CN102426426A - Aviation navigation signal simulation system applied to flight check - Google Patents
Aviation navigation signal simulation system applied to flight check Download PDFInfo
- Publication number
- CN102426426A CN102426426A CN2011104213003A CN201110421300A CN102426426A CN 102426426 A CN102426426 A CN 102426426A CN 2011104213003 A CN2011104213003 A CN 2011104213003A CN 201110421300 A CN201110421300 A CN 201110421300A CN 102426426 A CN102426426 A CN 102426426A
- Authority
- CN
- China
- Prior art keywords
- signal
- simulation
- navigation
- aviation
- ils
- 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.)
- Pending
Links
Images
Abstract
The invention discloses an aviation navigation signal simulation system applied to flight check, which mainly comprises a control computer, a multimode receiver, an aviation signal generator, an ARINC (Aeronautical Radio Incorporated) 429 bus, an emission antenna and a receiving antenna. According to the simulation models of various navigation signals under different flight procedures, the system utilizes a simulation system control program to control the aviation signal generator to generate various navigation signals; the navigation signals are sent out via the emission antenna so as to provide an analog simulation signal for the flight check system; and cost for researching, calibrating and maintaining the flight check system is lowered. The aviation navigation signal simulation system can better simulate navigation signals, such as ILS (Instrument Landing System), VOR (Very High Frequency Omnidirectional Radio Range), DME (Distance Measure Equipment), Marker and the like and has the advantages of low cost, beautiful interface and good stability.
Description
Technical field
The present invention relates to a kind of aerial navigation signal imitation system of the verification that is applied to fly; Utilize industrial control computer to produce various navigation signals according to concrete mission program and realistic model control aviation signal generator, the present invention is applied to the air traffic control field.
Background technology
The airport air navigation radio aids is used for to aircraft navigator fix information being provided; Yet owing to receive the influence of factors such as site condition, artificial obstacle and electromagnetic interference (EMI); Test also is difficult to guarantee to aerospace plane navigation information accurately to be provided even navigator has been passed through ground check, and this just need carry out actual flight verification to the space electromagnetic wave signal of its emission.
The airflight verification is meant to guaranteeing flight safety; Use is equipped with the aircraft of special-purpose calibration equipment; Relevant specification according to the flight verification; Calibration, check and assess various navigation, radar, communicate by letter and the quality and the tolerance limit thereof of the spacing wave of equipment such as navaid, and provide flight verification report, and foundation and reference are provided for blank pipe department safeguards the calibration of various device according to the result.
Flight verification navigation evaluating system need carry out acquisition process and generate assessment report the spacing wave of desire assessment; Yet in evaluating system exploitation or maintenance process; Frequent flight test is expensive not only; And be difficult to be guaranteed safely, this has just proposed the demand of the various aerial navigation signals of static simulation on ground.
There has been ripe product in present many companies in order to produce the aerial navigation signal of standard; IFR series like AEROFLEX company; But the signal that these products produce can only static manual adjustments; Can't satisfy the demand of flight check system, especially can not satisfy according to different mission programs, the function of the various navigation signals of dynamic similation to actual dynamic change navigation signal.
Summary of the invention
The technical matters that the present invention solves: the defective that overcomes existing aerial navigation signal emulation system; A kind of aerial navigation signal imitation system of the verification that is applied to fly is provided; This system implements in practical application easily, has realized the closed-loop control of simulate signal, has abandoned the shortcoming of the static manual adjustments of existing aerial navigation signal imitation system; Can set up the complete flight verification simulated environment of a cover, the flight check system that has independent intellectual property right for China's research and development provides dummy source.
Structure of the present invention and composition: aerial navigation signal imitation of the present invention system is mainly by industrial control computer and go up the analogue system control program of operation; Gpib bus, ARINC429 bus and respective communication integrated circuit board; The aviation signal generator; Multi-mode receiver, compositions such as feeder line and antenna.
Technical scheme of the present invention: the mode that adopts modular structure and software/hardware to combine makes up the aerial navigation signal imitation system of the check system that is applied to fly.May further comprise the steps:
At first carrying out hardware connects; The GPIB integrated circuit board and the CEI-520 integrated circuit board of pci bus are installed in industrial control computer system; Be respectively applied for realization GPIB communication and communicate by letter, GPIB integrated circuit board external pin is linked to each other with the aviation signal generator, CEI-520 integrated circuit board external pin is linked to each other with the multi-modal navigation receiver with ARINC429; The analogue system control program is installed on industrial control computer; Connect aviation signal generator and emitting antenna through feeder line, simultaneously receiving antenna is linked to each other with multi-mode receiver, the multi-modal navigation receiver that wherein adopts can use the combination of ILS receiver, VOR receiver, Marker receiver and DME receiver etc. to replace.
