CN216057706U

CN216057706U - Unmanned helicopter triple redundancy design flight control computer structure

Info

Publication number: CN216057706U
Application number: CN202120860780.2U
Authority: CN
Inventors: 雷新光
Original assignee: Shenyang Zhuoyi Aviation Technology Co ltd
Current assignee: Shenyang Zhuoyi Aviation Technology Co ltd
Priority date: 2021-04-25
Filing date: 2021-04-25
Publication date: 2022-03-15
Anticipated expiration: 2031-04-25

Abstract

The utility model discloses a triple-redundancy-design flight control computer structure of an unmanned helicopter, and relates to the technical field of unmanned helicopters. Including back casing and top casing, top casing inlays admittedly in back casing top, the left lower extreme of top casing inlays inherent connector panel, it has the aviation plug to inlay on the connector panel outer wall, connector panel bottom is inlayed admittedly in the upper left end of bottom casing, top casing lower extreme inlays inherent preceding seal shell, it has main control panel to peg graft at top casing lower extreme, main control panel includes guide rail, the control unit and a screw. This unmanned helicopter triple redundancy designs flight control computer structure, the design of pegging graft through with the slot-in type structure solves unmanned aerial vehicle flight controller main control unit and realizes redundantly, and this structure makes three sets of modules of flight controller main control unit completely independent, parallel, has made things convenient for the staff to the installation maintenance of flight controller, improves staff's installation maintenance efficiency.

Description

Unmanned helicopter triple redundancy design flight control computer structure

Technical Field

The utility model relates to the technical field of unmanned helicopters, in particular to a flight control computer structure with triple redundancy design for an unmanned helicopter.

Background

An unmanned aircraft, abbreviated as "drone", and abbreviated in english as "UAV", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer. Drones tend to be more suitable for tasks that are too "fool, dirty, or dangerous" than are manned aircraft. Unmanned aerial vehicles can be classified into military and civil applications according to the application field. For military use, unmanned aerial vehicles divide into reconnaissance aircraft and target drone. In the civil aspect, the unmanned aerial vehicle + the industry application is really just needed by the unmanned aerial vehicle; at present, the unmanned aerial vehicle is applied to the fields of aerial photography, agriculture, plant protection, miniature self-timer, express transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, film and television shooting, romantic manufacturing and the like, the application of the unmanned aerial vehicle is greatly expanded, and developed countries actively expand industrial application and develop unmanned aerial vehicle technology.

In the prior art, the flight control computer of the existing unmanned helicopter is fixedly installed on the unmanned helicopter, so that the flight control computer is inconvenient to overhaul by workers, and the integration causes inconvenience in installation and influences the use and maintenance efficiency of the workers.

SUMMERY OF THE UTILITY MODEL

Technical problem to be solved

Aiming at the defects of the prior art, the utility model provides a flight control computer structure with a triple redundancy design for an unmanned helicopter, which solves the problems in the background technology.

(II) technical scheme

In order to achieve the purpose, the utility model is realized by the following technical scheme: the utility model provides a three redundant design flight control computer structures of unmanned helicopter, includes back casing and top casing, top casing inlays admittedly in back casing top, the left lower extreme of top casing inlays inherent connector panel, it has aviation plug to inlay on the connector panel outer wall, connector panel bottom is inlayed admittedly in the upper left end of end casing, top casing lower extreme inlays inherent preceding seal housing, it has main control panel to peg graft at top casing lower extreme, main control panel includes guide rail, the control unit and a screw, the control unit slides with the guide rail relatively.

Preferably, the control unit comprises a panel, a PCB main control panel and a second screw, and the panel is in threaded connection with the front end of the PCB main control panel through the second screw.

Preferably, a power panel is inserted into the upper end of the bottom shell, and the power panel and the front sealing shell slide relatively.

Preferably, a PCB bottom plate is embedded in the inner wall of the rear shell, a guide rail supporting piece is embedded between the rear shell and the front sealing shell, and the guide rail is embedded in the guide rail supporting piece.

