CN109533388B - General evaluation platform for man-machine work efficiency of helicopter cockpit - Google Patents
General evaluation platform for man-machine work efficiency of helicopter cockpit Download PDFInfo
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- CN109533388B CN109533388B CN201811361729.6A CN201811361729A CN109533388B CN 109533388 B CN109533388 B CN 109533388B CN 201811361729 A CN201811361729 A CN 201811361729A CN 109533388 B CN109533388 B CN 109533388B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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Abstract
The invention provides a general evaluation platform for man-machine work efficiency of a helicopter cockpit, and belongs to the technical field of helicopter man-machine efficiency design. The device comprises a cockpit floor, a seat on which a helicopter cockpit is mounted, a central console, an instrument panel and a top console; the instrument panel, the central control console, the top control console and the seat are all arranged on the floor of the cockpit through supporting pieces, and the heights of the supporting pieces are adjustable; the seat is symmetrically distributed with two seats along the central axis of the cockpit, the bottom of the seat is installed on the floor of the cockpit through a transverse sliding rail, and the seat surface and the backrest are connected through a rotating mechanism. The method can be used for evaluating the visual field, accessibility and comfort of the cockpit of different helicopters, provides input for the design of the model of the helicopter according to the development requirement of the cockpit of the helicopter and the evaluation conclusion of an actual pilot, reduces iteration time and improves evaluation efficiency.
Description
Technical Field
The invention belongs to the field of helicopter man-machine efficiency design, and particularly relates to a general helicopter cockpit man-machine efficiency evaluation platform.
Background
The general evaluation of the helicopter cockpit is a very important link in the development process of the helicopter cockpit, and in order to improve the development efficiency of the cockpit and reduce the cost, a cockpit engineering prototype platform is required to be constructed in the development stage of the cockpit for verifying the man-machine work efficiency design of the helicopter, including the visibility, accessibility and operation comfort of a driver. Existing helicopter cockpit engineering simulators are often designed according to the following 1: 1, verifying the design rationality in the development stage, redesigning an unreasonable place, and then continuing to iteratively evaluate until the evaluation is satisfactory, wherein the disadvantages are that the period is too long, the evaluation result cannot provide effective input for the design, and a cockpit engineering prototype is often required to be developed for each different helicopter model, which is expensive and has too long period.
Disclosure of Invention
The invention provides a general evaluation platform for man-machine work efficiency of a helicopter cockpit, which is used for solving and evaluating partial problems in the design of the traditional helicopter model.
The invention relates to a general evaluation platform for man-machine work efficiency of a helicopter cockpit, which comprises:
the cockpit floor is used for mounting a seat, a central console, an instrument panel and a top console of a helicopter cockpit;
the bottom support piece is used for supporting the cockpit floor and is of a height-adjustable structure;
the instrument board is arranged on the floor of the cockpit through an instrument board support frame, and the height of the instrument board support frame is adjustable;
a center console mounted on the cockpit floor by a center console support, the center console support being height adjustable;
a top console mounted on the cockpit floor by a top console support, the top console support being height adjustable;
the seat is symmetrically distributed with two seats along the central axis of the cockpit, the bottom of the seat is installed on the floor of the cockpit through a transverse sliding rail, and the seat surface and the backrest of the seat are connected through a rotating mechanism.
Preferably, the bottom support comprises a bottom platform, a support rod extending upwards from the bottom platform, the other side of the support rod is connected with a cylinder, and the other side of the cylinder is connected to the bottom of the cockpit floor.
Preferably, the number of the supporting rods is at least 3, and the supporting rods are distributed in a triangle shape.
Preferably, the device also comprises a left steering column and a right steering column which are symmetrically arranged on the central lines of the two driver seats along the central axis of the driver cabin, the left steering column and the right steering column are mounted on the floor through transverse sliding rails, and the bottoms of the steering columns are respectively connected with the force feedback control box.
