CN104658398A - Semi-physical real-time simulation platform and method for airplane automatic brake - Google Patents
Semi-physical real-time simulation platform and method for airplane automatic brake Download PDFInfo
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- CN104658398A CN104658398A CN201310607166.5A CN201310607166A CN104658398A CN 104658398 A CN104658398 A CN 104658398A CN 201310607166 A CN201310607166 A CN 201310607166A CN 104658398 A CN104658398 A CN 104658398A
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- G—PHYSICS
- G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
- G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
- G09B25/00—Models for purposes not provided for in G09B23/00, e.g. full-sized devices for demonstration purposes
Abstract
The invention relates to a semi-physical real-time simulation platform and a semi-physical real-time simulation method for an airplane automatic brake. The platform comprises an automatic brake selective switch, an automatic brake controller, an automatic brake control valve, a real-time emulation computer, an airplane wheel rotating speed driving device, an airplane wheel velocity sensor and a visual display system. Compared with the conventional airplane anti-skid brake testing system, the semi-physical real-time simulation platform adopts the real-time emulation computer to perform operation on an airplane model, an undercarriage model and an airplane wheel braking system model; the automatic brake selective switch, the automatic brake controller, the automatic brake control valve and the airplane wheel velocity sensor adopt the real devices on the airplane; the airplane wheel rotating speed driving device can drive the airplane wheel velocity sensor to rotate; the semi-physical real-time simulation platform provides an effective means for design, test and verification of the control law of the airplane anti-skid braking system, reduces the time risk of the conventional inertia table test, saves a lot of capitals, and achieves obvious benefits.
Description
Technical field
The present invention relates to aircraft brake technical field, particularly relate to a kind of aircraft self-actuating brake semi-physical simulation platform and method.
Background technology
Aircraft brake control system is as important airborne equipment, can brake system normally work and will have a strong impact on aircraft safety, autobrake system is due in termination take-off and landing process, do not need manually to apply the deceleration that brake operation can complete aircraft, in aircraft landing process, autobrake system regulates brake pressure to ensure automatically, and aircraft slows down with the permanent rate of deceleration, occupant and the comfort of passenger in landing mission can be significantly improved, the working load of driver can also be reduced simultaneously, avoid the improper danger that may cause of pilot control brake, therefore technique widespread use in present military-civil aircraft.
But normally develop system test part in the development process of aircraft autobrake system, then carry out inertia test table to system test part to test, the traditional simulation of employing brake inertia platform joint-trial method to aircraft and runway pavement has suitable limitation, therefore truly cannot reflect the adaptability of autobrake system to environment for use, and with the matching of aircraft body.And test is wasted time and energy, costly.
Summary of the invention
The object of the invention is: provide one can simulated aircraft autobrake system real operating environments emulation test system and and its implementation.
Technical scheme of the present invention is: a kind of aircraft self-actuating brake semi-physical simulation platform, comprises self-actuating brake selector switch 1, automatic brake controller 2, self-actuating brake operation valve 3, real-time simulation computer 4, wheel rotational speed drives 5, wheel spin-up transducer 6 and visual display system 7; Self-actuating brake selector switch 1 and automatic brake controller 2 are electrically connected; Automatic brake controller 2 and self-actuating brake operation valve 3 adopt true connected mode on aircraft, self-actuating brake operation valve 3 and real-time simulation computer 4 are electrically connected, real-time simulation computer 4 and wheel rotational speed drives 5 are electrically connected, wheel rotational speed drives 5 and wheel spin-up transducer 6 are electrically connected, and real-time simulation computer 4 and visual display system 7 are electrically connected.
Self-actuating brake selector switch 1 have termination take off, land low, land in, land high and close gear, and any one in above-mentioned gear can be selected in.
Automatic brake controller 2 can realize controlling self-actuating brake operation valve 3 according to the output signal of the selected gear of self-actuating brake selector switch 1, aircraft rate that real-time simulation computer 4 real-time resolving goes out and wheel spin-up transducer 6.