The hardware connection finishes, and system power-up starts the analogue system control program; Whether inspection GPIB communication is normal; Whether inspection ARINC429 communication is normal, and whether inspection aviation signal generator and multi-modal navigation receiver operate as normal, according to desiring to carry out the subject of verification and the mission program of selection; Select analogue system control program corresponding work mode, simulation produces the navigation signal under the corresponding mission program.The aviation signal generator dynamically produces various navigation signals under the control of analogue system control program; Navigation signal radiate through feeder line and through emitting antenna; Receiving antenna receives the navigation signal of space radiation; And the navigation signal that receives is sent into the multi-modal navigation receiver through feeder line, multi-modal navigation receiver demodulation corresponding navigation signal, and send navigation signal back in the industrial control computer analogue system control program with the form of numeral through the ARINC429 bus; The signal message of analogue system control program through relatively feeding back further kept the Changing Pattern of signal according to corresponding model with certain algorithm.Industrial control computer is the data that promptly feed back of the data of storage emulation signal simultaneously, so that the later stage further handles.
The present invention has following advantage:
1, the present invention is simple in structure, and whole hardware system is made up of Industry Control calculating, aviation signal generator, multi-mode receiver and corresponding connecting line.
2, operation is succinct, flexible.This project is used independently developed software systems, and operating process is simple.Its hardware device is few, between connection also very easily easy.
Description of drawings
Fig. 1 is an aerial navigation signal imitation system hardware device connection diagram of the present invention;
Fig. 2 is an analogue system control program structural drawing of the present invention;
Fig. 3 is a circular flight verification mission program synoptic diagram;
Fig. 4 is a VOR signal simulation control flow chart in the circular flight verification;
Fig. 5 is a radial flight program synoptic diagram;
Fig. 6 is a VOR signal simulation control flow chart in the radial flight verification;
Fig. 7 is an ILS-1 mission program synoptic diagram;
Fig. 8 is course signal simulation control flow chart in the ILS-1 flight verification;
Fig. 9 is an ILS-2 mission program synoptic diagram;
Figure 10 is downslide signal simulation control flow chart in the ILS-2 flight verification.
Embodiment
Below in conjunction with accompanying drawing and embodiment the aerial navigation signal imitation system of the verification that is applied to fly provided by the invention is elaborated.
As shown in Figure 1; The hardware device connection layout of the aerial navigation signal imitation system of the verification that is applied to fly provided by the invention; Mainly comprise industrial control computer 100, aviation signal generator 700 and multi-modal navigation receiver 800, above equipment constitutes a complete closed-loop simulation system.
On described industrial control computer 100, analogue system control program 200 is installed; This program mainly realizes the simulation control of corresponding navigation signal under the various mission programs; For different mission programs corresponding signal simulation model is arranged all, concrete signal simulation mode can specifically be introduced in the back.
Described aviation signal generator 700 connects the GPIB integrated circuit board through gpib bus 500, and is connected with emitting antenna 900 through feeder line.Aviation signal generator 700 adopts the IFR2030 signal generator of AEROFLEX companies, navigation signals such as this generator can static simulation ILS, VOR, DME, MARKER, and this signal generator can carry out dynamic adjustments control through gpib bus.Gpib bus 500 is a standard GPIB joint connecting line.
As shown in Figure 2, the analogue system functions of control program module diagram among the present invention, described analogue system control program 200 mainly comprises like the lower part:
GPIB bottom layer driving module; It mainly is the driving that has encapsulated the GPIB integrated circuit board of NI company production; Encapsulation through this GPIB bottom layer driving module; Make the upper strata to the operation transparentization of GPIB integrated circuit board, all GPIB integrated circuit board details of operations are all accomplished in this GPIB bottom layer driving inside modules, and the interface that upper layer application only need be called this GPIB bottom layer driving module gets final product.
ARINC429 bottom layer driving module; This module is the driving encapsulation to the CEI-520A of GE company integrated circuit board; Encapsulation through this ARINC429 bottom layer driving module; Make the upper strata to the operation transparentization of CEI-520A integrated circuit board, all CEI-520A integrated circuit board details of operations are all accomplished in this ARINC429 bottom layer driving inside modules, and the interface that upper layer application only need be called this ARINC429 bottom layer driving module gets final product.
