CN109969418B - Aircraft and electrical system and circuit board frame thereof - Google Patents
Aircraft and electrical system and circuit board frame thereof Download PDFInfo
- Publication number
- CN109969418B CN109969418B CN201711445323.1A CN201711445323A CN109969418B CN 109969418 B CN109969418 B CN 109969418B CN 201711445323 A CN201711445323 A CN 201711445323A CN 109969418 B CN109969418 B CN 109969418B
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- Prior art keywords
- frame
- circuit board
- aircraft
- bases
- main body
- Prior art date
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- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 9
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 9
- 238000004891 communication Methods 0.000 claims description 10
- 230000008878 coupling Effects 0.000 claims description 7
- 238000010168 coupling process Methods 0.000 claims description 7
- 238000005859 coupling reaction Methods 0.000 claims description 7
- 239000004411 aluminium Substances 0.000 claims description 3
- 238000005259 measurement Methods 0.000 claims 1
- 238000004519 manufacturing process Methods 0.000 abstract description 9
- 230000017525 heat dissipation Effects 0.000 abstract description 8
- 230000008054 signal transmission Effects 0.000 abstract description 4
- 238000012423 maintenance Methods 0.000 abstract description 3
- 238000011144 upstream manufacturing Methods 0.000 abstract 1
- 230000005540 biological transmission Effects 0.000 description 7
- 238000012545 processing Methods 0.000 description 6
- 230000010354 integration Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000002788 crimping Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 238000005253 cladding Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000012797 qualification Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/14—Mounting supporting structure in casing or on frame or rack
- H05K7/1401—Mounting supporting structure in casing or on frame or rack comprising clamping or extracting means
- H05K7/1411—Mounting supporting structure in casing or on frame or rack comprising clamping or extracting means for securing or extracting box-type drawers
- H05K7/1412—Mounting supporting structure in casing or on frame or rack comprising clamping or extracting means for securing or extracting box-type drawers hold down mechanisms, e.g. avionic racks
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Mounting Of Printed Circuit Boards And The Like (AREA)
- Combinations Of Printed Boards (AREA)
Abstract
The invention relates to an aircraft, an electrical system thereof and a circuit board frame, wherein the circuit board frame comprises an aluminum frame base, frame supporting rods and a mother board, and the supporting rods are fixed between the two frame bases; all the modularized circuit components are sequentially arranged and fixed on the supporting rod and are reliably and electrically connected with a motherboard, and two ends of the motherboard are connected with an upstream circuit and a downstream circuit through cables. The invention has stable structure and high modularization degree, improves the manufacturability of the equipment product, lightens the weight of the equipment product, reduces the production and manufacturing cost, is easy to overhaul, lightens the operation and maintenance burden, and solves the problem that high-speed signal transmission cannot be accurately controlled; and a gap is left between the plates, so that a heat dissipation air path is convenient to plan, and the heat dissipation problem can be effectively solved.
Description
Technical Field
The invention relates to an aircraft, an electrical system of the aircraft and a circuit board frame, and belongs to the field of electricity.
Background
An aircraft is composed of cylindrical main body, power supply module, telemetering module, etc, and power module at front end and back end.
The aircraft electrical components are structurally independent, a main cable form is generally adopted, and the electrical components are organically connected together to form a whole by one or more connecting cables, so that the functional components can complete the exchange and transmission of electrical signals according to corresponding working time sequences and control logics. The weight and the volume of the main cable are large; the processing and manufacturing of the main cable need a large amount of manual operation, including procedures of welding, crimping, encapsulating, cladding and the like, the processing work time is long, the efficiency is low, and meanwhile, problems easily occur in links of welding, crimping, encapsulating and the like; the main cable is adopted, so that the transmission of high-speed signals is not facilitated, the transmission quality of the high-speed signals is sensitive to the length of a transmission line, and the length of each high-speed signal transmission line cannot be accurately controlled, so that the characteristics of each main cable in the transmission of the high-speed signals are different, and the quality of products is difficult to effectively control.