The size of the control signal that self-actuating brake operation valve 3 can export according to automatic brake controller 2 exports corresponding brake pressure signal to real-time simulation computer 4.
Real-time simulation computer 4 can according to the wheel rate signal of input and brake pressure signal, run model aircraft, Landing gear model and wheel brake system model, and real-time resolving can go out aircraft current operating conditions, main wheel velocity of rotation and aircraft rate.
Wheel rotational speed drives 5 accepts main wheel velocity of rotation signal that real-time simulation computer 4 real-time resolving goes out and controls wheel spin-up transducer 6 running speed.
Wheel spin-up transducer 6 is rotated by self thus obtains main airplane wheel rotational speed.
Visual display system 7 can show the picture of aircraft current operating conditions.
A kind of aircraft self-actuating brake semi-physical simulation method, comprises the following steps:
The first step, driver's selected self-actuating brake selector switch 1 before landing is low in landing, land in, high any gear of landing, and self-actuating brake rate of deceleration gear is sent to automatic brake controller 2;
Second step, automatic brake controller 2 carries out brake to self-actuating brake operation valve 3 according to rate of deceleration gear, wheel spin-up transducer (6) and aircraft rate signal that self-actuating brake selector switch 1 is selected and controls after computing;
3rd step, self-actuating brake pressure signal is sent to real-time simulation computer 4 by self-actuating brake operation valve 3;
4th step, real-time simulation computer 4 goes out current aircraft running status, main wheel velocity of rotation and aircraft rate according to current aircraft system brake pressure signal, model aircraft, Landing gear model and wheel brake system model real-time resolving; Wherein, aircraft current operating conditions is shown by being sent to visual display system 7, main wheel velocity of rotation value is sent to wheel rotational speed drives 5, aircraft rate signal is sent to automatic brake controller 2;
5th step, wheel rotational speed drives 5 is resolved the velocity of rotation of value to wheel spin-up transducer 6 according to main wheel velocity of rotation and is controlled, and makes it export corresponding speed;
6th step, automatic brake controller 2 receives the rotary regimes of wheel spin-up transducer 6, judge whether airplane wheel is in slip state, and carry out brake and pine in conjunction with the rate of deceleration gear of self-actuating brake selector switch 1 and aircraft front deceleration rate and to stop control, and then forward second step to and circulate.
The invention has the beneficial effects as follows: compared with traditional aircraft self-actuating brake pilot system, the present invention adopts real-time simulation computer to carry out model aircraft, the computing of undercarriage and wheel brake system model, self-actuating brake selector switch, automatic brake controller, self-actuating brake operation valve and wheel spin-up transducer adopt real equipment on aircraft, wheel rotational speed drives energy driving machine wheel speed sensor rotation, this self-actuating brake semi-physical simulation platform is aircraft autobrake system design of control law, test and checking provide effective means, decrease time risk also saving and a large amount of funds that conventional inertia bench teat is tested, there is obvious benefit.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
Embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail:
As shown in Figure 1, a kind of aircraft self-actuating brake semi-physical simulation platform, comprises self-actuating brake selector switch 1, automatic brake controller 2, self-actuating brake operation valve 3, real-time simulation computer 4, wheel rotational speed drives 5, wheel spin-up transducer 6 and visual display system 7; Self-actuating brake selector switch 1 and automatic brake controller 2 are electrically connected; Automatic brake controller 2 and self-actuating brake operation valve 3 adopt true connected mode on aircraft, self-actuating brake operation valve 3 and real-time simulation computer 4 are electrically connected, real-time simulation computer 4 and wheel rotational speed drives 5 are electrically connected, wheel rotational speed drives 5 and wheel spin-up transducer 6 are electrically connected, and real-time simulation computer 4 and visual display system 7 are electrically connected.