The IFR20320 communication module; This module package for the various control commands of IFR2030 signal generator; This IFR20320 communication module intrinsic call GPIB bottom layer driving module; Command word is sent to aviation signal generator 700, simultaneously can resolve the character set of returning as a result, this IFR20320 communication module makes the various control transparences of upper strata to aviation signal generator 700.
Communication parameter configuration module, this module mainly realize the parameter initialization configuration of GPIB integrated circuit board 300 communications and the setting of air-mail generator 700 original states.
The fixed point control module; This module mainly is to realize the static state control of navigation signal; That is simulation aviation signal generator 700 various navigation modes panel button function down, mainly comprise VOR fixed point control module, DME control module, the ILS control module of fixing a point of fixing a point.
VOR fixed point control module is mainly used in the static state control of VOR signal.
DME fixed point control module is mainly used in the static state control of DME signal.
ILS fixed point control module is mainly used in the static state control of ILS signal.
The mission program analog module is mainly used in verification subject according to different mission programs and selection according to the various navigation signals of corresponding signal simulation model emulation.This mission program analog module mainly comprises circular flight process simulation, radial flight process simulation, the simulation of ILS-1 mission program, the simulation of ILS-2 mission program etc.; Wherein the circular flight process simulation is mainly used in the Changing Pattern of dynamic simulation VOR signal in the circular flight verification, and control aviation signal generator 700 produces corresponding VOR signal.The radial flight process simulation is mainly used in the Changing Pattern of dynamic simulation VOR signal in the radial flight, and control aviation signal generator 700 produces corresponding VOR signal.The simulation of ILS-1 mission program is mainly used in the Changing Pattern of dynamic simulation course signal in the ILS-1 mission program, and control aviation signal generator 700 produces corresponding signal.The simulation of ILS-2 mission program is mainly used in the Changing Pattern of dynamic simulation downslide signal in the control ILS-2 mission program, and control aviation signal generator 700 produces corresponding signal.
Be the Simulation Control Model that example is introduced signal in the analogue system control program with VOR, ILS signal below.
VHF Omnidirection range (being called for short VOR) belongs to ground-based navigation, is a kind of short-range wireless electricity phase place angle measuring system, is used for the airport and advances nearly landing or air route navigation.Its frequency of operation is between 108.0MHZ～117.95MHZ; The VOR platform mainly is made up of two parts to the signal field of space radiation in the real work; A part is the 30HZ phase place variable-phase signal relevant with the orientation; Another part is the reference signal of 30HZ phase place and orientation-independent, and the phase relation between receiving end benchmark signal and the variable-phase signal draws the azimuth information of beacon station with respect to the magnetic north direction.
Shown in Fig. 3 circular flight program synoptic diagram, aircraft is done circular flight around the VOR platform clockwise or counterclockwise with any required radius in the circular flight, and the flight angle can be greater than 360 degree.
Circular flight is measured parameter information such as position angle, azimuth angle error, the AM depth of 30ZH signal, the AM depth of 9960HZ signal and frequency deviation.In the circular flight process, the influence of getting rid of factors such as environment and landform mainly is the variation of position angle parameter.Thereby the simplest model is that the angle, control azimuth changes in time under the constant situation of other parameters keeping.
Suppose that radius of a circle is R, speed of a ship or plane V, calculate at the uniform velocity under the situation VOR azimuth angle alpha over time rate be:
V*180/(R*π) (1)
And, can adopt integral operation to obtain azimuthal rate of change under the non-at the uniform velocity situation.The variation that can certainly in azimuthal variation, introduce other parameters comes in the actual environment because the variation of the signal condition that a variety of causes causes.In the realistic model of analogue system control program, adopt the value of consult volume of the current VOR signal of timer trigger event correction.Shown in VOR signal simulation control flow chart in the verification of Fig. 4 circular flight, after the timer trigger event,, detect its tolerance limit then to doing an increment operation when forward angle.If exceed the theoretical value scope, then, then signal generator is carried out the angle setting to result's processing of transfiniting; If the result still within theoretical scope, then directly carries out the angle setting to signal generator, the angle value of signal generator is arranged to the numerical value of result of calculation.Whether signal generator is provided with after the completion, needs the read signal generator angle, detect identical with settings.If different needs carries out fault processing, identical words say that bright work is correct, can begin the file storage step.Next need curve waveform and dial plate orientation values be set at display interface, and show the Set For Current angle.Read image data from navigation neceiver then, the feedback data waveform is drawn.
Shown in Fig. 5 radial flight program synoptic diagram, VOR platform radially verification can start at arbitrary height and apart from VOR platform any distance place, does the verification flight of marching into the arena or appearing on the scene.
