CN204078085U - Aircraft floor motion simulator - Google Patents
Aircraft floor motion simulator Download PDFInfo
- Publication number
- CN204078085U CN204078085U CN201420379175.3U CN201420379175U CN204078085U CN 204078085 U CN204078085 U CN 204078085U CN 201420379175 U CN201420379175 U CN 201420379175U CN 204078085 U CN204078085 U CN 204078085U
- Authority
- CN
- China
- Prior art keywords
- aircraft
- aircraft floor
- motion simulator
- rotating disk
- floor motion
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Abstract
The utility model provides a kind of aircraft floor motion simulator, comprising: base; Rotating disk, it can be rotatably set on described base; Transmission, it is supported in described rotating disk by the horizontal rotating shaft that two are arranged in parallel; Actuator, it rotates around described horizontal rotating shaft for driving described Transmission, to drive the wheel of undercarriage to move, and drives described rotating disk to deflect along with the deflection of described wheel in horizontal plane, and power interface, it to be arranged on described base and for connecting power supply.This aircraft floor motion simulator may be used in the turning zero control of the aircraft of various model, zeroing operation is carried out to aircraft turn control system, to improve aircraft floor slide safety, ensure aviator accurately control aircraft floor deflection there is vital function.
Description
Technical field
The utility model belongs to aircraft turn control technology field, more specifically, relates to a kind of aircraft floor motion simulator of aircraft turn control system being carried out to zeroing operation.
Background technology
Nose Wheel Steering system is one of Major Systems of aircraft floor manipulation, is realizing playing an important role in aircraft floor Servo Control, minimizing takeoff and landing accident.It is ensure that aircraft floor slides safe pacing factor that aviator controls angle of turn consistent with front-wheel deflection angle, and zeroing of turning is the effective measures ensureing that Servo Control angle is consistent with actual deflection angle.Turning zeroing comprises machine zero and software returns to zero, and machine zero generally can reach higher precision, is easy to operation, but software zeroing is due to precision restriction, has certain error, and after can not ensureing to return to zero, front-wheel is entirely on the center, controls there is certain influence to Nose Wheel Steering.
Utility model content
In order to solve the problem, the utility model provides a kind of aircraft floor motion simulator, and it is for determining the degree of bias of aircraft nose landing gear, to carry out zeroing operation to aircraft turn control system.
According to aircraft floor motion simulator of the present utility model, comprising:
Base;
Rotating disk, it can be rotatably set on described base;
Transmission, it is supported in described rotating disk by the horizontal rotating shaft that two are arranged in parallel;
Actuator, it rotates around described horizontal rotating shaft for driving described Transmission, to drive the wheel of undercarriage to move, and drives described rotating disk to deflect along with the deflection of described wheel in horizontal plane, and
Power interface, it to be arranged on described base and for connecting power supply.
Preferably, described Transmission is crawler belt.
Preferably, described crawler belt has the various physical parameters of true runway.
Preferably, described aircraft floor motion simulator also comprises: angle measuring mechanism, and it to be arranged on described base and deflection angle for measuring described rotating disk.
Preferably, described aircraft floor motion simulator also comprises: signaling interface, and it to be arranged on described base and for described aircraft floor motion simulator input emulation mode and the deflection angle outwards exporting described rotating disk.
Preferably, described angle measuring mechanism is sensor.
May be used in the turning zero control of the aircraft of various model according to aircraft floor motion simulator of the present utility model, zeroing operation is carried out to aircraft turn control system, to improve aircraft floor slide safety, ensure aviator accurately control aircraft floor deflection there is vital function.
The utility model, without the need to changing aircraft existing structure, only once need tested it, and be input in software by zeroing angle, effectively can improve the control accuracy of aircraft turn system after aircraft general assembly.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of the preferred embodiment according to aircraft floor motion simulator of the present utility model.
Fig. 2 shows the schematic diagram of the degree of bias of the aircraft floor motion simulator determination aircraft nose landing gear using Fig. 1.
Detailed description of the invention
Discuss the enforcement according to embodiment of the present utility model and use below in detail.But, should be appreciated that discussed specific embodiment only exemplarily illustrates and implement and use ad hoc fashion of the present utility model, and unrestricted scope of the present utility model.
As shown in Figure 1, aircraft floor motion simulator of the present utility model mainly comprises base 10, rotating disk 20, Transmission 30, actuator (not shown) and power interface 40.Rotating disk 20 can be rotatably set on base 10; Transmission 30 is preferably crawler belt, and it is supported in rotating disk 20 by two horizontal rotating shafts be arranged in parallel 50; Power interface 40 to be arranged on base 10 and for connecting power supply, to power to aircraft floor motion simulator.Actuator drive Transmission 30 rotate around horizontal rotating shaft 50, to drive the wheel of undercarriage move, and along with wheel in horizontal plane deflection drive rotating disk 20 deflect.