Self-actuating brake selector switch 1 have termination take off, land low, land in, land high and close gear, and any one in above-mentioned gear can be selected in.After driver is selected, self-actuating brake selector switch 1 can outwards export corresponding level signal to simulate this gear.The aircraft rate that each correspondence of analog level signal of above-mentioned gear is different.
Automatic brake controller 2 can realize controlling self-actuating brake operation valve 3 according to the output signal of the selected gear of self-actuating brake selector switch 1, aircraft rate that real-time simulation computer 4 real-time resolving goes out and wheel spin-up transducer 6.According to the output signal of wheel spin-up transducer 6, first automatic brake controller 2 judges whether aircraft is in slip state, as aircraft is in slip state, then reduce the control signal of automatic brake controller 2 pairs of self-actuating brake operation valves 3; As aircraft is in non-slip state, carry out following computing: by aircraft rate corresponding for incoming level signal and time the simulation computer 4 real-time resolving aircraft rate that goes out compare, the aircraft rate that when if the aircraft rate that incoming level signal is corresponding is greater than, simulation computer 4 real-time resolving goes out, then automatic brake controller 2 increases the control signal to self-actuating brake operation valve 3; The aircraft rate that when if the aircraft rate that incoming level signal is corresponding is less than, simulation computer 4 real-time resolving goes out, then automatic brake controller 2 reduces the control signal to self-actuating brake operation valve 3; The aircraft rate that when if the aircraft rate that incoming level signal is corresponding equals, simulation computer 4 real-time resolving goes out, then automatic brake controller 2 keeps the control signal to self-actuating brake operation valve 3.
The size of the control signal that self-actuating brake operation valve 3 can export according to automatic brake controller 2 exports corresponding brake pressure signal to real-time simulation computer 4.
Real-time simulation computer 4 can according to the wheel rate signal of input and brake pressure signal, run model aircraft, Landing gear model and wheel brake system model, above-mentioned model by MATLAB software simulating, and real-time resolving can go out aircraft current operating conditions, main wheel velocity of rotation and aircraft rate.
Wheel rotational speed drives 5 accepts main wheel velocity of rotation signal that real-time simulation computer 4 real-time resolving goes out and controls wheel spin-up transducer 6 to operate according to this rate signal.Wheel rotational speed drives 5 can be the drive motor of tape controller.
Wheel spin-up transducer 6 is rotated by self thus obtains main airplane wheel rotational speed.During concrete enforcement, this wheel spin-up transducer 6 can be directly installed on drive motor, and does not need to be arranged on wheel.
Visual display system 7 can show the picture of aircraft current operating conditions.
When aircraft carries out self-actuating brake semi-physical simulation, first, driver sends self-actuating brake instruction by self-actuating brake selector switch 1, and brake deceleration rate gear is sent to automatic brake controller 2; Automatic brake controller 2 carries out self-actuating brake control according to brake deceleration rate gear to brake control valve 3; System brake pressure signal is sent to real-time simulation computer 4 by self-actuating brake operation valve 3; Real-time simulation computer 4, according to current aircraft system brake pressure, run model aircraft and Landing gear model and wheel brake system model, and real-time resolving goes out current aircraft running status, main wheel velocity of rotation and aircraft rate; Wherein, aircraft current operating conditions is shown by being sent to visual display system 7, main wheel velocity of rotation value is sent to wheel rotational speed drives 5; Wheel rotational speed drives 5 is resolved the velocity of rotation of value to wheel spin-up transducer 6 according to main wheel velocity of rotation and is controlled, and makes it export corresponding speed; Aircraft rate signal is sent to automatic brake controller 2; Automatic brake controller 2 receives the rotary regimes of wheel spin-up transducer 6, judge whether airplane wheel is in slip state, and carry out brake and pine in conjunction with the aircraft rate signal that the brake deceleration rate gear of self-actuating brake selector switch 1 and real-time simulation computer transmit and to stop control.