Radial flight is mainly verified parameter information such as navigation channel signal structure, signal intensity, degree of modulation and vertical polarization; Signal intensity becomes main variation parameter in this mission program; The variation of signal intensity can be provided with according to the decay formula of radio signal with propagation distance under the ideal situation, and formula is following:
A＝20log(λ/4*π*d) (2)
Wherein λ is the wavelength of radio signal, and the wavelength of current demand signal can calculate according to the frequency of operation of VOR; D is the distance of radio propagation, i.e. the distance of verification plane distance VOR platform.In the realistic model of analogue system Control Software, adopt the value of consult volume of the current VOR signal of timer trigger event correction.Shown in VOR signal simulation control flow chart in the verification of Fig. 6 radial flight, after the timer trigger event, the current distance value is calculated, then according to distance calculation current power value.According to performance number signal generator is provided with, the performance number of signal generator is arranged to the numerical value of result of calculation.Whether signal generator is provided with after the completion, needs the read signal generator performance number, detect identical with settings.If different needs carries out fault processing, identical words say that bright work is correct, can begin the file storage step.Next need curve waveform and current aircraft position and signal power value be set at display interface, and show the performance number of Set For Current.Read image data from navigation neceiver then, the feedback data waveform is drawn, and completion is set.
Instrument landing system (ILS) (being called for short ILS); Belong to radio amplitude navigational system; Be a kind ofly the airfield approach Landing Guidance System of localizer, glide path and range information to be provided with the instrument mode, the level that predetermined relatively glissade is provided for the pilot and the indication of the correction in the vertical plane and to runway threshold point apart from indicating.
The navigation principle of localizer, beacon antenna are launched the radiation lobe that two bundle levels are intersected along the runway centerline both sides, respectively by 90HZ and the amplitude modulation of 150HZ low frequency signal.When aircraft flight is on runway centerline; Both indexes of modulation are identical; Navigation channel bar in gauge pointer or the horizontal situation indicator is in the center, and when the left side of aircraft at runway centerline, the index of modulation of 90HZ signal will be greater than the index of modulation of 150HZ; Gauge pointer deflection the right, aircraft is revised the navigation channel to the right; When being positioned at the right of runway centerline, aircraft is revised the navigation channel left.The navigation principle of glide path is identical with localizer.
When the performance of assessment ILS system, adopt three kinds of different mission programs to weigh the navigation quality of course platform, following slide unit.
Shown in Fig. 7 ILS-1 mission program synoptic diagram, this mission program is used to weigh course beacon gap, channel span and symmetry.Aircraft is to be flying radius apart from course platform 10nm (in the sea), and 1000 feet to 1500 feet of height fly one section circular arc in the positive and negative 35 degree scopes in runway centerline both sides.Simultaneously also need be that radius flies one section circular arc and comes checking signal intensity with 18nm in positive and negative 10 degree scopes.
ILS requires the DDM value linear change of course signal in the channel span scope; At first according to half channel span of channel span and the navigation channel symmetry place that calculates that the 90HZ signal is preponderated and the 150HZ signal is preponderated; In this two and half channel span; To 0.155DDM, and in the interval from half channel span critical point to positive and negative 35 degree, DDM value only needs satisfied greater than 0.155DDM and non-ly subtract variation and get final product the DDM value of course beacon from the 0DDM linear change; For simplicity, still see the DDM value from the 0.155DDM linear growth to 0.4DDM here.
Thereby the field sector width that can calculate the middle of fairway both sides according to the channel span and the navigation channel symmetry of preparatory simulation field pattern, be controlled at the interior DDM of place width range then with the angle value linear change.In the realistic model of analogue system Control Software; Adopt the value of consult volume of the current course signal of timer trigger event correction; Shown in course signal simulation control flow chart in the ILS-1 flight verification among Fig. 8, after the timer trigger event, current location information is calculated; And result of calculation detected, estimate whether aircraft is in the navigation channel.If in the navigation channel, then adopt the linear zone Model Calculation; If not in the navigation channel, then adopt nonlinear model to calculate.When aircraft is positioned at the navigation channel, need to judge that further aircraft is in left navigation channel or right navigation channel; In like manner, when aircraft is positioned at non-navigation channel district, need also further to judge that it still is non-navigation channel, right side district that aircraft is positioned at non-navigation channel district, left side.Adopt concrete method to calculate the DDM value according to particular location.According to result of calculation the course DDM value of signal generator is arranged to the result of calculation value then.Whether signal generator is provided with after the completion, needs the course DDM value information of read signal generator, detect identical with settings.If different needs carries out fault processing, identical words say that bright work is correct, can begin the file storage step.Next need curve waveform and current aircraft position and course signal DDM value be set at display interface, and show the course DDM value of Set For Current.Read image data from navigation neceiver then, the feedback data waveform is drawn, and completion is set.