Preferably, still include left collective pitch pole and right collective pitch pole, all install in the left side of driver's seat just vice, install on the floor through horizontal slide rail, collective pitch pole bottom is connected with force feedback control box respectively.
Preferably, the escalator also comprises a left escalator and a right escalator which are connected with the ground and the floor of the cockpit.
Preferably, the left pedal and the right pedal are symmetrically arranged along the central axis of the cab and are respectively installed on the floor of the cab through a transverse sliding rail.
The general evaluation platform for the helicopter cockpit can be used for evaluating the view field, accessibility and comfort of the cockpit of different helicopters, provides input for helicopter model design according to the development requirement of the helicopter cockpit and the evaluation conclusion of an actual pilot, reduces iteration time, improves evaluation efficiency, effectively solves the problem that one cockpit platform needs to be manufactured for each helicopter model development, and reduces cost loss.
Drawings
Fig. 1 is a schematic structural diagram of a preferred embodiment of the universal evaluation platform for the man-machine efficiency of the helicopter cockpit according to the present invention.
Fig. 2 is a rear view of the platform of the embodiment of fig. 1 of the present invention.
Wherein 1-instrument panel support, 2-instrument panel mounting plate, 3-center console support, 4-left console support, 5-right console support, 6-top console support, 7-left seat, 8-right seat, 9-left steering column, 10-right steering column, 11-left collective rod, 12-right collective rod, 14-left foot peg, 13-right foot peg, 15-cockpit floor, 16-bottom support, 17-left escalator, 18-right escalator, 19-platform base, 20-top console mounting plate.
DETAILED DESCRIPTION OF EMBODIMENT (S) OF INVENTION
A general evaluation platform for man-machine ergonomics of helicopter cockpit can be used for evaluating different helicopter cockpit model designs, and comprises:
a cockpit floor: a seat for mounting a helicopter cockpit, left, middle and right consoles, an instrument panel, a top console support;
the bottom supporting piece is used for supporting the weight of all mechanisms on the helicopter floor, the bottoms of 3 bottom supporting pieces are fixedly connected with the platform base, the upper ends of 3 bottom supporting piece struts are respectively connected with the lower ends of 3 actuators, the upper ends of 3 actuators are fixedly connected with the bottom of the cockpit floor, and the horizontal inclination angle of the helicopter cockpit in different flight section states and the ground clearance height of different helicopter floors are simulated by respectively adjusting the heights of the 3 actuators;
the bottom of the mounting plate of the instrument panel is fixedly connected with the upper parts of the 3 actuators, and the mounting plate of the instrument panel is used for mounting instruments and display equipment;
the lower section of the instrument board support frame is fixedly arranged on the floor, the upper end of the instrument board support frame is connected with 3 actuators, and the upper ends of the 3 actuators are fixedly connected with the instrument board mounting plate; the pitching angle and the height of the instrument panel can be adjusted by respectively adjusting the heights of the actuators, and the ground clearance sizes and different flight attitudes of different helicopter instrument panels can be simulated;
a center console mounting box for mounting a handling device of a basic configuration of the helicopter in the same manner as the mounting structure of the bottom support. The lower end of the central control console installation box is fixedly connected with the upper ends of the 3 actuators, the lower ends of the 3 actuators are fixedly connected with the cockpit floor installation plate, and the height and the pitching angle of the central control console can be adjusted in a simulated mode by adjusting the heights of the 3 actuators respectively;
the left and right control console installation boxes are identical and are used for installing control equipment selected and installed by the helicopter. The left and right control console installation boxes are symmetrically arranged along the axis of the cockpit, the lower ends of the installation boxes are respectively and fixedly connected with the upper ends of 3 actuators, the lower ends of the 3 actuators are fixedly connected with a cockpit floor installation plate, and the ground clearance of the control console and the tilting angle in the pitching direction are adjusted by adjusting the heights of the actuators;
a top console mounting box mounted on the top console support through a rotating shaft, the top console mounting box being rotated to simulate a pitch tilt angle of the top console;
the top control platform supporting piece is fixedly arranged on the floor, the top control platform supporting piece is connected with the top control platform installation box, a customized actuator cylinder is arranged in the middle of the supporting piece, and the height of the top control platform can be adjusted through adjusting the height of the actuator cylinder.