In addition, if a large amount of space is reserved for other parts such as machinery and the like, the volume of the electric part needs to be compressed as much as possible, the electronic circuit with higher power consumption has great heat productivity, and the arrangement with a compact structure has high heat dissipation requirements; how to solve the problems of realizing compact layout of an electric part and simultaneously meeting the heat dissipation requirement is a problem to be solved urgently.
Disclosure of Invention
The invention aims to provide an aircraft, an electrical system of the aircraft and a circuit board frame of the aircraft, which are used for solving the problems that the aircraft adopts cables to connect various electrical components, so that the processing technology is complex, the processing time is long, and the high-speed signal transmission cannot be accurately controlled.
In order to achieve the above object, the scheme of the invention comprises:
the invention relates to a circuit board frame, which comprises the following frame scheme:
the first frame scheme comprises a mother board for realizing communication connection of a circuit board, two frame bases arranged at intervals along the front and the rear and an intermediate support frame arranged between the two frame bases in a supporting mode, wherein the intermediate support frame comprises the mother board, and a cable interface for connecting cables and a circuit board interface for inserting the circuit board, which are sequentially arranged along the front and the rear directions, are arranged on the mother board.
And on the basis of the first frame scheme, the middle support frame is provided with a positioning structure for positioning each circuit board along the front-back direction.
And on the basis of the frame scheme II, the positioning structure comprises a fastening connection structure for fastening and assembling the corresponding circuit board on the middle support frame.
And on the basis of the frame scheme III, the middle support frame comprises support rods with two ends correspondingly fixed on the two frame bases, and the fastening connection structure is arranged on the support rods.
And a fifth frame scheme, wherein on the basis of the first frame scheme, the frame base comprises a mounting structure for fixed mounting.
And on the basis of the first frame scheme, a lightening hole is formed in the frame base.
And a seventh frame scheme, wherein on the basis of any one of the first frame scheme to the sixth frame scheme, two ends of the motherboard are correspondingly connected to corresponding edge positions of two frame bases.
And a seventh frame scheme, wherein the circuit board interface is a wire spring contact coupling electric connector.
And on the basis of the frame scheme eight, the frame base and the support rods are made of aluminum.
The invention relates to an aircraft electrical system, comprising a system solution:
the first system scheme comprises a circuit board, and comprises a mother board for realizing communication connection of the circuit board, two frame bases arranged at intervals along the front and the rear, and an intermediate support frame arranged between the two frame bases in a supporting manner, wherein the intermediate support frame comprises the mother board, a cable interface for connecting a cable and circuit board interfaces for inserting the circuit board, which are sequentially arranged along the front and the rear directions, are arranged on the mother board, and the circuit board is inserted into the corresponding circuit board interfaces.
And in the second system scheme, on the basis of the first system scheme, a positioning structure for positioning each circuit board along the front-back direction is arranged on the middle support frame.
And on the basis of the second system scheme, the positioning structure comprises a fastening connection structure for fastening and assembling the corresponding circuit board on the middle support frame.
And on the basis of the third system scheme, the middle support frame comprises support rods with two ends correspondingly fixed on the two frame bases, and the fastening connection structure is arranged on the support rods.
In a fifth aspect of the present invention, based on the first aspect of the present invention, the frame base includes a mounting structure for fixed mounting.
And in a sixth system scheme, on the basis of the first system scheme, the frame base is provided with lightening holes.
And in a seventh system scheme, on the basis of any one of the first system scheme to the sixth system scheme, two ends of the motherboard are correspondingly connected to corresponding edge positions of the two frame bases.
And a eighth system scheme, wherein on the basis of the seventh system scheme, the circuit board interface is a wire spring contact coupling electric connector.
And on the basis of the eighth system scheme, the frame base and the support rods are aluminum frame bases and support rods.
The invention relates to an aircraft, which comprises the following aircraft schemes:
aircraft scheme one, including electric portion, electric portion is including the mother board that is used for realizing circuit board communication connection, two frame bases along front and back interval arrangement and support the intermediate strut who sets up between two frame bases, intermediate strut includes the mother board, be provided with the cable interface that is used for connecting the cable on the mother board and follow the circuit board interface that is used for cartridge circuit board that the fore-and-aft direction arranged in proper order.