Shown in ILS-2 mission program synoptic diagram among Fig. 9, this mission program is used for weighing the glide path structure, mainly measures gliding angle, glide path width and symmetry.Aircraft crosses runway along the edge of localizer or course beacon action scope with constant altitude, and general the employing highly is 1000 feet, and initial distance is 10nm.
The variation of glide-path localizer signal DDM value also is an approximately linear in the channel span scope, calculates downslide signal 90HZ the preponderate width of signal area of signal area and 150HZ of preponderating according to channel span value and symmetry.According to the flying height h of aircraft, aircraft calculates angle [alpha] apart from the horizontal range d of downslide intercept point:
α＝arctan(d/h) (3)
In the time of in α falls channel span; Signal DDM value from the 0DDM linear change to 0.175DDM; When falling outside the interval, navigation channel, Changing Pattern is non-linear, but because the part outside the channel span is not that verification is paid close attention to; The variation that still can suppose signal DDM value is linear, and variation range is that 0.175DDM is to 0.8DDM.That is model hypothesis signal DDM value has piecewise linear relation with the variation of angle [alpha].In the realistic model of analogue system Control Software; Adopt the value of consult volume of the current downslide signal of timer trigger event correction; Shown in course signal simulation control flow chart in the ILS-2 flight verification among Figure 10, after the timer trigger event, current location information is calculated; And result of calculation detected, estimate whether aircraft is in the navigation channel.If in the navigation channel, then adopt the linear zone Model Calculation; If not in the navigation channel, then adopt nonlinear model to calculate.When aircraft is positioned at the navigation channel, need to judge that further aircraft is in first navigation channel or second navigation channel; In like manner, when aircraft is positioned at non-navigation channel district, need also further to judge that aircraft is positioned at still non-navigation channel district, below, non-navigation channel district, top.Adopt concrete method to calculate the DDM value according to particular location.According to result of calculation the downslide DDM value of signal generator is arranged to the result of calculation value then.Whether signal generator is provided with after the completion, needs the downslide DDM value information of read signal generator, detect identical with settings.If different needs carries out fault processing, identical words say that bright work is correct, can begin the file storage step.Next need curve waveform and current aircraft position and course signal DDM value be set at display interface, and show the downslide DDM value of Set For Current.Read image data from navigation neceiver then, the feedback data waveform is drawn, and completion is set.
And the ILS-3 mission program mainly is used for weighing the structure and the guiding function of localizer and glide path; Aircraft need be 0 track flight in strict accordance with course signal and downslide signal DDM value; Need course signal in signal imitation and the DDM value of downslide signal be set to 0ddm, can add the process of zigzag noise simulation aircraft skew localizer or glide path on this basis.
Emulation for signals such as DME can realize with reference to the emulation mode of VOR signal.
What should explain at last is: above embodiment is only in order to explaining technical scheme of the present invention, but not to its restriction; Although with reference to previous embodiment the present invention has been carried out detailed explanation, those of ordinary skill in the art is to be understood that: it still can be made amendment to the technical scheme that aforementioned each embodiment put down in writing, and perhaps part technical characterictic wherein is equal to replacement; And these are revised or replacement, do not make the spirit and the scope of the essence disengaging various embodiments of the present invention technical scheme of relevant art scheme.
Claims (5)
1. the aerial navigation signal imitation system of the verification that is applied to fly; It is characterized in that: mainly form by industrial control computer, aviation signal generator and multi-modal navigation receiver; Has expansion PCI slot at industrial control computer; The GPIB integrated circuit board and the CEI-520 integrated circuit board of pci bus are installed, are respectively applied for realization GPIB communication and communicate by letter with ARINC429, the GPIB integrated circuit board links to each other with the aviation signal generator; The CEI-520 integrated circuit board links to each other with the multi-modal navigation receiver; The analogue system control program is installed on industrial control computer, and the aviation signal generator is connected with emitting antenna through feeder line, and the multi-modal navigation receiver links to each other with receiving antenna through feeder line simultaneously.
2. the aerial navigation signal imitation system of a kind of verification that is applied to fly according to claim 1, it is characterized in that: the multi-modal navigation receiver replaces with the combination of ILS receiver, VOR receiver, Marker receiver and DME receiver.