The right side of the driver seat is provided with a front driver seat, the left side of the driver seat is provided with a secondary driver seat, the front driver seat and the secondary driver seat are symmetrically arranged along the axis of the driver cabin, the bottoms of the front driver seat and the secondary driver seat are arranged on the floor through transverse sliding rails, and the backrest can be rotationally adjusted through a rotating mechanism between the seat surface and the backrest; the position of a transverse sliding rail of the seat can be adjusted, the seat spacing of helicopters with different tonnages can be simulated, and the seat is fixed after the size is determined; because the existing real helicopter considers the reasons of crash resistance and the like, the backrest is not adjustable, so that the rotation angle of the backrest is required to be adjusted to evaluate and determine the most suitable tilting angle for sitting of the seat, and reference is provided for design.
The left and right steering levers are symmetrically arranged on the central lines of the two driver seats along the central axis of the cockpit, the installation type is the same as that of the seats, the left and right steering levers are installed on the floor through transverse sliding rails, the distances between the steering levers of helicopters with different tonnages are simulated by adjusting the positions of the transverse sliding rails of the left and right steering levers, and the bottoms of the steering levers are respectively connected with the force feedback control box, so that the real force feedback effect can be sensed without connecting rod systems.
The left and right collective pitch rods are all installed on the left side of the driver seat and installed on the floor through the transverse sliding rail, left and right direction adjustment can be carried out along the sliding rail, the distances between the collective pitch rods of the helicopters with different tonnages can be simulated, and the bottoms of the collective pitch rods are respectively connected with the force feedback control boxes, so that the real force feedback effect can be sensed without connecting rod systems.
The aerostaircase is used for simulating the ground clearance requirement of a real helicopter cockpit, and if a helicopter with larger tonnage generally enters the cockpit from the rear, 2 groups of escalators can be placed together and placed at the rear part of a cockpit platform; the simulation small-tonnage helicopter enters the cockpit from the left and right directions, two groups of escalators can be respectively moved to two sides of the cockpit evaluation platform, and the boarding mode of entering the cockpit from two sides is simulated.
The left pedal and the right pedal are symmetrically arranged on the floor along the axis of the cockpit, the pedals are respectively arranged on the floor through a transverse sliding rail, the distance between the pedals of the 2 groups is adjusted through adjusting the positions on the sliding rail, and the distance between the pedals of different helicopters can be simulated.
Referring to fig. 1-2, the invention relates to a general evaluation platform for a helicopter cockpit, wherein a bottom mounting plate 16 is placed on a flat ground and is connected with a cockpit floor 15 through 3 bottom supporting pieces 16, each bottom supporting piece 16 is connected with the lower end of a corresponding actuator, the upper end of each actuator is connected with the bottom of the cockpit floor, and the ground clearance and the tilt angle of the whole cockpit platform can be adjusted by respectively adjusting the heights of the 3 actuators.
The cockpit floor 15 is a hollow structure, and is provided with an instrument panel support frame 1, an instrument panel mounting plate 2, a center console support 3, a left console support 4, a right console support 5, a top console support 6, a left seat 7, a right seat 8, a left steering column 9, a right steering column 10, a left collective pitch rod 11, a right collective pitch rod 12, a left foot peg 14, a right foot peg 13, a bottom support 16, a left escalator 17, a right escalator 18, a platform base 19, and a top console mounting plate 20.
