CN205050405U - Analog simulation system - Google Patents
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- CN205050405U CN205050405U CN201520481493.5U CN201520481493U CN205050405U CN 205050405 U CN205050405 U CN 205050405U CN 201520481493 U CN201520481493 U CN 201520481493U CN 205050405 U CN205050405 U CN 205050405U
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Abstract
The embodiment of the utility model discloses analog simulation system relates to aviation technical field, can carry out ground proximity warning system's flight experiment with lower cost and risk. The utility model discloses a method includes: aircraft dynamics simulation system links to each other with operating mechanism, and operating mechanism includes at least: steering wheel, pedal and throttle lever, three -dimensional what comes into a driver's display system links to each other with aircraft dynamics simulation system, it links to each other with aircraft dynamics simulation system and three -dimensional what comes into a driver's display system to report an emergency and ask for help or increased vigilance the computer for the outside flight environment information of sending according to aircraft state information and three -dimensional what comes into a driver's display system generates alarm information, the instrument display module respectively with report an emergency and ask for help or increased vigilance computer, aircraft dynamics simulation system and three -dimensional what comes into a driver's display system and link to each other. The utility model is suitable for an analog simulation of warning system.
Description
Technical field
The utility model relates to technical field of aerospace, particularly relates to a kind of Analog Simulation System.
Background technology
Ground proximity warning system is mainly used in the distance ensureing aircraft and ground, in the situation such as terrible weather, low visibility, especially avoid the collision on aircraft and ground, is ensure one of requisite subsystem of aircraft safety.
But the research and development of ground proximity warning system and subsequent upgrade, need a large amount of flying qualities and log, for the ground proximity warning system of different machine, flying quality needed for it and log are not identical, need to carry out a large amount of experiment in flight test and just can obtain flying quality and log comparatively accurately, and because environment of taking a flight test is changeable, be difficult to prediction, therefore Aircraft Flight Test is very risky, and cost of taking a flight test is also very high.And if ground proximity warning system is tested insufficient, be then easy to cause system flaw thus cause aircraft accident.Therefore the research and development of ground proximity warning system and maintenance cost and experiment risk very high.
Utility model content
Embodiment of the present utility model provides a kind of Analog Simulation System, can carry out the flight experiment of ground proximity warning system with lower cost and risk.
For achieving the above object, embodiment of the present utility model adopts following technical scheme:
First aspect, embodiment of the present utility model provides a kind of Analog Simulation System, comprising: catanator (1), aircraft dynamics analogue system (2), three-dimensional vision display system (3), alarm computing machine (4) and meter display module (5);
Described aircraft dynamics analogue system (2) is connected with described catanator (1), for receiving the operational order that described catanator (1) sends, described catanator (1) at least comprises: bearing circle, pedal and throttle lever;
Described three-dimensional vision display system (3) is connected with described aircraft dynamics analogue system (2), for the flight status parameter display three-dimensional vision image sent according to described aircraft dynamics analogue system (2), described flight status parameter at least comprises: longitude, latitude, highly, the angle of pitch, crab angle, roll angle, the angle of attack and yaw angle;
Described alarm computing machine (4) is connected with described three-dimensional vision display system (3) with described aircraft dynamics analogue system (2), generates warning information for the external flight environmental information sent according to described aircraft state information and described three-dimensional vision display system (3);
Described meter display module (5) is connected with described three-dimensional vision display system (3) with described alarm computing machine (4), described aircraft dynamics analogue system (2) respectively, for showing the flight control information that described aircraft state information, described warning information and described aircraft dynamics analogue system (2) send.