And on the basis of the first aircraft scheme, a positioning structure for positioning each circuit board in the front-back direction is arranged on the middle support frame.
Aircraft scheme three, on aircraft scheme two's basis, location structure includes the fastening connection structure of fastening the assembly on the intermediate strut with corresponding circuit board.
Aircraft scheme four, on aircraft scheme three's basis, middle support frame includes that both ends correspond the vaulting pole of fixing on two frame bases, the fastening connection structure dress is in on the vaulting pole.
And the frame base comprises a mounting structure for fixed mounting on the basis of the first aircraft scheme.
And on the basis of the first aircraft scheme, the frame base is provided with lightening holes.
And in the seventh aircraft scheme, on the basis of any one of the first aircraft scheme to the sixth aircraft scheme, two ends of the motherboard are correspondingly connected to the corresponding edge positions of the two frame bases.
And in the eighth aircraft scheme, on the basis of the seventh aircraft scheme, the circuit board interface is a wire spring contact coupling electric connector.
Aircraft scheme nine, on aircraft scheme eight's basis, frame base and vaulting pole are aluminium frame base and vaulting pole.
The invention has the beneficial effects that:
the invention can realize the communication of the circuit board through the motherboard on the basis of the modularization of the electric part, and the components do not need to communicate through cables, thereby adopting more efficient and reliable motherboard communication. The invention has stable structure and high modularization degree, improves the manufacturability of the aircraft, lightens the weight of the aircraft, reduces the production and manufacturing cost, is easy to overhaul and replace modules, lightens the operation and maintenance burden and solves the problem that high-speed signal transmission cannot be accurately controlled; and a gap is left between the plates, so that a heat dissipation air path is convenient to plan, and the heat dissipation problem can be effectively solved.
Drawings
Fig. 1 is a schematic view of an aircraft circuit board frame of the present invention.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
Fig. 1 is a schematic diagram of a circuit board frame of an aircraft, including a frame base 1, a support rod 8, and a motherboard 6; the frame base 1 is circular, two supporting rod 8 fixing positions are arranged at opposite positions of the edge, a plurality of protruding portions used for fixing the frame on the barrel-shaped body of the aircraft are evenly distributed at the edge, and bolt fixing round holes are formed in the protruding portions. The two support rods 8 are respectively fixed on two opposite support rods 8 at the edge of the frame base 1, and the other ends of the support rods 8 are fixed on the other frame base 1. On the frame base 1, be provided with the mother board fixed position in the middle of the circular arc between two bracing piece fixed positions, mother board 6 is fixed in on the corresponding position between two frame bases 1 through the mother board fixed position. The motherboard 6 is provided with a circuit board interface which adopts a wire spring contact coupling electric connector. And a circuit board fixing position is arranged on the support rod 8 at a position corresponding to the circuit board interface of the motherboard 6. The frame base 1 and the support rod 8 are made of aluminum.
As shown in fig. 1, the circuit board 2, the circuit board 3, the circuit board 4, and the circuit board 5 are arranged on a plane perpendicular to the support bar 8, with the center of the circuit board coinciding with the center of the frame base 1. The two frame bases 1 and the two support rods 8 form a frame for supporting a circuit board, and the circuit board and the motherboard 6 are reliably connected with the frame through a bracket and a fastening screw. The circuit board is securely connected to the motherboard 6 both structurally and electrically by means of wire spring contact coupling electrical connectors. The electrical connection between the circuit boards is accomplished through the motherboard. The motherboard is connected to the front and back end circuits by cables 10. The circuit board 2, the circuit board 3, the circuit board 4 and the circuit board 5 are respectively modularized printed circuit boards with different functions of the electrical part of the aircraft. The shape of each circuit board should preferably be the same as the shape of the frame base 1.