Preferably, the PCB main control panel is movably connected with the bottom plate connector, the PCB main control panel is movably connected with the main control panel connector, and the bottom plate connector and the main control panel connector are fixedly embedded on the inner wall of the rear shell.

Preferably, the right shell is fixedly embedded at the right end of the rear shell, and the inner wall of the right shell slides relative to the main control panel and the power panel.

(III) advantageous effects

The utility model provides a flight control computer structure with a triple redundancy design for an unmanned helicopter. The method has the following beneficial effects:

(1) this unmanned helicopter triple redundancy designs flight control computer structure, through the grafting design with the slot-in type structure solve unmanned aerial vehicle flight controller main control unit and realize redundantly, this structure makes three sets of modules of flight controller main control unit completely independent, parallel, has made things convenient for the staff to the installation maintenance of flight controller, improves staff's installation maintenance efficiency.

(2) This unmanned helicopter triple redundancy designs flight control computer structure through making flight controller main control unit set up to three, installs one set of host system module and does not have redundancy, installs two sets of host system module and realizes dual redundancy, installs three sets of host system modules and realizes triple redundancy, and nimble combination is replaced wantonly, has improved the efficiency of work change maintenance.

Drawings

FIG. 1 is a schematic view of the overall front view structure of the present invention;

FIG. 2 is a schematic view of the overall internal structure of the present invention;

FIG. 3 is a schematic diagram of an exploded view of the control unit of the present invention;

FIG. 4 is a schematic diagram of an exploded view of a control unit according to the present invention;

FIG. 5 is a schematic view of the rear housing of the present invention;

FIG. 6 is a schematic view of the top housing construction of the present invention;

FIG. 7 is a schematic view of the bottom housing of the present invention;

FIG. 8 is a schematic view of the right housing of the present invention;

FIG. 9 is a schematic view of the track support structure of the present invention;

FIG. 10 is a schematic view of a connector panel according to the present invention;

FIG. 11 is a schematic view of a front seal housing of the present invention;

FIG. 12 is a front view of the main control panel of the present invention;

fig. 13 is a schematic view of a power panel structure according to the present invention.

In the figure: 1. a rear housing; 2. a top housing; 3. a connector panel; 4. an aviation plug; 5. a bottom housing; 6. a main control panel; 61. a guide rail; 62. a control unit; 63. a first screw; 621. a panel; 11. a PCB main control panel; 623. a second screw; 7. a power panel; 8. a front seal housing; 9. a PCB backplane; 10. a rail support; 12. a backplane connector; 13. a main control board connector; 14. and a right housing.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

Referring to fig. 1-13, the present invention provides a technical solution: a flight control computer structure with triple redundant design for an unmanned helicopter comprises a rear shell 1 and a top shell 2, wherein the top shell 2 is fixedly embedded at the top end of the rear shell 1, a connector panel 3 is fixedly embedded at the left lower end of the top shell 2, an aviation plug 4 is fixedly embedded on the outer wall of the connector panel 3, the bottom end of the connector panel 3 is fixedly embedded at the left upper end of a bottom shell 5, a front sealing shell 8 is fixedly embedded at the lower end of the top shell 2, a main control panel 6 is inserted at the lower end of the top shell 2, the main control panel 6 comprises a guide rail 61, a control unit 62 and a first screw 63, the control unit 62 and the guide rail 61 slide relatively, the redundancy of the main control unit of the unmanned aerial vehicle flight controller is realized by the plug-in design of a slot-in type structure, the structure enables three sets of modules of the main control unit of the flight controller to be completely independent and parallel, facilitates installation and maintenance of the flight controller by workers, and improves the installation and maintenance efficiency of the workers.