When detecting that aircraft is in slip state, automatic brake controller 2 pairs of self-actuating brake operation valves 3 carry out anti-sliding control, discharge system brake pressure, now real-time simulation computer 4 is according to the system pressure after release, carry out aircraft running status, main wheel velocity of rotation and aircraft rate real-time resolving, main wheel velocity of rotation value is sent to wheel rotational speed drives 5; Wheel rotational speed drives 5 is resolved the velocity of rotation of value to wheel spin-up transducer 6 according to main wheel velocity of rotation and is controlled.
When detecting that aircraft is in rotary state, and when aircraft rate is less than the rate of deceleration of brake deceleration rate gear requirement, automatic brake controller 2 self-actuating brake controls 3 and carries out brake control, increase system brake pressure, until the deceleration rate value required with brake deceleration rate gear is suitable, now real-time simulation computer 4 is according to the system pressure after increase, carry out aircraft running status, main wheel velocity of rotation and aircraft rate real-time resolving, main wheel velocity of rotation value is sent to wheel rotational speed drives 5; Wheel rotational speed drives 5 is resolved the velocity of rotation of value to wheel spin-up transducer 6 according to main wheel velocity of rotation and is controlled.
Claims (6)
1. an aircraft self-actuating brake semi-physical simulation platform, it is characterized in that, this platform comprises self-actuating brake selector switch (1), automatic brake controller (2), self-actuating brake operation valve (3), real-time simulation computer (4), wheel rotational speed drives (5), wheel spin-up transducer (6) and visual display system (7); Self-actuating brake selector switch (1) and automatic brake controller (2) are electrically connected; Automatic brake controller (2) and self-actuating brake operation valve (3) adopt true connected mode on aircraft, self-actuating brake operation valve (3) and real-time simulation computer (4) are electrically connected, real-time simulation computer (4) and wheel rotational speed drives (5) are electrically connected, wheel rotational speed drives (5) and wheel spin-up transducer (6) are electrically connected, and real-time simulation computer (4) and visual display system (7) are electrically connected.
2. a kind of aircraft self-actuating brake semi-physical simulation platform as claimed in claim 1, is characterized in that, self-actuating brake selector switch (1) have termination take off, land low, land in, land high and close gear, and any one in above-mentioned gear can be selected in.
3. a kind of aircraft self-actuating brake semi-physical simulation platform as claimed in claim 1, it is characterized in that, real-time simulation computer (4) can run model aircraft, Landing gear model and wheel brake system model, and real-time resolving can go out aircraft current operating conditions, main wheel velocity of rotation and aircraft rate.
4. a kind of aircraft self-actuating brake semi-physical simulation platform as claimed in claim 1, is characterized in that, wheel rotational speed drives (5) can accept external control signal and control wheel spin-up transducer (6) running speed.
5. a kind of aircraft self-actuating brake semi-physical simulation platform as claimed in claim 1, it is characterized in that, visual display system (7) can show the picture of aircraft current operating conditions.