Second aspect, embodiment of the present utility model provides a kind of method for Analog Simulation System, and described Analog Simulation System comprises: catanator (1), aircraft dynamics analogue system (2), three-dimensional vision display system (3), alarm computing machine (4) and meter display module (5); Described aircraft dynamics analogue system (2) is connected with described catanator (1), for receiving the operational order that described catanator (1) sends, described catanator (1) at least comprises: bearing circle, pedal and throttle lever; Described three-dimensional vision display system (3) is connected with described aircraft dynamics analogue system (2), for the flight status parameter display three-dimensional vision image sent according to described aircraft dynamics analogue system (2), described flight status parameter at least comprises: longitude, latitude, highly, the angle of pitch, crab angle, roll angle, the angle of attack and yaw angle; Described alarm computing machine (4) is connected with described three-dimensional vision display system (3) with described aircraft dynamics analogue system (2), generates warning information for the external flight environmental information sent according to described aircraft state information and described three-dimensional vision display system (3); Described meter display module (5) is connected with described three-dimensional vision display system (3) with described alarm computing machine (4), described aircraft dynamics analogue system (2) respectively, for showing the flight control information that described aircraft state information, described warning information and described aircraft dynamics analogue system (2) send;
Described alarm computing machine (4) generates warning information according to described aircraft state information and described external flight environmental information, comprising:
Described alarm computing machine (4) judges aircraft status according to described aircraft state information, and described aircraft status comprises: rise, decline is peaceful flies state; And obtain the priority of the alert mode corresponding with determined state and alert mode, then generate described warning information according to the priority of determined alert mode and alert mode.
The Analog Simulation System that the utility model embodiment provides, the control command that can send according to catanator, the flight progress of aircraft is simulated by aircraft dynamics analogue system, form flight status parameter, and by alarm computing machine with reference to flight status parameter and flight environment of vehicle information, warning information sent to the meter display module be connected and shows, thus achieves and carry out experiment in flight test by the Analog Simulation System on ground replacement aircraft, reducing the cost and risk of flight experiment.
Accompanying drawing explanation
In order to be illustrated more clearly in the technical scheme in the utility model embodiment, be briefly described to the accompanying drawing used required in embodiment below, apparently, accompanying drawing in the following describes is only embodiments more of the present utility model, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to these accompanying drawings.
The structural representation of the Analog Simulation System that Fig. 1 provides for the utility model embodiment;
The schematic flow sheet of the Analog Simulation System course of work that Fig. 2 provides for the utility model embodiment.
Embodiment
Below in conjunction with the accompanying drawing in the utility model embodiment, be clearly and completely described the technical scheme in the utility model embodiment, obviously, described embodiment is only the utility model part embodiment, instead of whole embodiments.Based on the embodiment in the utility model, those of ordinary skill in the art are not making other embodiments all obtained under creative work prerequisite, all belong to the scope of the utility model protection.
The utility model embodiment provides a kind of Analog Simulation System as shown in Figure 1, comprising: catanator (1), aircraft dynamics analogue system (2), three-dimensional vision display system (3), alarm computing machine (4) and meter display module (5).
Wherein: aircraft dynamics analogue system (2) is connected with catanator (1), for receiving the operational order that catanator (1) sends, catanator (1) at least comprises: bearing circle, pedal and throttle lever.In the preferred version of the present embodiment, aircraft dynamics analogue system (2) is set up based on Simulink, and is generated as the C code through optimizing, thus improves computing velocity, reduces process time delay.Aircraft dynamics analogue system (2), specifically for being read the operational order that catanator (1) sends by USB interface, described operational order is for representing described pedal to elevating rudder and aileron, described bearing circle to yaw rudder, and described throttle lever is to the control of throttle, realize the real-time simulation of aircraft six degree of freedom, and obtain flight status parameter.
Three-dimensional vision display system (3) is connected with aircraft dynamics analogue system (2), for the flight status parameter display three-dimensional vision image sent according to aircraft dynamics analogue system (2), flight status parameter at least comprises: longitude, latitude, highly, the angle of pitch, crab angle, roll angle, the angle of attack and yaw angle.
Alarm computing machine (4) is connected with three-dimensional vision display system (3) with aircraft dynamics analogue system (2), generates warning information for the external flight environmental information sent according to aircraft state information and three-dimensional vision display system (3).
Meter display module (5) is connected with three-dimensional vision display system (3) with alarm computing machine (4), aircraft dynamics analogue system (2) respectively, for showing the flight control information that aircraft state information, warning information and aircraft dynamics analogue system (2) send.
Concrete, catanator (1) is connected with the PilotControl module in aircraft dynamics analogue system (2) by USB interface.Aircraft dynamics analogue system (2), specifically for being read the operational order that catanator (1) sends by USB interface, operational order is for representing pedal to elevating rudder and aileron, bearing circle to yaw rudder, and throttle lever is to the control of throttle.
