opening and fixedly connected with the outer shell 15, the outer cover 16 is provided with a data pre-reading opening and a plugging piece 152, and the plugging piece 152 is used for plugging the data pre-reading opening. The inner shell 12, the middle shell 13 and the outer shell 15 are respectively provided with a lead hole 101, the lead holes 101 are used for penetrating data wires of the circuit core board 11, the data wires comprise pre-reading wires and backup transmission wires, joints of the pre-reading wires are arranged at the data pre-reading ports, and the backup transmission wires are used for connecting data acquisition sources of the aircraft.

It is understood that the inner housing 12 may be an inner housing made of an alloy material or composite material having a certain structural strength, such as, but not limited to, titanium alloy, carbon fiber, or aluminum alloy. The shape and size of the inner housing 12 may be flexibly selected according to the shape and size of the actually used circuit core board 11, for example, when the size of the circuit core board 11 (typically in the form of a printed board) is small, the inner housing 12 may also be in the form of a multi-layer cloth board, and the overall shape thereof may be adjusted accordingly, for example, but not limited to, a column shape, an oval shape, a sphere shape, or a hemispherical shape. The circuit core board 11 can be fixed on the inner shell 12 through screws, column pads and the like, and is encapsulated by using an electrical potting adhesive, and after the adhesive is dried, the circuit core board 11 and the inner shell 12 can be integrated into a whole, which is called an inner core body. The data lines of the circuit board 11 may be led out through holes or grooves (e.g., on one side) formed in the inner housing 12. The inner shell 12 is used for ensuring the basic shape of the inner core body to be good, and has certain structural strength, and the matching of the inner shell 12 and the electrical pouring sealant can ensure the shape of the circuit core board 11 to be good and the cementing strength under the condition of high overload.

The middle housing 13 and the middle cover 14 are housings and covers made of high strength materials such as, but not limited to, high strength alloy steel, titanium alloy, or other high strength alloy materials. The shape and size of the middle case 13 and the middle cover 14 may also be determined according to the shape and size of the inner core, etc. The inner core body is placed in the middle shell 13, in order to facilitate description, the placing state of the overload aircraft recorder 100 as shown in fig. 1 can be used as a benchmark, the upper side and the lower side of the inner core body are respectively provided with a first buffer pad 131 in the vertical direction, the periphery of the inner core body is filled with silicone rubber liquid, when the silicone rubber liquid is filled, certain pre-pressing is carried out on the inner core body, after the silicone rubber liquid is completely dried, the upper layer (the side departing from the inner core body) of the first buffer pad 131 on the side where the middle cover opening is located in the vertical direction of the inner core body is provided with a polytetrafluoroethylene pad 132, and the middle cover body 14 is used for sealing and fastening to meet the moment requirement required in the practical application environment, and the data line of the circuit core board 11 can be led out through the lead hole 101 on the side surface of the middle shell 13. The inner core body encapsulated by the middle case 13 and the middle cover 14 is called a middle core body. The middle shell 13 and the middle cover 14 are used for preventing the inner core from being deformed by impact, thus allowing deformation at the moment of impact grounding, maintaining structural integrity, the inner first buffer pad 131 is used for absorbing shock and energy of the inner core in the vertical direction, and the poured silicon rubber layer can strengthen the buffer effect to the greatest extent and isolate the impact effect from the inner core to the greatest extent.

The outer shell 15 and the outer shell 16 are shells and covers made of materials with certain strength, and can be made of alloy materials with different strengths or materials according to different impact overload sizes required to be born in practical application scenes, for example, but not limited to shells and covers made of various aluminum alloys or other high polymer composite materials with different strengths. The shape and size of the outer shell 15 and the outer shell 16 can also be determined according to the shape and size of the central core, taking into account the need for installation on a carrier aircraft. The outer casing 15 and the outer casing 16 are used for guaranteeing the basic shape of the recorder, and allow fracture deformation to absorb energy at the moment of impact grounding, wherein the second buffer pad 151 is significantly larger than the first buffer pad 131 in size and thickness so as to be used for absorbing the shock impact and energy in the vertical direction of the middle core body greatly, and the poured epoxy pouring sealant is used for protecting and fixing the middle core body, so that the overall protection effect is enhanced.

After the middle core body is manufactured, the middle core body is placed in the outer shell body 15, as shown in fig. 1, the upper side and the lower side of the middle core body are respectively provided with a second buffer cushion 151, the periphery of the middle core body is filled with epoxy potting adhesive, when the adhesive is filled, the middle core body is subjected to certain prepressing, after the adhesive is completely dried, the outer shell body 16 is used for sealing and fastening, so that the moment requirement required in the practical application environment is met. The data line of the circuit core board 11 may be led out through the lead hole 101 on the side of the outer shell 15, where the data line may include at least two paths of a pre-reading line and a backup transmission line, where the pre-reading line is set in the data pre-reading port through its connector, so that after the test of the aircraft (also called carrier aircraft of the recorder), the data in the recorder may be read from the data pre-reading port; the backup transmission line may be used to connect data acquisition sources deployed on the aircraft to collect and store test data for the aircraft. The data line can be any one or a combination of several types of data lines commonly used in the field, and specifically can be selected according to the requirements of data transmission and reading in practical application scenes.