3. the aerial navigation signal imitation system of a kind of verification that is applied to fly according to claim 1 is characterized in that: described analogue system control program mainly comprises GPIB bottom layer driving module, ARINC429 bottom layer driving module, IFR20320 communication module, communication parameter configuration module, fixed point control module and mission program analog module.
4. the aerial navigation signal imitation system of a kind of verification that is applied to fly according to claim 3; It is characterized in that: said fixed point control module; Mainly be the static state control that realizes navigation signal; Simulation aviation signal generator various navigation modes panel button function down mainly comprises VOR fixed point control module, DME control module, the ILS control module of fixing a point of fixing a point.
5. the aerial navigation signal imitation system of a kind of verification that is applied to fly according to claim 3; It is characterized in that: said mission program analog module mainly comprises circular flight process simulation, radial flight process simulation, the simulation of ILS-1 mission program and the simulation of ILS-2 mission program; Wherein the circular flight process simulation is mainly used in the Changing Pattern of dynamic simulation VOR signal in the circular flight verification, and control aviation signal generator produces corresponding VOR signal; The radial flight process simulation is mainly used in the Changing Pattern of dynamic simulation VOR signal in the radial flight, and control aviation signal generator produces corresponding VOR signal; The simulation of ILS-1 mission program is mainly used in the Changing Pattern of dynamic simulation course signal in the ILS-1 mission program, and control aviation signal generator produces corresponding signal; The simulation of ILS-2 mission program is mainly used in the Changing Pattern of dynamic simulation downslide signal in the control ILS-2 mission program, and control aviation signal generator produces corresponding signal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011104213003A CN102426426A (en) | 2011-12-15 | 2011-12-15 | Aviation navigation signal simulation system applied to flight check |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011104213003A CN102426426A (en) | 2011-12-15 | 2011-12-15 | Aviation navigation signal simulation system applied to flight check |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102426426A true CN102426426A (en) | 2012-04-25 |
Family
ID=45960426
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011104213003A Pending CN102426426A (en) | 2011-12-15 | 2011-12-15 | Aviation navigation signal simulation system applied to flight check |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102426426A (en) |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103791943A (en) * | 2014-02-24 | 2014-05-14 | 北京航空航天大学 | Missed approach point positional accuracy flight inspection method |
| CN104089630A (en) * | 2014-07-08 | 2014-10-08 | 中国航空无线电电子研究所 | Radio navigation parameter simulation method considering navigation station and tuning information |
| CN105703844A (en) * | 2016-03-10 | 2016-06-22 | 中国计量科学研究院 | VOR standard signal generating method and transmitter |
| CN106991001A (en) * | 2017-04-05 | 2017-07-28 | 中国航空无线电电子研究所 | Radionavigation recognizes simulation system |
| CN109102720A (en) * | 2017-12-25 | 2018-12-28 | 中国民用航空总局第二研究所 | A kind of ILS safe operation state verification, reliability judgment means and method |
| CN109131938A (en) * | 2018-11-06 | 2019-01-04 | 北京航空航天大学东营研究院 | A kind of flight check system |
| CN110187648A (en) * | 2019-06-03 | 2019-08-30 | 西安飞机工业（集团）有限责任公司 | A kind of Aircraft radio system integrated emulation simulated testing system |
| CN110231526A (en) * | 2019-06-11 | 2019-09-13 | 中国民用航空总局第二研究所 | Civil air navigation aids active Electromagnetic environment assessment system and its appraisal procedure |
| CN110462418A (en) * | 2017-02-02 | 2019-11-15 | 弗劳恩霍夫应用研究促进协会 | Positioning using millimeter wave wave beam infrastructure to unmanned plane |
| CN110987025A (en) * | 2020-03-03 | 2020-04-10 | 北京航空航天大学东营研究院 | Display device for carrying out unmanned aerial vehicle flight verification on very high frequency omnidirectional beacon |