Preferably, aircraft floor motion simulator also comprises angle measuring mechanism, such as sensor, and it is for measuring the deflection angle of rotating disk 20.More preferably, aircraft floor motion simulator also comprises signaling interface, and it to be arranged on base 10 and for aircraft floor motion simulator input emulation mode and the deflection angle outwards exporting rotating disk 20.
In use, this aircraft floor motion simulator is placed on immediately below undercarriage wheel, and after switching on power, actuator drives Transmission 30 to operate, and moves to drive wheel.Rotating disk 20 1 aspect is used to fixed pedestal crawler belt, be on the other hand by wheel to the action transport of crawler belt on angle measuring mechanism.The deflection of wheel makes crawler belt deflect, thus drives rotating disk 20 to move in a circle in horizontal surface, conter clockwise or rotate clockwise respectively corresponding wheel left avertence or right avertence.The effect of base 10 supports topside, and obtain the deflection angle of wheel, base 10 must be fixed with ground simultaneously, and keep absolute rest.Power interface is used for powering to above device, and signaling interface is mainly to analog machine input emulation mode and the actual machine drift angle outwards exporting each undercarriage leg.Except the crawler belt indicated in Fig. 1, rotating disk, base and interface, this aircraft floor motion simulator also can comprise other support and mobile device.
Main purpose of the present utility model improves the zero setting accuracy of aircraft turn system.Main method is after aircraft general assembly, the mechanical drift angle of both sides main landing gear is first obtained by ground motion analog machine, core drives wheel to run up by crawler belt, and the deviation of each alighting gear is captured by sensor, then by calculate ensure nose-gear centering time nose-gear due degree of bias in current aircraft configuration, ensure that the actual angle of turn of aircraft is consistent with aviator's control angle, improve safety during aircraft taxi.
The core apparatus of aircraft turn zeroing is aircraft floor motion simulator, when the relative ground static of overall aircraft, can be returned to zero to aircraft turn according to test results by aircraft floor motion simulator.The similar wind tunnel test principle of principle of work of aircraft floor motion simulator, wind tunnel test is the motion of the manual control aircraft ambient atmosphere when aircraft is static, the motion of indirect analog aircraft in Real Atmosphere, and aircraft floor motion simulator is when aircraft and ground geo-stationary, drive wheel motion with mechanical device, thus simulated aircraft is at the two dimensional motion on ground.
The real work principle that wheel drives is: by aircraft jack-up, move to immediately below airplane wheel by ground motion analog machine, ensures that wheel initial motion direction is parallel with the static direction of crawler belt simultaneously.When carrying out turning zeroing, start aircraft floor motion simulator, crawler belt rotarily drives wheel and rotates, when stable, the geometry degree of bias of tested alighting gear can be drawn, respectively arranged on left and right sides main landing gear is tested, respective drift angle A, B can be obtained, as shown in Figure 2, finally show that the drift angle C of nose-gear is according to geometrical principle:
The making and installation of this aircraft floor motion simulator requires:
According to different runway requirement, crawler belt should have different friction force, must possess the various physical parameters of true runway;
The attaching parts of rotating disk and crawler belt should have sufficient intensity, and warranty test is safe and effective to carry out;
Flexibility and reliability answered by movement or the bracing or strutting arrangement of whole simulation mechanism, is convenient to test operation.
According to aircraft actual weight, wheel actual size, turning system state, rationally determine the correlation parameter such as physical dimension and intensity of each parts, comprise the width of crawler belt, length, the attaching parts intensity etc. of crawler belt and rotating disk.
Start analog machine, after wheel stable rotation, the degree of bias of main of both sides can be obtained, before current aircraft can being obtained according to the method for calculating in Fig. 2, play the due degree of bias, finally in turning control system, relative set be carried out to front the degree of bias.The method is without the need to aircraft in ground taxi, and namely the turning efficiency of measurable aircraft, can save a large amount of research funding.
Specific embodiment described in the utility model is only preferred embodiment of the present utility model, is not used for limiting practical range of the present utility model.Namely all equivalences done according to the content of the utility model claim change and modify, and all belong to protection domain of the present utility model.
Claims (6)
1. an aircraft floor motion simulator, is characterized in that, comprising:
Base;
Rotating disk, it can be rotatably set on described base;
Transmission, it is supported in described rotating disk by the horizontal rotating shaft that two are arranged in parallel;
Actuator, it rotates around described horizontal rotating shaft for driving described Transmission, to drive the wheel of undercarriage to move, and drives described rotating disk to deflect along with the deflection of described wheel in horizontal plane, and
Power interface, it to be arranged on described base and for connecting power supply.