In the present embodiment, the machinery instrument, electronic instrument, the display instrument that are specifically connected with alarm computing machine (4) of meter display module (5); Or the virtual instrument be integrated on alarm computing machine (4), such as: meter display module (5) is the virtual instrument adopting Tilcon Software for Design.Further, meter display module (5) comprises main flight display and navigation display two parts, the parameter of main flight display section display at least comprises: the attitude of aircraft, air speed, Mach number, barometer altitude, air pressure benchmark, rising or falling speed and radio altitude, the parameter of navigation display section display at least comprises: flight path, front landform, alarm word and sound.
In the possibility of the present embodiment, catanator (1), aircraft dynamics analogue system (2), three-dimensional vision display system (3), connected by STP netting twine between alarm computing machine (4) and meter display module (5) and be constructed as LAN (Local Area Network).Such as, by STP netting twine, catanator (1), aircraft dynamics analogue system (2), three-dimensional vision display system (3), alarm computing machine (4) be connected with meter display module (5) with Huawei S5700-24TP-SI (AC) Ethernet switch and be constructed as LAN (Local Area Network), realizing the data interaction of each ingredient in Analog Simulation System by too network switch.
Wherein, three-dimensional vision display system (3) comprises at least three displays, and each display is connected with a what comes into a driver's computing machine, and each display specifies the scenery of viewing angle for showing.Three-dimensional vision display system (3) specifically can be realized by FlightGear, flight status parameter is packed, FlightGear is sent to by UDP network, realize three-dimensional vision display, visual display uses the scenery outside three pieces of display display machines, and three what comes into a driver's computing machines can obtain the scenery of different view mode by the different viewpoint position of setting, angle of pitch side-play amount, deflection side-play amount, visual angle.
Concrete, what comes into a driver's computing machine in the present embodiment, alarm computing machine (4) and the hardware configuration of computing machine running aircraft dynamics analogue system (2) are all the processor of IntelCorei3, dominant frequency 2.93GHz, 2G internal memory, the video card of GTS450.If meter display module (5) is for computing machine is by the virtual instrument of process simulation, then alarm computing machine (4) and meter display module (5) can be integrated on same computer.
The UDP message bag that the what comes into a driver's computing machine be connected with display is broadcasted by STP netting twine for receiving aircraft dynamics analogue system (2), UDP message bag is packed by flight status parameter and is obtained.
Based on Analog Simulation System as shown in Figure 1, the utility model embodiment also provides a kind of method for Analog Simulation System, comprising:
Alarm computing machine (4) generates warning information according to aircraft state information and external flight environmental information, comprising:
Alarm computing machine (4) judges aircraft status according to aircraft state information, and aircraft status comprises: rise, decline is peaceful flies state.And obtain the priority of the alert mode corresponding with determined state and alert mode, then generate warning information according to the priority of determined alert mode and alert mode.
Concrete, according to the aircraft state information received, alarm computing machine (4) judges that aircraft is in rising, decline peaceful which kind of state flown in state, determine the priority of the alert mode corresponding with this state again, finally calculate according to the algorithm under alert mode, provide correct warning information.This design avoids the algorithm of exhaustive each alert mode, improves the processing speed of alarm computing machine (4), reduces time delay, thus makes the response speed of Analog Simulation System close to the flight of real aircraft.
In the present embodiment, alert mode at least comprises:
Pattern 1 (excessive rate of descent warning): if radio altitude h<30ft or h>2450ft or h+572+0.6035*hd (altitude rate, ft/min) >0, then not at alarm region, do not send any warning
If: h+1620+1.1133*hd>0 or h+400+0.4*hd>0, be then in outer alarm region, sends " SINKRATE " and report to the police.Otherwise: be in interior alarm region, send warning information " PULLUP ".
Pattern 2 (excessive landform is reported to the police close to rate): if (landform is close to rate for V (air speed) <220kn and h<=1650ft and h+1579-0.7895*CR, ft/min) <=0, and h-522-0.1968*CR<=0
Or V>310kn and h<=2450ft and h+1579-0.7895*CR<=0 and h-522-0.1968*CR<=0,
Or 220<=V<=310kn and h<=1650+ (V-220) * 8.9 and h+1579-0.7895*CR<=0 and h-522-0.1968*CR<=0,
Then all be in outer alarm region, send warning information " TERRAIN ".Warning information " TERRAIN " continued after 1.6 seconds, sent warning information " PULLUP ".
Mode 3 (take off or go around high too many report to the police): if 30ft<h<1500ft and △ h
p(falling height)-5.4-0.092*h>=0, be then in alarm region, sends warning information " DON'TSINK ".