The data pre-reading port may be a mechanical connection port of a screw port, a bayonet or other connection modes, and the plugging member 152 is a mechanical component matched with the mechanical structure of the data pre-reading port, and may be a plugging member 152 in a screw, a buckle or other structural forms. The first cushion pad 131 is smaller than the second cushion pad 151 in structural dimension, the first cushion pad 131 and the second cushion pad 151 can be made of the same material, and can also be made of different materials, and the two cushion pads can be of a discrete type (namely, formed by a plurality of independent and discretely distributed cushion pads) structure or an integrated type structure.

According to the high overload aircraft recorder 100, the circuit core plates 11 for collecting and backing up the data of the aircraft are encapsulated by the inner shell 12 through the electrical pouring sealant, the circuit core plates 11 are integrated to form an inner layer protection effect, the middle shell 13 and the middle cover 14 are used, the middle layer protection design is carried out by matching the first buffer pad 131, the poured silicon rubber and the polytetrafluoroethylene pad 132, and finally the outer shell 15 and the outer cover 16 are adopted, and the second buffer pad 151 and the poured epoxy pouring sealant are matched to carry out an outer layer protection design, so that when the recorder is applied to the high overload aircraft, the outer shell can be allowed to be damaged and broken to absorb part of energy under the condition of multiple impacts, the middle shell is allowed to deform, the basic appearance of the recorder is ensured, and the inner core in the middle shell is ensured not to deform. In addition, due to the factors such as buffer pads, glue solution and the like in each protection shell layer, overload energy can be effectively absorbed, peak values of shock impact can be weakened, impact on the circuit core board 11 is greatly reduced, and the purpose that the recorder has stronger protection performance under the condition of high overload is achieved.

In one embodiment, further, as shown in FIG. 2, the inner housing 12 is an aluminum alloy housing. It can be understood that in this embodiment, the inner housing 12 processed by aluminum alloy is used as the potting body of the circuit core 11, so as to ensure the basic shape of the recorder core, and meet the basic requirement of having a certain strength, so that the recorder can obtain a good inner layer protection strength with a lighter weight of the inner core.

In one embodiment, further, the middle housing 13 is a high strength alloy steel housing, and the middle cover 14 is a high strength alloy steel cover. It will be appreciated that in this embodiment, the middle shell 13 and the middle cover 14 are made of high strength alloy steel, so that high mechanical rigidity and protection strength can be obtained at low cost, and thus the inner core can be effectively prevented from being deformed by impact by the middle shell 13, and structural integrity can be ensured by matching with the middle cover 14.

In one embodiment, further, the silicone rubber is GD401 silicone rubber. It can be appreciated that in the present embodiment, the GD401 silicone rubber is poured between the middle shell and the inner shell, so that the best cushioning performance can be provided, and meanwhile, adverse effects caused by differences in thermal expansion coefficients between different materials can be eliminated, so that the reliability of the product structure can be increased.

In one embodiment, further, outer housing 15 is an aluminum alloy housing and outer housing 16 is an aluminum alloy housing. It will be appreciated that in this embodiment, the outer shell 15 and the outer shell 16 are machined from a relatively thick, high strength aluminum alloy, so that a better energy absorbing protection is achieved at a lower cost.

In one embodiment, further, the data pre-reading port is a threaded hole and the plug 152 is a screw plug. It will be appreciated that in this embodiment, the mechanical connection between the data pre-reading port and the blocking member 152 is implemented by using a threaded connection, so that a highly reliable pre-reading port blocking effect can be implemented by using a simple mechanical structure. When the high overload aircraft recorder 100 is carried on an aircraft to prepare for collection of test data, the high overload aircraft recorder is only screwed into the threaded hole by a screw plug to seal the threaded hole, so that the threaded hole is prevented from being deformed and damaged, polluted or disturbed in the test process. When the data in the high overload aircraft recorder 100 need to be read after the test is finished, the data can be read only by unscrewing the plug, taking out the data wire and connecting the data reading equipment, and the operation is simple and convenient and the reliability is high.

In one embodiment, further, the first cushion 131 is an air rubber cushion having a perforated structure. It can be appreciated that in this embodiment, the first cushion pad 131 may be manufactured by using a rubber plate or an aviation rubber plate, and the rubber plate is perforated to form a required aviation rubber pad, so that an energy absorption area increase caused by the hole structure can be utilized to further enhance the middle layer buffering effect.