6. an aircraft self-actuating brake semi-physical simulation method, is characterized in that, this method comprises the following steps:
The first step, driver's selected self-actuating brake selector switch (1) before landing is low in landing, land in, high any gear of landing, and self-actuating brake rate of deceleration gear is sent to automatic brake controller (2);
Second step, automatic brake controller (2) carries out brake to self-actuating brake operation valve (3) according to rate of deceleration gear, wheel spin-up transducer (6) and aircraft rate signal that self-actuating brake selector switch (1) is selected and controls after computing;
3rd step, self-actuating brake pressure is sent to real-time simulation computer (4) by self-actuating brake operation valve (3);
4th step, real-time simulation computer (4) goes out current aircraft running status, main wheel velocity of rotation and aircraft rate according to current aircraft system brake pressure signal, model aircraft, Landing gear model and wheel brake system model real-time resolving; Wherein, aircraft current operating conditions being shown by being sent to visual display system (7), main wheel velocity of rotation value being sent to wheel rotational speed drives (5), aircraft rate signal is sent to automatic brake controller (2);
5th step, wheel rotational speed drives (5) is resolved the velocity of rotation of value to wheel spin-up transducer (6) according to main wheel velocity of rotation and is controlled, and makes it export corresponding speed;
6th step, automatic brake controller (2) receives the rotary regimes of wheel spin-up transducer (6), judge whether airplane wheel is in slip state, and carry out brake and pine in conjunction with the rate of deceleration gear of self-actuating brake selector switch (1) and aircraft front deceleration rate and to stop control, and then forward second step to and circulate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310607166.5A CN104658398A (en) | 2013-11-22 | 2013-11-22 | Semi-physical real-time simulation platform and method for airplane automatic brake |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310607166.5A CN104658398A (en) | 2013-11-22 | 2013-11-22 | Semi-physical real-time simulation platform and method for airplane automatic brake |
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| CN104658398A true CN104658398A (en) | 2015-05-27 |
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| CN201310607166.5A Pending CN104658398A (en) | 2013-11-22 | 2013-11-22 | Semi-physical real-time simulation platform and method for airplane automatic brake |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106933216A (en) * | 2017-03-13 | 2017-07-07 | 北京航空航天大学 | A kind of test device for aircraft brake controller |
| CN111125924A (en) * | 2019-12-30 | 2020-05-08 | 四川函钛科技有限公司 | Airplane landing automatic deceleration gear identification method based on QAR parameter feature extraction |
| CN114419951A (en) * | 2022-02-24 | 2022-04-29 | 中航贵州飞机有限责任公司 | DDS-based airplane wheel speed simulation system |
Citations (4)
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| US5024491A (en) * | 1976-11-18 | 1991-06-18 | The Boeing Company | Automatic aircraft braking system including wheelspeed responsive control apparatus |
| CN101604490A (en) * | 2008-06-11 | 2009-12-16 | 北京航空航天大学 | Semi-physical simulation platform structure of airplane brake system |
| CN102092373A (en) * | 2010-12-16 | 2011-06-15 | 西安航空制动科技有限公司 | Automatic braking method and device for plane |
| CN103309241A (en) * | 2013-03-25 | 2013-09-18 | 中国航空工业集团公司沈阳飞机设计研究所 | United simulation braking semi-physical simulation system |
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2013
- 2013-11-22 CN CN201310607166.5A patent/CN104658398A/en active Pending
Patent Citations (4)
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|---|---|---|---|---|
| US5024491A (en) * | 1976-11-18 | 1991-06-18 | The Boeing Company | Automatic aircraft braking system including wheelspeed responsive control apparatus |
| CN101604490A (en) * | 2008-06-11 | 2009-12-16 | 北京航空航天大学 | Semi-physical simulation platform structure of airplane brake system |
| CN102092373A (en) * | 2010-12-16 | 2011-06-15 | 西安航空制动科技有限公司 | Automatic braking method and device for plane |
| CN103309241A (en) * | 2013-03-25 | 2013-09-18 | 中国航空工业集团公司沈阳飞机设计研究所 | United simulation braking semi-physical simulation system |
Non-Patent Citations (1)
| Title |
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| 张航其: "机轮刹车系统半物理仿真仿真试验平台设计与实现", 《中国优秀硕士学位论文全文数据库 工程科技II辑》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106933216A (en) * | 2017-03-13 | 2017-07-07 | 北京航空航天大学 | A kind of test device for aircraft brake controller |
| CN111125924A (en) * | 2019-12-30 | 2020-05-08 | 四川函钛科技有限公司 | Airplane landing automatic deceleration gear identification method based on QAR parameter feature extraction |
| CN111125924B (en) * | 2019-12-30 | 2023-04-11 | 四川函钛科技有限公司 | Airplane landing automatic deceleration gear identification method based on QAR parameter feature extraction |
| CN114419951A (en) * | 2022-02-24 | 2022-04-29 | 中航贵州飞机有限责任公司 | DDS-based airplane wheel speed simulation system |
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Application publication date: 20150527 |
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