The circuit boards of all electrical components in the aircraft are intensively and compactly arranged together through electrical integration, electrical signal connection between the circuit boards is realized through a motherboard, the bus communication mode is similar to that of a bus communication mode, and all signals are collected and shunted through the motherboard. Each circuit board is fixedly arranged through a light aluminum frame, and radiating air flow is arranged around the circuit boards along the direction vertical to the support rod 8, so that heat dissipation is easy. The frame is fixedly connected with the inner surface of the aircraft shell or other structural parts through the fixing protruding parts, the frame is used for fixing a circuit board, a printed board, an electric connector, corresponding cables and the like, and the circuit board is connected with the motherboard through a high-reliability wire spring contact coupling electric connector.
After the electrical part of the aircraft adopts a modularized compact arrangement based on a motherboard, the manufacturability of the aircraft is improved, the weight of the aircraft is reduced, the production and manufacturing cost is reduced, the circuit board is easy to overhaul and replace, the operation and maintenance burden is reduced, the high-speed transmission of digital signals is facilitated, and the heat dissipation is efficient and quick.
By adopting the printed board process, the electric integration is realized, the peripheral electric connection is greatly simplified, and the batch processing production of the printed boards can be realized. Meanwhile, the space resources are saved due to the internal electrical integration of the aircraft, larger space can be reserved for machinery, fuel or other parts, and the space utilization rate is improved.
The mother board adopts a multi-layer printed circuit board with mature technology, the processing and the manufacture of the mother board are finished by a machine, the technological stability of the product is ensured, the influence of human factors is reduced, the cost is reduced, the period is shortened, the yield is improved, and meanwhile, the mother board is beneficial to the high-speed transmission of digital signals, so that the test qualification rate of the product is improved.
Claims (18)
1. A circuit board frame is used for an aircraft, the main body of the aircraft is in a barrel shape, the electrical connection of the aircraft is located in the middle of the barrel-shaped main body, the components at the front end of the main body comprise a power supply component and a remote measuring component, and the components at the rear end of the main body are power components; the circuit board connector is characterized by comprising a mother board for realizing communication connection of a circuit board, two frame bases arranged at intervals along the front and the rear and an intermediate support frame arranged between the two frame bases in a supporting manner, wherein the intermediate support frame comprises the mother board and support rods of which two ends are correspondingly fixed on the two frame bases; the middle support frame is provided with a positioning structure for positioning each circuit board along the front-back direction, and the positioning structure comprises a fastening connection structure for fastening and assembling the corresponding circuit board on the middle support frame; wherein, the fastening connection structure is arranged on the stay bar; the two frame bases and the two support rods form a frame for supporting the circuit board.
2. A circuit board frame according to claim 1, wherein the frame base comprises mounting structures for fixed mounting.
3. The circuit board frame as claimed in claim 1, wherein the frame base has lightening holes.
4. A circuit board frame according to any one of claims 1 to 3, wherein the two ends of the motherboard are attached at respective edge positions of the two frame bases.
5. The circuit board frame according to claim 4, wherein the circuit board interface is a wire spring contact coupling electrical connector.
6. A circuit board frame according to claim 5, characterised in that the frame base and the braces are aluminium frame bases and braces.
7. An aircraft electrical system comprises a circuit board and is characterized by comprising a mother board for realizing communication connection of the circuit board, two frame bases arranged at intervals along the front and the rear and a middle support frame arranged between the two frame bases in a supporting mode, wherein the main body of the aircraft is in a barrel shape, the electrical connection of the aircraft is positioned in the middle of the barrel-shaped main body, the assembly at the front end of the main body comprises a power supply assembly and a remote measurement assembly, and the assembly at the rear end of the main body is a power assembly; the middle support frame comprises a mother board and support rods, two ends of each support rod are correspondingly fixed on two frame bases, cable interfaces for connecting cables and circuit board interfaces which are sequentially arranged along the front-back direction and used for inserting circuit boards are arranged on the mother board, and the circuit boards are inserted into the corresponding circuit board interfaces; the middle support frame is provided with a positioning structure for positioning each circuit board along the front-back direction, and the positioning structure comprises a fastening connection structure for fastening and assembling the corresponding circuit board on the middle support frame; wherein, the fastening connection structure is arranged on the stay bar; the two frame bases and the two support rods form a frame for supporting the circuit board.