In one embodiment, further, the second cushion 151 is an air rubber cushion of perforated construction. It can be appreciated that in this embodiment, the second cushion pad 151 may also be processed by using a rubber plate or an aviation rubber plate, and the rubber plate is perforated to form a required aviation rubber pad, so that the energy absorption area increase caused by the hole structure can be utilized to further improve the outer layer buffering effect.

In one embodiment, further, each of the lead holes 101 is plugged by poured GD704 silicone rubber. It will be appreciated that, for each layer of the housing, the lead holes 101 may be formed in a position matching manner, or may be formed in a position mismatch manner (in this case, the wiring length of the data line is increased because the positions of the lead holes 101 on different shells are not in a uniform orientation). In this embodiment, the lead holes 101 on each layer of the shell are preferably formed in a position matching manner, that is, the lead holes 101 with identical hole axes are formed at the same position on each layer of the shell, and the lead holes 101 on each shell layer are filled with GD704 silicone rubber for plugging after the data wires are led out, so that the cost of the data wires can be saved to the greatest extent, and meanwhile, the safety protection effect on the circuit core board 11 is further improved.

In one embodiment, further, the inner housing 12 is a cylindrical or spherical structure. It will be appreciated that in this embodiment, the inner shell 12 with a cylindrical or spherical structure is preferably used to encapsulate the circuit core 11, and due to the limitation of the shape and structure of the carrier aircraft, the inner shell 12 with a cylindrical or spherical structure can perform inner protection on the circuit core 11 with higher structural strength, and meanwhile, the shape selection and encapsulation operations of the middle shell 13 and the outer shell 15 are more convenient, so that the applicability to different carrier aircrafts is also enhanced.

The technical features of the above embodiments may be arbitrarily combined, and all possible combinations of the technical features in the above embodiments are not described for brevity of description, however, as long as there is no contradiction between the combinations of the technical features, they should be considered as the scope of the description.

The foregoing examples represent only a few embodiments of the present application, which are described in more detail and are not to be construed as limiting the scope of the invention. It should be noted that it would be apparent to those skilled in the art that various modifications and improvements could be made without departing from the spirit of the present application, which would be within the scope of the present application. Accordingly, the scope of protection of the present application is to be determined by the claims appended hereto.

Claims

1. The high overload aircraft recorder is characterized by comprising a circuit core board, an inner shell, a middle cover, an outer shell and an outer cover, wherein the circuit core board is used for collecting and backing up the data of an aircraft;

the circuit core board is connected with the inner shell through screws and is fixed in the inner shell through column pads, the inner shell is used for encapsulating the circuit core board through electric pouring sealant, an inner core body which is integrally and fixedly connected with the circuit core board is formed, and the inner shell is an aluminum alloy shell;

the middle shell is used for accommodating the inner core body, first buffer pads are arranged on two sides of the middle shell in the vertical direction of the inner core body, silicon rubber is poured on the periphery of the inner core body, a middle cover opening is formed in one side of the middle shell in the vertical direction of the inner core body, a polytetrafluoroethylene pad is arranged on the first buffer pad on one side of the middle cover opening, the middle cover opening is sealed by the polytetrafluoroethylene pad, the middle cover body is mechanically connected with the middle shell to form a middle core body, the middle shell is a high-strength alloy steel shell, the middle cover body is a high-strength alloy steel cover body, and the first buffer pad is an aviation rubber pad with a punching structure;

the outer shell is used for accommodating the middle core body, second buffer pads are respectively arranged on two sides of the middle core body in the vertical direction, epoxy pouring sealant is poured on the periphery of the middle core body, an outer cover opening is formed in one side of the outer shell in the vertical direction of the middle core body, the outer cover body is used for sealing the outer cover opening and is fixedly connected with the outer shell body, a data pre-reading opening and a plugging piece are arranged on the outer cover body, and the plugging piece is used for plugging the data pre-reading opening; the second cushion pad is larger than the first cushion pad in size and thickness, the outer shell is an aluminum alloy shell, the outer shell is an aluminum alloy cover, and the second cushion pad is an aviation rubber cushion plate with a punching structure;

the inner shell, the middle shell and the outer shell are respectively provided with a lead hole, the lead holes are used for penetrating the data wires of the circuit core board, the data wires comprise a pre-reading wire and a backup transmission wire, the connector of the pre-reading wire is arranged at the data pre-reading port, and the backup transmission wire is used for connecting the data acquisition source of the aircraft.

2. The high overload aircraft recorder of claim 1, wherein the silicone rubber is GD401 silicone rubber.

3. The high overload aircraft recorder of claim 1, wherein the data pre-reading port is a threaded hole and the plug is a plug.

4. The high overload aircraft recorder of claim 1, wherein each of the lead holes is plugged with poured GD704 silicone rubber.

5. The high overload aircraft recorder of claim 1, wherein the inner housing is a cylindrical or spherical structure.