Pattern 4 (dangerous terrain clearance warning): if wing flap is transferred be less than 25 units, and gear up, and V<=190kn and 30ft<h<500ft, then be in left side alarm region, send warning information " TOOLOWGEAR "
If 190kn<=V<=250kn and h<500+500* (V-190)/60 or V>250kn and 30ft<h<1000ft, then be in the right alarm region, send warning information " TOOLOWTERRAIN ".
Pattern 5 (glide-slope deviation is reported to the police too much): if 30ft<h<300ft and Ω >0.7 ° and h>293-204.1* Ω, then be in hard alarm region, send warning information " GLIDESLOPE ".
If 30ft<h<1000ft and Ω >0.455 ° and h>243-204.1* Ω, be then in soft alarm region, send warning information " GLIDESLOPE ".
Pattern 6 (report of radio altitude and decision height): if when h drop to 100ft, then send warning information " ONEHUNDRED ",
If when h drop to 50ft, then send warning information " FIFTY ",
If when h drop to 30ft, then send warning information " THIRTY ".
Mode 7 (low warning): if 10ft<h<1500ft, and ud (percentage speed variation windward, kn/s)/2.75+w (vertical velocity, ft/min)/2250>1, then send warning information " CautionWindShear "
If ud/2.75+w/2250<-1, then send warning information " WindShear, WindShear ".
Wherein, the priority of alert mode comprises: be followed successively by by the order of height to ground according to priority: the warning information " Windshear " of mode 7, the warning information " Pull-Up " of pattern 1, the warning information " Pull-Up " of pattern 2, the warning information " Terrain " of pattern 2, the warning information " TooLowTerrain " of pattern 4, warning information " the Minimum of pattern 6, Minimum ", the warning information " TooLowGear " of pattern 4, the warning information " SinkRate " of pattern 1, the warning information " Don'tSink " of mode 3, the warning information " GlideSlope " of pattern 5, the warning information " ONEHUNDRED " of pattern 6, the warning information " CautionWindshear " of mode 7.
Apply above-mentioned pattern, Analog Simulation System of the present utility model, its main working process can as shown in Figure 2, comprise: by handling Manual operation mechanism (1), produce the operational order of main control rudder face and throttle; After PilotControl module in aircraft dynamics analogue system (2) receives command signal, starting in aircraft dynamics analogue system (2) emulates, and flight status parameter is packaged into UDP message bag, three-dimensional vision display system (3) is transferred to by ethernet line, such as FlightGear, meter display module (5) and alarm computing machine (4); Three-dimensional vision display system (3) display aircraft and the outer scene of machine, be convenient to the motion state that user observes aircraft; Meter display module (5) is display aircraft state parameter in real time, environmental parameter and warning information; Alarm computing machine (4) is according to the status information of aircraft and external environmental information, which kind of judge that aircraft is in take off, enter near landing and state in other state of flight, determine the priority of the alert mode corresponding with this state again, calculate finally by the algorithm under alert mode, provide correct warning information.
Each embodiment in this instructions all adopts the mode of going forward one by one to describe, between each embodiment identical similar part mutually see, what each embodiment stressed is the difference with other embodiments.Especially, for apparatus embodiments, because it is substantially similar to embodiment of the method, so describe fairly simple, relevant part illustrates see the part of embodiment of the method.
The above; be only embodiment of the present utility model; but protection domain of the present utility model is not limited thereto; anyly be familiar with those skilled in the art in the technical scope that the utility model discloses; the change that can expect easily or replacement, all should be encompassed within protection domain of the present utility model.Therefore, protection domain of the present utility model should be as the criterion with the protection domain of claim.
Claims (5)
1. an Analog Simulation System, it is characterized in that, comprising: catanator (1), aircraft dynamics analogue system (2), three-dimensional vision display system (3), alarm computing machine (4) and meter display module (5);
Described aircraft dynamics analogue system (2) is connected with described catanator (1), for receiving the operational order that described catanator (1) sends, described catanator (1) at least comprises: bearing circle, pedal and throttle lever;
Described three-dimensional vision display system (3) is connected with described aircraft dynamics analogue system (2), for the flight status parameter display three-dimensional vision image sent according to described aircraft dynamics analogue system (2), described flight status parameter at least comprises: longitude, latitude, highly, the angle of pitch, crab angle, roll angle, the angle of attack and yaw angle;
Described alarm computing machine (4) is connected with described three-dimensional vision display system (3) with described aircraft dynamics analogue system (2), generates warning information for the external flight environmental information sent according to described aircraft state information and described three-dimensional vision display system (3);
Described meter display module (5) is connected with described three-dimensional vision display system (3) with described alarm computing machine (4), described aircraft dynamics analogue system (2) respectively, for showing the flight control information that described aircraft state information, described warning information and described aircraft dynamics analogue system (2) send.