| CN111007555A (en) * | 2019-11-28 | 2020-04-14 | 中国航空工业集团公司西安航空计算技术研究所 | General aircraft airborne integrated navigation system and navigation method |
| CN111404578A (en) * | 2020-06-03 | 2020-07-10 | 天津七一二通信广播股份有限公司 | Very high frequency transceiver and ground equipment of ground based on GBAS |
| CN113282098A (en) * | 2021-07-08 | 2021-08-20 | 北京航空航天大学东营研究院 | Method for improving flight verification accuracy of instrument landing system |
| CN113593307A (en) * | 2021-09-29 | 2021-11-02 | 北京航空航天大学东营研究院 | Unmanned aerial vehicle-based data acquisition system and method for aviation navigation equipment |
| CN117688779A (en) * | 2024-01-29 | 2024-03-12 | 北京蓝天航空科技股份有限公司 | Simulation scene construction method, device, navigation simulation system, equipment and medium |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5610600A (en) * | 1994-06-07 | 1997-03-11 | Koenig; Robert H. | Operation verification system and method for navigational instruments |
| US6298318B1 (en) * | 1998-07-01 | 2001-10-02 | Ching-Fang Lin | Real-time IMU signal emulation method for test of Guidance Navigation and Control systems |
| CN101267987A (en) * | 2005-09-22 | 2008-09-17 | 法国空中巴士公司 | Method and device for carrying out at least one flight testing on an aircraft and the use thereof |
| CN201488738U (en) * | 2009-08-05 | 2010-05-26 | 成都飞亚航空设备应用研究所有限公司 | Signal formation system of integrated navigation verification instrument |
| WO2010123611A1 (en) * | 2009-02-02 | 2010-10-28 | Aerovironment | Multimode unmanned aerial vehicle |
| CN101963668A (en) * | 2010-08-19 | 2011-02-02 | 北京华力创通科技股份有限公司 | Method for realizing real-time closed-loop synchronization control by simulating satellite navigation signal |
| CN102147473A (en) * | 2010-12-17 | 2011-08-10 | 航天恒星科技有限公司 | Common-frequency multi-system satellite navigation signal generation system |
-
2011
- 2011-12-15 CN CN2011104213003A patent/CN102426426A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5610600A (en) * | 1994-06-07 | 1997-03-11 | Koenig; Robert H. | Operation verification system and method for navigational instruments |
| US6298318B1 (en) * | 1998-07-01 | 2001-10-02 | Ching-Fang Lin | Real-time IMU signal emulation method for test of Guidance Navigation and Control systems |
| CN101267987A (en) * | 2005-09-22 | 2008-09-17 | 法国空中巴士公司 | Method and device for carrying out at least one flight testing on an aircraft and the use thereof |
| WO2010123611A1 (en) * | 2009-02-02 | 2010-10-28 | Aerovironment | Multimode unmanned aerial vehicle |
| CN201488738U (en) * | 2009-08-05 | 2010-05-26 | 成都飞亚航空设备应用研究所有限公司 | Signal formation system of integrated navigation verification instrument |
| CN101963668A (en) * | 2010-08-19 | 2011-02-02 | 北京华力创通科技股份有限公司 | Method for realizing real-time closed-loop synchronization control by simulating satellite navigation signal |
| CN102147473A (en) * | 2010-12-17 | 2011-08-10 | 航天恒星科技有限公司 | Common-frequency multi-system satellite navigation signal generation system |
Non-Patent Citations (1)
| Title |
|---|
| 张全明等: "飞行校验中航空导航信号的模拟实现", 《测控技术》, vol. 28, no. 12, 31 December 2009 (2009-12-31) * |
Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103791943B (en) * | 2014-02-24 | 2016-08-17 | 北京航空航天大学 | MAP positioning precision flight check method |
| CN103791943A (en) * | 2014-02-24 | 2014-05-14 | 北京航空航天大学 | Missed approach point positional accuracy flight inspection method |
| CN104089630A (en) * | 2014-07-08 | 2014-10-08 | 中国航空无线电电子研究所 | Radio navigation parameter simulation method considering navigation station and tuning information |
| CN104089630B (en) * | 2014-07-08 | 2016-11-23 | 中国航空无线电电子研究所 | A kind of radionavigation parameters simulation method considering guidance station and tuning information |
| CN105703844A (en) * | 2016-03-10 | 2016-06-22 | 中国计量科学研究院 | VOR standard signal generating method and transmitter |
| CN110462418A (en) * | 2017-02-02 | 2019-11-15 | 弗劳恩霍夫应用研究促进协会 | Positioning using millimeter wave wave beam infrastructure to unmanned plane |
| CN110462418B (en) * | 2017-02-02 | 2024-02-06 | 弗劳恩霍夫应用研究促进协会 | Positioning of drones using millimeter wave beam infrastructure |
| US11755037B2 (en) | 2017-02-02 | 2023-09-12 | Fraunhofer-Gesellschaft Zur Foerderung Der Angewandten Forschung E.V. | Positioning of unmanned aerial vehicles using millimeter-wave beam infrastructure |
| CN106991001A (en) * | 2017-04-05 | 2017-07-28 | 中国航空无线电电子研究所 | Radionavigation recognizes simulation system |