Instrument board support frame 1 fixed mounting is on the floor, by 3 actuators and the mounting panel 2 fixed connection of instrument board, the equal adjustable height of every actuator can realize the height, the angle of pitch regulation to the mounting panel of instrument board.
The bottom of the central control console supporting piece 3 is fixed on a cockpit floor 15 and is connected by 3 actuators, the upper ends of the 3 actuators are fixedly connected with a central control console mounting box, and each actuator can be adjusted in height, so that the height and the pitching angle of the central control console can be adjusted.
Left side operation panel support piece 4 and right side operation panel support piece 5 symmetrical arrangement, fix on the floor respectively, pass through 2 horizontal slide rail fixed connection by 3 actuator bottoms and floor mounting panel, can realize the horizontal of operation panel, height, inclination and adjust.
The top console support 6 is mounted on the cockpit floor 15, and the top console height can be adjusted by adjusting the height of the ram in the top console support 6, and the top console mounting plate 20 can adjust the pitch angle of the top console by rotating the shaft.
The left seat 7 and the right seat 8 are installed in the same way, are symmetrically installed on the floor along the axis of the cockpit, and are both transversely adjusted through a transverse sliding rail at the bottom, and the backrest of the seat is adjusted in angle through a rotating shaft between the backrest and the seat cushion;
the left driving rod 9 and the right driving rod 10 are installed in the same mode and are symmetrically arranged on the floor along the axis in the cockpit, the left driving rod 9 and the right driving rod 10 can be transversely adjusted through the transverse sliding rail at the bottom, the lower surface of the floor is connected with the force feedback mechanism control box, the force feedback effect can be real by designing according to the real force feedback size.
The left total distance rod 11 and the right total distance rod 12 are installed on the left side of the seat in the same installation mode, can be transversely adjusted through a bottom sliding rail, are connected with a force feedback mechanism control box below the floor, are designed according to the real force feedback size, and can achieve the real force feedback effect.
The left pedal 14 is the same as the right pedal 13, is symmetrically arranged on the floor along the central axis of the cockpit, can realize transverse adjustment through a transverse sliding rail at the bottom, is connected with a force feedback mechanism control box below the floor, is designed according to the real force feedback size, and can realize the real force feedback effect.
The left side staircase 17 and the right side staircase 18 are arranged at the rear end of the general evaluation platform of the cockpit, which can meet the requirement that the rear part of the cockpit enters the cockpit, and the staircase 17 and the staircase 18 can be respectively arranged at two sides of the platform of the cockpit to simulate a left side boarding mode and a right side boarding mode.
Interfaces are reserved on the periphery of a cockpit floor 15 of the universal assessment platform for the cockpit, and cockpit covers of different helicopters can be installed in a matched mode through platform adding and expanding.
The invention greatly reduces the development period of the helicopter by adopting the universal evaluation platform of the helicopter cockpit, can simulate and verify the design scheme and the overall arrangement of the helicopter cockpit in the early development period, avoids the condition that each helicopter is developed and needs to manufacture a cockpit platform, and greatly saves the development cost.
Claims (5)
1. A general assessment platform for man-machine ergonomics of a helicopter cockpit is characterized by comprising:
a cockpit floor (15) for mounting seats, a center console, a dashboard and a top console of a helicopter cockpit;
the bottom support piece (16) is used for supporting the cockpit floor (15), the bottom support piece (16) is of a height-adjustable structure, the bottom support piece (16) comprises a bottom platform and a support rod extending upwards from the bottom platform, the other side of the support rod is connected with an actuating cylinder, the other side of the actuating cylinder is connected to the bottom of the cockpit floor, and the support rods at least comprise 3 and are distributed in a delta shape;
the instrument board is arranged on a cockpit floor (15) plate through an instrument board support frame (1), and the height of the instrument board support frame (1) is adjustable;
a center console mounted on the cockpit floor (15) by a center console support (3), the center console support (3) being height adjustable;
a top console mounted on the cockpit floor (15) by a top console support (6), the top console support (6) being height adjustable;
the two seats are symmetrically distributed along the central axis of the cockpit, the bottoms of the seats are installed on the cockpit floor (15) through transverse sliding rails, and the seat surface and the backrest of each seat are connected through a rotating mechanism.