2. Analog Simulation System according to claim 1, is characterized in that, described catanator (1) is connected with the PilotControl module in described aircraft dynamics analogue system (2) by USB interface;
Aircraft dynamics analogue system (2), specifically for being read the operational order that catanator (1) sends by described USB interface, described operational order is for representing described pedal to elevating rudder and aileron, described bearing circle to yaw rudder, and described throttle lever is to the control of throttle.
3. Analog Simulation System according to claim 1, it is characterized in that, described meter display module (5) comprises main flight display and navigation display two parts, the parameter of described main flight display section display at least comprises: the attitude of aircraft, air speed, Mach number, barometer altitude, air pressure benchmark, rising or falling speed and radio altitude, the parameter of described navigation display section display at least comprises: flight path, front landform, alarm word and sound.
4. Analog Simulation System according to claim 1, it is characterized in that, described catanator (1), described aircraft dynamics analogue system (2), described three-dimensional vision display system (3), connected by STP netting twine between described alarm computing machine (4) and described meter display module (5) and be constructed as LAN (Local Area Network).
5. Analog Simulation System according to claim 4, it is characterized in that, described three-dimensional vision display system (3) comprises at least three displays, and each display is connected with a what comes into a driver's computing machine, and each display specifies the scenery of viewing angle for showing;
The UDP message bag that the what comes into a driver's computing machine be connected with display is broadcasted by described STP netting twine for receiving described aircraft dynamics analogue system (2), described UDP message bag is packed by described flight status parameter and is obtained.
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104992587A (en) * | 2015-07-06 | 2015-10-21 | 南京航空航天大学 | Analog simulation system |
| CN107293157A (en) * | 2016-04-01 | 2017-10-24 | 中国航空工业集团公司雷华电子技术研究所 | A kind of Testing Platform method perceived for landform with warning system |
| CN110992764A (en) * | 2019-12-27 | 2020-04-10 | 北京和利时电机技术有限公司 | Simulated driving control system, method and device and readable storage medium |
| CN111028611A (en) * | 2019-12-18 | 2020-04-17 | 珠海翔翼航空技术有限公司 | Data processing system and method for aircraft driving parameter simulation playback |
| CN111161409A (en) * | 2019-12-27 | 2020-05-15 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft support equipment verification system |
| CN114120792A (en) * | 2021-11-30 | 2022-03-01 | 中国人民解放军海军航空大学 | Special teaching aid based on aircraft attitude control |
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2015
- 2015-07-06 CN CN201520481493.5U patent/CN205050405U/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104992587A (en) * | 2015-07-06 | 2015-10-21 | 南京航空航天大学 | Analog simulation system |
| CN107293157A (en) * | 2016-04-01 | 2017-10-24 | 中国航空工业集团公司雷华电子技术研究所 | A kind of Testing Platform method perceived for landform with warning system |
| CN107293157B (en) * | 2016-04-01 | 2020-07-03 | 中国航空工业集团公司雷华电子技术研究所 | Test platform design method for terrain awareness and warning system |
| CN111028611A (en) * | 2019-12-18 | 2020-04-17 | 珠海翔翼航空技术有限公司 | Data processing system and method for aircraft driving parameter simulation playback |
| CN110992764A (en) * | 2019-12-27 | 2020-04-10 | 北京和利时电机技术有限公司 | Simulated driving control system, method and device and readable storage medium |
| CN111161409A (en) * | 2019-12-27 | 2020-05-15 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft support equipment verification system |
| CN111161409B (en) * | 2019-12-27 | 2023-10-13 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft guarantee equipment verification system |
| CN114120792A (en) * | 2021-11-30 | 2022-03-01 | 中国人民解放军海军航空大学 | Special teaching aid based on aircraft attitude control |
| CN114120792B (en) * | 2021-11-30 | 2024-02-27 | 中国人民解放军海军航空大学 | Special teaching aid based on aircraft attitude control |
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