In this embodiment, the number of the main control panels 6 is three, three main control panels 6 all slide relative to the guide rail support member 10 through the guide rail 61, the control unit 62 includes a panel 621, a PCB main control panel 11 and a second screw 623, the panel 621 is connected with the front end of the PCB main control panel 11 through the second screw 623, the PCB main control panel 11 is movably connected with the bottom plate connector 12, the PCB main control panel 11 is movably connected with the main control panel connector 13, the bottom plate connector 12 and the main control panel connector 13 are both embedded and fixed on the inner wall of the rear housing 1, the main control unit of the flight controller is set to be three sets, one set of main control module is installed without redundancy, two sets of main control modules are installed to realize double redundancy, three sets of main control modules are installed to realize triple redundancy, flexible combination and random replacement are performed, and the efficiency of work replacement and maintenance is improved.

In this embodiment, a power panel 7 is inserted into the upper end of the bottom housing 5, the power panel 7 slides relative to the front sealing housing 8, a PCB bottom plate 9 is embedded in the inner wall of the rear housing 1, a guide rail supporting member 10 is embedded between the rear housing 1 and the front sealing housing 8, a guide rail 61 is embedded in the guide rail supporting member 10, a right housing 14 is embedded in the right end of the rear housing 1, and the inner wall of the right housing 14 slides relative to the main control panel 6 and the power panel 7.

During operation (or during the use), when needs carry out plug-in components installation to main control panel 6, only need insert main control panel 6 along guide rail 61, until PCB main control panel 11 inserts behind bottom plate connector 12 and main control panel connector 13, alright fix main control panel 6 through a screw 63, it is very convenient to make the installation, main control panel 6 of installation does not have the redundancy, after installing two main control panel 6, alright realize the two redundancies in master control, after installing three main control panel 6, alright realize the three redundancies, can carry out nimble combination as required, arbitrary replacement, work efficiency has been improved, when needs are dismantled and are overhauld, only need lift screw 63 down, take main control panel 6 out afterwards, alright reach the purpose of dismantling the maintenance, it is very convenient.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.

Claims

1. The utility model provides a three redundant designs of unmanned helicopter flight control computer structures, includes back casing (1) and top casing (2), its characterized in that: top casing (2) inlay admittedly in back casing (1) top, top casing (2) left side lower extreme inlays inherent connector panel (3), it has aviation plug (4) to inlay on connector panel (3) outer wall, connector panel (3) bottom is inlayed admittedly in end casing (5) upper left end, top casing (2) lower extreme inlays inherent preceding seal housing (8), it has main control panel (6) to peg graft top casing (2) lower extreme, main control panel (6) include guide rail (61), control unit (62) and screw (63), control unit (62) and guide rail (61) relative slip.

2. The unmanned helicopter triple redundant design flight control computer structure of claim 1, characterized in that: the control unit (62) comprises a panel (621), a PCB main control board (11) and a second screw (623), and the panel (621) is in threaded connection with the front end of the PCB main control board (11) through the second screw (623).

3. The unmanned helicopter triple redundant design flight control computer structure of claim 1, characterized in that: the upper end of the bottom shell (5) is plugged with a power panel (7), and the power panel (7) and the front sealing shell (8) slide relatively.

4. The unmanned helicopter triple redundant design flight control computer structure of claim 1, characterized in that: the PCB is characterized in that a PCB bottom plate (9) is embedded in the inner wall of the rear shell (1), a guide rail support (10) is embedded between the rear shell (1) and the front sealing shell (8), and the guide rail (61) is embedded in the guide rail support (10).

5. The unmanned helicopter triple redundant design flight control computer structure of claim 2, characterized in that: PCB master control board (11) and bottom plate connector (12) swing joint, PCB master control board (11) and master control board connector (13) swing joint, bottom plate connector (12) and master control board connector (13) all inlay and fix on back casing (1) inner wall.

6. The unmanned helicopter triple redundant design flight control computer structure of claim 1, characterized in that: the right end of the rear shell (1) is embedded with a right shell (14), and the inner wall of the right shell (14) slides relative to the main control panel (6) and the power panel (7).