2. The helicopter cockpit ergonomic general assessment platform of claim 1, further comprising a left cockpit and a right cockpit, symmetrically arranged on the center lines of the two cockpit seats along the central axis of the cockpit, mounted on the floor by means of transverse slide rails, the bottom of the cockpit being connected to the force feedback control box, respectively.
3. The universal ergonomic evaluation platform for helicopter cockpit of claim 1 further comprising a left collective rod and a right collective rod, both mounted on the left side of the front and rear pilot seat, mounted on the floor by a transverse slide rail, the bottoms of the collective rods being connected to the force feedback control boxes, respectively.
4. The helicopter cockpit ergonomic general evaluation platform of claim 1 further comprising a left escalator (17) and a right escalator (18) connecting the ground to the cockpit floor.
5. A universal ergonomic evaluation platform for helicopter cabs according to claim 1 further comprising left (14) and right (13) side footrests symmetrically disposed about the central axis of the cockpit and mounted on the cockpit floor (15) by respective lateral slide rails.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811361729.6A CN109533388B (en) | 2018-11-15 | 2018-11-15 | General evaluation platform for man-machine work efficiency of helicopter cockpit |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811361729.6A CN109533388B (en) | 2018-11-15 | 2018-11-15 | General evaluation platform for man-machine work efficiency of helicopter cockpit |
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| Publication Number | Publication Date |
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| CN109533388A CN109533388A (en) | 2019-03-29 |
| CN109533388B true CN109533388B (en) | 2020-10-02 |
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| EP3739559B1 (en) * | 2019-05-13 | 2024-03-20 | Ratier-Figeac SAS | Cockpit controls simulation |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN1156807C (en) * | 2001-12-21 | 2004-07-07 | 北京航空航天大学 | Analog flight training equipment for manipulator of robot helicopter |
| CN102390544B (en) * | 2011-09-15 | 2013-11-13 | 北京航空航天大学 | Motion-linked cabin layout converting device for airplane simulator |
| FR2991295B1 (en) * | 2012-06-04 | 2015-02-27 | Eurocopter France | AIRCRAFT WITH GREAT VISIBILITY |
| CN102855410A (en) * | 2012-09-20 | 2013-01-02 | 上海品铭机械工程有限公司 | Method and system for evaluation of man-machine work efficiency of cabin simulation test bed |
| FR3005032B1 (en) * | 2013-04-26 | 2016-06-10 | Eurocopter France | SYMMETRICAL PILOTAGE STATION OF A GIRAVION HAVING SEATS POSSIBLE SIDE BY SIDE AND SIDE ACCESS DOORS |
| CN203910062U (en) * | 2014-02-27 | 2014-10-29 | 中国人民解放军空军第一航空学院 | Helicopter cabin base plate dynamic simulation platform |
| CN204759813U (en) * | 2015-06-15 | 2015-11-11 | 天津飞联科技有限公司 | Novel semi -closed emulation cockpit |
| CN105539854B (en) * | 2016-01-21 | 2018-08-24 | 南京航空航天大学 | A kind of aircraft cockpit drives ergonomics and assessment system platform |
| CN106126786B (en) * | 2016-06-17 | 2019-12-27 | 中国航空无线电电子研究所 | Method for quantitatively evaluating man-machine work efficiency of man-machine interface design of cockpit display |
| CN106599416A (en) * | 2016-11-30 | 2017-04-26 | 中国直升机设计研究所 | Man-machine work efficiency evaluation and optimization design method |
| CN107274747A (en) * | 2017-08-01 | 2017-10-20 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft cockpit ergonomic assessment system |
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