8. An aircraft electrical system according to claim 7 wherein the frame base comprises mounting structure for fixed mounting.
9. An aircraft electrical system according to claim 7 wherein the frame base is provided with lightening holes.
10. An aircraft electrical system according to any one of claims 7 to 9 wherein the two ends of the motherboard are connected at respective edge locations of the two frame mounts.
11. An aircraft electrical system according to claim 10 wherein the circuit board interface is a wire spring contact coupled electrical connector.
12. An aircraft electrical system according to claim 11 wherein the frame bases and struts are aluminium frame bases and struts.
13. An aircraft comprises an electric part and is characterized in that the main body of the aircraft is in a barrel shape, the electric connection of the aircraft is positioned in the middle of the barrel-shaped main body, the components at the front end of the main body comprise a power supply component and a remote measuring component, and the components at the rear end of the main body are power components; the electrical part comprises a mother board for realizing communication connection of circuit boards, two frame bases arranged at intervals along the front and the rear and an intermediate support frame arranged between the two frame bases in a supporting manner, the intermediate support frame comprises the mother board and support rods with two ends correspondingly fixed on the two frame bases, and the mother board is provided with a cable interface for connecting cables and circuit board interfaces which are sequentially arranged along the front and the rear directions and are used for inserting the circuit boards; the middle support frame is provided with a positioning structure for positioning each circuit board along the front-back direction, and the positioning structure comprises a fastening connection structure for fastening and assembling the corresponding circuit board on the middle support frame; wherein, the fastening connection structure is arranged on the stay bar; the two frame bases and the two support rods form a frame for supporting the circuit board.
14. The aircraft of claim 13, wherein the frame base comprises mounting structures for fixed mounting.
15. The aircraft of claim 13 wherein said frame base is formed with lightening holes.
16. An aircraft according to any one of claims 13 to 15, wherein the two ends of the mother board are connected at respective edge positions of the two frame bases.
17. The aircraft of claim 16, wherein the circuit board interface is a wire spring contact coupled electrical connector.
18. The aircraft of claim 17 wherein said frame bases and struts are aluminum frame bases and struts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711445323.1A CN109969418B (en) | 2017-12-27 | 2017-12-27 | Aircraft and electrical system and circuit board frame thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711445323.1A CN109969418B (en) | 2017-12-27 | 2017-12-27 | Aircraft and electrical system and circuit board frame thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109969418A CN109969418A (en) | 2019-07-05 |
| CN109969418B true CN109969418B (en) | 2023-01-31 |
Family
ID=67071605
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711445323.1A Active CN109969418B (en) | 2017-12-27 | 2017-12-27 | Aircraft and electrical system and circuit board frame thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109969418B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113247210A (en) * | 2021-05-08 | 2021-08-13 | 北京凌天智能装备集团股份有限公司 | ROV control cabin and fixing device thereof |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020012235A1 (en) * | 1999-08-18 | 2002-01-31 | Kupnicki Richard A. | Circuit board interface |
| US6747866B1 (en) * | 2002-07-18 | 2004-06-08 | Rockwell Collins | Electronic module restraint apparatus |
| US7215557B2 (en) * | 2003-08-27 | 2007-05-08 | Visteon Global Technologies, Inc. | Assembly comprising multiple microelectronic modules |
| FR2953361B1 (en) * | 2009-12-01 | 2012-08-03 | Airbus Operations Sas | CABINET FOR AVIONIC EQUIPMENT |
| DE102014011036A1 (en) * | 2014-07-23 | 2016-01-28 | Diehl Bgt Defence Gmbh & Co. Kg | Sensor head for a missile |
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2017
- 2017-12-27 CN CN201711445323.1A patent/CN109969418B/en active Active
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| Publication number | Publication date |
|---|---|
| CN109969418A (en) | 2019-07-05 |
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