| CN106991001B (en) * | 2017-04-05 | 2020-09-15 | 中国航空无线电电子研究所 | Radio navigation identification simulation system |
| CN109102720A (en) * | 2017-12-25 | 2018-12-28 | 中国民用航空总局第二研究所 | A kind of ILS safe operation state verification, reliability judgment means and method |
| CN109131938A (en) * | 2018-11-06 | 2019-01-04 | 北京航空航天大学东营研究院 | A kind of flight check system |
| CN109131938B (en) * | 2018-11-06 | 2020-03-27 | 北京航空航天大学东营研究院 | Flight checking system |
| CN110187648A (en) * | 2019-06-03 | 2019-08-30 | 西安飞机工业（集团）有限责任公司 | A kind of Aircraft radio system integrated emulation simulated testing system |
| CN110231526A (en) * | 2019-06-11 | 2019-09-13 | 中国民用航空总局第二研究所 | Civil air navigation aids active Electromagnetic environment assessment system and its appraisal procedure |
| CN111007555A (en) * | 2019-11-28 | 2020-04-14 | 中国航空工业集团公司西安航空计算技术研究所 | General aircraft airborne integrated navigation system and navigation method |
| CN110987025A (en) * | 2020-03-03 | 2020-04-10 | 北京航空航天大学东营研究院 | Display device for carrying out unmanned aerial vehicle flight verification on very high frequency omnidirectional beacon |
| CN111404578A (en) * | 2020-06-03 | 2020-07-10 | 天津七一二通信广播股份有限公司 | Very high frequency transceiver and ground equipment of ground based on GBAS |
| CN113282098B (en) * | 2021-07-08 | 2021-10-08 | 北京航空航天大学东营研究院 | Method for improving flight verification accuracy of instrument landing system |
| CN113282098A (en) * | 2021-07-08 | 2021-08-20 | 北京航空航天大学东营研究院 | Method for improving flight verification accuracy of instrument landing system |
| CN113593307A (en) * | 2021-09-29 | 2021-11-02 | 北京航空航天大学东营研究院 | Unmanned aerial vehicle-based data acquisition system and method for aviation navigation equipment |
| CN117688779A (en) * | 2024-01-29 | 2024-03-12 | 北京蓝天航空科技股份有限公司 | Simulation scene construction method, device, navigation simulation system, equipment and medium |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102426426A (en) | Aviation navigation signal simulation system applied to flight check | |
| US4490117A (en) | Inflight IFR procedures simulator | |
| CN103163507A (en) | Radar tracking low-altitude small-target dynamic precision calibrating method and device | |
| CN106093855B (en) | The navigation control method and control system of unmanned plane | |
| CN107421565B (en) | Instrument landing system lower slide wire calibration system based on unmanned aerial vehicle | |
| CN102722184A (en) | Monopulse antenna angle simulation tracking method | |
| CN104133121A (en) | Automatic test method for directional diagram of short-wave large-scale antenna array | |
| CN110231526A (en) | Civil air navigation aids active Electromagnetic environment assessment system and its appraisal procedure | |
| CN109131938A (en) | A kind of flight check system | |
| CN205898998U (en) | Unmanned aerial vehicle's navigation control system | |
| CN103631250B (en) | A kind of method of elevation axis of antenna tracking accuracy being carried out to ground test | |
| CN110501667B (en) | Test system and ground test method of ultrashort wave orientation instrument | |
| CN110058267A (en) | A kind of quick Navigation of Pilotless Aircraft deception system of gapless and method | |
| CN202421491U (en) | Multilateral positioning system based on distributed clocks | |
| CN107024702A (en) | A kind of half control system circled simulation flat in kind based on inertia/satellite navigation | |
| CN105066986B (en) | A kind of multi-mode uploads the Ground landing system and its control method of system | |
| RU2501031C2 (en) | Method for flight inspection of ground-based radio flight support equipment and apparatus for realising said method | |
| Barrado et al. | Remote flight inspection using unmanned aircraft | |
| CN102590786A (en) | Multilateral positioning system based on distributed clock | |
| CN208459855U (en) | A kind of unmanned plane landing-gear based on laser conduction | |
| RU2214943C1 (en) | Method of landing flying vehicle | |
| CN205450264U (en) | TACAN monitoring facilities | |
| RU2285932C1 (en) | System for determining spatial position of object | |
| CN205404807U (en) | Meteorological electro -optical distance measurment(EDM) system that corrects device and correct device based on meteorological phenomena | |
| CN210774085U (en) | Compass in-situ comprehensive detection system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20120425 |