2. aircraft floor motion simulator according to claim 1, is characterized in that, described Transmission is crawler belt.
3. aircraft floor motion simulator according to claim 2, is characterized in that, described crawler belt has the various physical parameters of true runway.
4. the aircraft floor motion simulator according to any one of Claim 1-3, is characterized in that, also comprise:
Angle measuring mechanism, it to be arranged on described base and deflection angle for measuring described rotating disk.
5. aircraft floor motion simulator according to claim 4, is characterized in that, also comprise:
Signaling interface, it to be arranged on described base and for described aircraft floor motion simulator input emulation mode and the deflection angle outwards exporting described rotating disk.
6. aircraft floor motion simulator according to claim 4, is characterized in that, described angle measuring mechanism is sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420379175.3U CN204078085U (en) | 2014-07-10 | 2014-07-10 | Aircraft floor motion simulator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420379175.3U CN204078085U (en) | 2014-07-10 | 2014-07-10 | Aircraft floor motion simulator |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204078085U true CN204078085U (en) | 2015-01-07 |
Family
ID=52170826
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420379175.3U Active CN204078085U (en) | 2014-07-10 | 2014-07-10 | Aircraft floor motion simulator |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204078085U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105083589A (en) * | 2015-09-06 | 2015-11-25 | 吕亮霞 | Airplane rising, landing and taxiing performance comprehensive verification platform |
| CN109774966A (en) * | 2017-11-13 | 2019-05-21 | 中航通飞华南飞机工业有限公司 | A kind of device and method for not pushing up aircraft and carrying out Nose Wheel Steering functional check |
| CN112572827A (en) * | 2020-12-04 | 2021-03-30 | 中国航空工业集团公司成都飞机设计研究所 | Zero correction method for aircraft nose wheel turning |
-
2014
- 2014-07-10 CN CN201420379175.3U patent/CN204078085U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105083589A (en) * | 2015-09-06 | 2015-11-25 | 吕亮霞 | Airplane rising, landing and taxiing performance comprehensive verification platform |
| CN109774966A (en) * | 2017-11-13 | 2019-05-21 | 中航通飞华南飞机工业有限公司 | A kind of device and method for not pushing up aircraft and carrying out Nose Wheel Steering functional check |
| CN112572827A (en) * | 2020-12-04 | 2021-03-30 | 中国航空工业集团公司成都飞机设计研究所 | Zero correction method for aircraft nose wheel turning |
| CN112572827B (en) * | 2020-12-04 | 2023-04-14 | 中国航空工业集团公司成都飞机设计研究所 | Zero correction method for aircraft nose wheel turning |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP3614118B1 (en) | System for testing comprehensive performance of driverless vehicle | |
| CN204078085U (en) | Aircraft floor motion simulator | |
| CN105151292B (en) | Distributive vectored thrust system | |
| CN103954426B (en) | A kind of rotor dynamic testing equipment | |
| CN203811349U (en) | Rotor dynamic test device | |
| CN105083589A (en) | Airplane rising, landing and taxiing performance comprehensive verification platform | |
| CN102589840B (en) | Vertical or short-distance takeoff and landing aircraft ground effect test system | |
| CN105158004A (en) | Rotor aircraft test platform | |
| CN109094817B (en) | Carrier-based helicopter self-adaptive landing gear landing simulation system | |
| CN103419947A (en) | Autonomous landing navigation control ground test verification system under microgravity environment | |
| CN204964217U (en) | Rotor craft test platform | |
| CN105775154A (en) | General launching platform for unmanned aerial vehicle | |
| CN103413480B (en) | Three-dimensional simulation motion device | |
| CN202183176U (en) | Loading gradient follow-up and passive loading steering gear load simulator | |
| CN106707793A (en) | Helicopter semi-physical simulation test system | |
| CN104679000B (en) | Indoor simulation testing device and testing method for target object sensing capability of mobile robot | |
| CN104590582B (en) | A kind of aircraft blade power imitates test device | |
| CN102527058B (en) | Device for simulating steering wheel of airplane | |
| CN104142221B (en) | A kind of machine wheel rotating device | |
| CN203422871U (en) | Three-dimensional simulation movement device | |
| CN203882472U (en) | A double-motor active loading steering engine load simulator | |
| CN104280176B (en) | Eliminate wheel load and measure the lunar surface rover wheel load measuring unit of lateral error | |
| CN105035353A (en) | Fixing end bearing and connecting device for unmanned aerial vehicle test bed | |
| CN103606332A (en) | Spacecraft rendezvous and docking multi-degree-of-freedom semi-physical simulation method and device thereof | |
| CN208903471U (en) | Plane simulation flight experience device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |