CN205353627U - Device that control course antenna switches in aircraft control system - Google Patents
Device that control course antenna switches in aircraft control system Download PDFInfo
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- CN205353627U CN205353627U CN201520915142.0U CN201520915142U CN205353627U CN 205353627 U CN205353627 U CN 205353627U CN 201520915142 U CN201520915142 U CN 201520915142U CN 205353627 U CN205353627 U CN 205353627U
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Abstract
The utility model discloses a device that control course antenna switches in aircraft control system, a serial communication port, include: the information acquisition unit, it is used for acquireing the landing mode information that is used for instructing the aircraft landing mode to acquire the landing stage information that is used for instructing the aircraft landing stage, antenna selected cell, it is used for the basis landing mode information with the selection of course antenna is confirmed to landing stage information, order the control unit, it is used for the basis the selection of course antenna generates switching command to control antenna change over switch is right the course antenna is implemented to switch. Through the utility model discloses a course antenna that the device used present switches over, can make aircraft alternative use signal the best course antenna under different situations, has strengthened the course way of aircraft to catch and traceability, and through the control to switching over the state feedback signal, can guarantee that antenna change over switch can normally work, further improve the reliable degree and the security performance of system.
Description
Technical field
This utility model relates to technical field of flight control, specifically, this utility model relates to a kind of device entering to control near process course antenna switching in aircraft landing, this utility model is primarily adapted for use in and is provided simultaneously with instrument landing (ILS) function and satellite and lands the aircraft of (GLS) function, and be these aircrafts select the antenna of the best using as course signal input source at different mission phases.
Background technology
The course signal source that seating plane adopts when carrying out approach for landing by instrument landing system is from the following two kinds antenna: a kind of LOC antenna being mounted in head, a kind of VOR/LOC antenna being mounted in vertical fin.General flivver all adopts the VOR/LOC antenna of vertical fin as LOC signal input sources, big aircraft then adopts the LOC antenna of head as LOC signal input sources (because instrument landing (ILS) ground platform is generally all arranged on runway two ends, the fuselage of big aircraft is likely to the VOR/LOC antenna of vertical fin is caused block).Development along with satellite landing technology, aircraft can also use satellite landing approach to carry out approach for landing, which needs to receive broadcast (VDB) signal from the VHF data of ground platform, and satellite landing (GLS) earth station can be installed on the optional position (without being positioned on runway) on airport.Possess omni-directional owing to the VOR/LOC antenna of vertical fin compares to the LOC antenna of head, therefore adopt when using satellite landing approach the VOR/LOC antenna of vertical fin to be more suitable for as VDB signal source.Land and during GLS landing function when aircraft possesses ILS, need to switch between head LOC antenna and vertical fin VOR/LOC antenna, to select optimal antenna as signal source.
Therefore, for possessing the aircraft of ILS landing and GLS landing function, it is desirable to provide a kind of scheme simply and efficiently is to realize the antenna switching of control course.
Utility model content
In order to solve above-mentioned technical problem, first aspect of the present utility model provides a kind of device controlling course antenna switching in aircraft control system, it is characterized in that, including: information acquisition unit, it is configured to obtain the landing approach information for indicating aircraft landing mode, and is configured to obtain the landing period information for indicating the aircraft landing stage；It line options unit, its selection being configured to determine course antenna according to described landing approach information and described landing period information；Command control unit, it is configured to the selection according to described course antenna and generates switching command, to control antenna change-over switch to the enforcement switching of described course antenna.
Especially, described information acquisition unit is additionally configured to the switching state feedback information after obtaining switching；Described device also includes: judging unit, and whether it is configured to the selection of course antenna described in comparison consistent with described switching state feedback information；When Alarm Unit, its selection being configured as described course antenna and described switching state feedback information are inconsistent, then send warning information.
Especially, described landing approach is instrument landing or satellite landing.
Especially, described landing period is preliminary stage or later stage.
Especially, described sky line options unit is further configured to: when described landing approach is instrument landing and described landing period is preliminary stage, selects vertical fin VOR/LOC antenna；When described landing approach is instrument landing and described landing period is later stage, select head LOC antenna；When described landing approach is that satellite lands and described landing period is preliminary stage, select vertical fin VOR/LOC antenna；When described landing approach is that satellite lands and described landing period is later stage, select vertical fin VOR/LOC antenna.
By device of the present utility model, currently used course antenna is switched over, it is possible to making aircraft select the course antenna using signal best under different situations, the localizer strengthening aircraft is caught and tracking ability；And by the monitoring to switching status feedback signal, and with the contrast of switch-over control signal, can the duty of consersion unit in time, warning information is provided when necessary, so that it is guaranteed that antenna change-over switch can normal operation, further increase reliability and the security performance of system.
Accompanying drawing explanation
By reading the detailed description that non-limiting example is made made with reference to the following drawings, other features, objects and advantages of the present utility model will become more apparent:
Fig. 1 illustrates the schematic diagram of the aircraft control system containing the device according to the switching of control course disclosed in the utility model antenna；
Fig. 2 illustrates according to a kind of method flow diagram controlling course antenna switching in aircraft control system disclosed in the utility model；And
Fig. 3 illustrates according to a kind of apparatus module figure controlling course antenna switching in aircraft control system disclosed in the utility model.
Detailed description of the invention
In the specific descriptions of following preferred embodiment, reference is constituted the accompanying drawing appended by this utility model part.Appended accompanying drawing has been illustrated by way of example and has been capable of specific embodiment of the present utility model.The embodiment of example is not intended as limit according to all embodiments of the present utility model.It is appreciated that under the premise not necessarily departing from scope of the present utility model, it is possible to use other embodiments, it is also possible to carry out structural or logicality amendment.Therefore, following specific descriptions are also nonrestrictive, and scope of the present utility model is defined by the claims appended hereto.In addition, although describing the step of method in description in a particular order, but this does not require that or implies and must operate to perform these according to this particular order, or having to carry out all shown operation could realize desired result, on the contrary, the step of description can change execution sequence.Additionally or alternatively, it is convenient to omit some step, multiple steps are merged into a step and performs, and/or a step is decomposed into the execution of multiple step.
Which in the prior art, for the aircraft possessing ILS landing and GLS landing function, judge to use antenna gain higher relative to the position of ground platform usually by aircraft, thus currently used course antenna is selected.Which needs to compare the position of ground platform in the GPS location of aircraft, inertial navigation position, flight maneuver and navigational route database, and calculation is complicated, it is necessary to the software of equipment is developed, relatively costly.
Mentality of designing of the present utility model is: determine that aircraft which antenna (head LOC antenna or vertical fin VOR/LOC antenna) when the different approach for landing stage can receive optimum signal by qualitative analysis, thus proposing a kind of simple control logic to control the selection for course antenna, in addition this utility model also further confirms that the result of course antenna switching, sends alarm prompt to ensure flight safety when the not correctly switching of course antenna.
The antenna of the localizer LOC of VOR nodirectional beacon VOR, ILS function and the very-high-frequency PECVD VDB three of GLS function receives frequency all in a frequency range (about 108MHz～120MHz).Therefore in actual applications, this three can share an antenna.In general, the VOR/LOC antenna being installed on aircraft vertical fin top is the carrier implementing these three receive capabilities, and the LOC antenna being arranged in nose radar cover is the carrier implementing ILS function.Antenna service condition under tri-kinds of functions of ILS, GLS, VOR is as shown in table 1.
Table-1:ILS, GLS and VOR function antenna service condition table
| Function and signal | Antenna used |
| The LOC signal of ILS | Vertical fin VOR/LOC antenna or head LOC antenna |
| The VDB signal of GLS | Vertical fin VOR/LOC antenna |
| VOR signal | Vertical fin VOR/LOC antenna |
Visible, under different landing patterns, it is necessary to receive the signal from different antennae.
In general, GLS landing function and ILS landing function are all integrated in a navigation neceiver, therefore need to use antenna change-over switch that the aircraft antenna that (ILS or GLS) uses under difference landing pattern is switched over.
In addition, land even with ILS pattern, under different mission phases, antenna used (vertical fin VOR/LOC antenna or head LOC antenna) is also had different optimum selections.Owing to the VOR/LOC antenna of vertical fin has a range of receiving of 360 °, and the LOC antenna of head can only receive the signal within the maximum 180 ° of scopes in head front.Therefore when aircraft takes ILS mode to land, after airfield approach, if aircraft flight flight path is bigger with runway angle, the LOC antenna of head is it would be possible to catch less than signal (such as, from the signal that fuselage rear direction is sent), now adopt the VOR/LOC antenna of vertical fin to catch LOC signal, can better ensure that aircraft receives LOC signal；And when aircraft enters approach path, the VOR/LOC antenna of vertical fin is likely subject to fuselage and blocks, and now following the trail of LOC signal with the LOC antenna of head is optimum selection.
It is to say, under ILS landing approach, if entering nearly landing period for difference, the VOR/LOC antenna of vertical fin and the LOC antenna of head are switched over selection with antenna change-over switch, then aircraft is conducive to obtain best LOC signal.
To sum up analyzing, for different landing approach and different landing periods in this utility model, antenna selection strategy is as shown in table 2:
The different approach for landing mode of table-2 and the optimal antenna selection strategy under the stage
| Landing approach and stage | Optimal antenna selection strategy |
| GLS approach for landing: omnidistance | Vertical fin VOR/LOC antenna |
| ILS approach for landing: early stage | Vertical fin VOR/LOC antenna |
| ILS approach for landing: later stage | LOC antenna |
What affect sky line options as known from Table 2 is the landing approach that aircraft adopts because have two: one；Two is the mission phase residing for aircraft.Owing to, after selecting GLS mode to land, optimal antenna should be the VOR/LOC antenna of vertical fin all the time, therefore now fly into nearly landing period without discussing.And if when the landing approach of aircraft is ILS mode, then needing to consider that flight landing enters the nearly stage.
Analyzing, through utility model people, the critical events finding to relate to/judge mission phase is: whether pilot presses APPR key.Marching into the arena at aircraft, but before pilot do not press APPR key, the LOC antenna of aircraft begins to try to catch LOC signal, now owing to the angular deviation of head and ILS bottom surface platform is likely to relatively big, best LOC antenna processing strategy is the VOR/LOC antenna of vertical fin；After pilot presses APPR key, aircraft enters into nearly armed, and aircraft to face toward runway centerline rapid alignment, after capturing LOC centrage, then captures GS, and auto-approach pattern is switched on, and the LOC antenna now using head is optimal strategy.Therefore, it can two stages whether pressing APPR key to divide landing, pressing is preliminary stage before, presses afterwards for later stage.Can be seen that antenna selection strategy is as shown in table 3 below with the corresponding relation of the event of triggering in this utility model.
Table 3 combination event and antenna selection strategy mapping table
In this utility model, it is possible to landing period is set as that event A, A=1 represent that APPR key is not pressed, and A=0 represents that APPR key is pressed；Landing approach is set as that event B, B=0 represent that landing approach adopts ILS pattern, and B=1 represents that landing approach adopts GLS pattern；Configuration switch control instruction (Command) represents the VOR/LOC antenna selecting vertical fin for C, C=1, and C=0 represents the LOC antenna selecting head.The logical expression that then can obtain control instruction C and event AB is: C=A+B.
Additionally, due to switching switch exists the risk being not carried out switching command, therefore can judge whether switch correctly performs control instruction by whether contrast switching control instruction C is consistent with switching switch feedback state.Configuration switch feedback of status (Feedback) represents, for F, F=1, the VOR/LOC antenna that on off state feedback display current antenna is vertical fin, and F=0 represents the LOC antenna that on off state feedback display current antenna is prow.
So, after powering on before taking off, according to switch logic, the VOR/LOC antenna of vertical fin should be received, if now switch is made that correct switching selects, then should be C=1, F=1.If switch does not correctly switch, then C=1, F=0 now should eject warning information: antenna handoff error (ANTSwitchFail).
If aircraft is in landing mission, landing approach selects GLS mode or selects ILS mode, and pilot does not press APPR key temporarily, then should keep C=1, the state of F=1, the decision logic that in this situation, whether normal the duty of switch is is then identical with said circumstances.
If aircraft is in landing mission, landing approach selects ILS mode, and pilot presses APPR key, and now switch should be switched to head LOC antenna from vertical fin VOR/LOC antenna.If the correct switching of switch, should be C=0, F=0.Do not switch if now switching, be then C=0, F=1, now should eject warning information: antenna handoff error (ANTSwitchFail).To sum up, antenna change-over switch should occur that the state of warning information is as shown in table 4 below.
Table-4 antenna change-over switch failure state warning watch
On the basis that above-mentioned utility model is conceived, describe method and apparatus of the present utility model in detail below with reference to accompanying drawing.Fig. 1 illustrates the schematic diagram of the aircraft control system 100 containing the device 300 according to the switching of control course disclosed in the utility model antenna；Antenna change-over switch 200 is for implementing the switching of course antenna within the system, namely switches to another course antenna from a course antenna.The device 300 of this control course antenna switching is connected to control this antenna change-over switch 200 and implements the switching of course antenna with antenna change-over switch 200.
The similar simple electric brake of operation principle of this antenna change-over switch, this antenna change-over switch includes: radio frequency unit, power subsystem, control unit and display unit.This switch is powered by power subsystem by 28V unidirectional current；Control unit is triggered by a discrete control signal from device 300 (C port) and switches over control；Display unit can feed back currently selected antenna condition.Table 5 gives each port and the corresponding function thereof of antenna change-over switch in figure.
Table-5 antenna change-over switch port function
Fig. 2 illustrates according to a kind of method flow diagram controlling course antenna switching in aircraft control system disclosed in the utility model；Fig. 3 illustrates the module map according to a kind of device 300 controlling course antenna switching in aircraft control system disclosed in the utility model.
The device 300 of this control course antenna switching may be located in flight control computer or realized by flight control computer and other electronic hardware.This device 300 includes: information acquisition unit 302, sky line options unit 304, command control unit 306.In a preferred embodiment, this device 300 also includes judging unit 308, Alarm Unit 310.Wherein the function of this judging unit 308 also can be substituted by cas system, is namely drawn control instruction signal C and switching status feedback signal F by cas system and carries out contrasting to provide the decision whether alerted.
Unit in this device 300 can hardware module and/or logic circuit by realizing corresponding function be constituted respectively, wherein, annexation between unit is as shown in Figure 3, information acquisition unit 302 and sky line options unit 304 communicate to connect, it line options unit 304 communicates to connect with command control unit 306, command control unit 306 and judging unit 308 communicate to connect, it is judged that unit 308 and Alarm Unit 310 communicate to connect.
Scheme disclosed in the utility model is specific as follows:
In step 202., information acquisition unit 302 obtains landing approach information, and which kind of mode is this information use land for indicating aircraft.Example of the present utility model has two kinds of landing approach, it may be assumed that instrument landing and satellite land.
It is to be noted that this utility model is not limited to both the above landing approach, it is also possible to be other landing approach.
In step 204, information acquisition unit 302 obtains landing period information, and this information is used for indicating which kind of landing period aircraft is currently at.Example of the present utility model has two kinds of landing periods, it may be assumed that preliminary stage or later stage.In a specific embodiment, it is possible to whether be pressed confirmation by APPR key and be in which kind of landing period, namely generate the instruction indication signal that whether is pressed of APPR key, using the signal of this instruction APPR key as landing period information.When this signal represents that APPR key is not pressed, then it represents that aircraft is in landing preliminary stage；When this signal represents that APPR key is pressed, then it represents that aircraft is in landing later stage.
It is to be noted that this utility model is not limited to landing period to be divided into both the above landing period, therefore this landing period can also be other landing periods.
In step 206, sky line options unit 304 obtains landing approach information and landing period information from information acquisition unit 302, and then sky line options unit 304 determines the selection of course antenna according to landing approach information and landing period information.Wherein, the function of the described selection determining course antenna according to landing approach information and landing period information can be realized by one or more electronic modules or logic circuit.
Concrete, when described landing approach is instrument landing and described landing period is preliminary stage, select vertical fin VOR/LOC antenna；When described landing approach is instrument landing and described landing period is later stage, select head LOC antenna；When described landing approach is that satellite lands and described landing period is preliminary stage, select vertical fin VOR/LOC antenna；When described landing approach is that satellite lands and described landing period is later stage, select vertical fin VOR/LOC antenna.Then 304 selected results of sky line options unit send to command control unit 306.
In a step 208, command control unit 306 generates according to the result of this selection and controls switching command and send to antenna change-over switch 200, to control antenna change-over switch to the enforcement switching of described course antenna.In another specific embodiment, command control unit 306 also sends this control switching command to judging unit 308.
In step 210, information acquisition unit 302 obtains the switching state feedback information F after switching, and this switching state feedback information F is sent to judging unit 308.
In the step 212, judging unit 308 is from controlling to confirm switching command the selection of course antenna, whether the selection then comparing described course antenna is consistent with described switching state feedback information, if inconsistent, informs warning unit 310, in order to warning unit 310 can send alarm.
Although the device 300 of this example is illustrated in figure 3, but Fig. 3 one or more unit illustrated can merged, separate, rearrange, omit, remove and/or be implemented by any way.Further, the information acquisition unit 302 of example, sky line options unit 304, command control unit 306, judging unit 308, Alarm Unit 310 can be implemented in combination in by hardware, software, firmware and/or any of hardware, software and/or firmware.More generally, any one in the said units of example can by one or more circuit, programmable processor, special IC (ASIC), and programmable logic device (PLD) and/or field programmable logic device (FPLD) etc. realize.
It is obvious to a person skilled in the art that this utility model is not limited to the details of above-mentioned one exemplary embodiment, and when without departing substantially from spirit of the present utility model or basic feature, it is possible to realize this utility model in other specific forms.Therefore, in any case, embodiment all should be regarded as exemplary, and be nonrestrictive.Additionally, it will be evident that " including " word is not excluded for other elements and step, and wording " one " is not excluded for plural number.In device claim, multiple elements of statement can also be realized by an element.The first, the second word such as grade is used for representing title, and is not offered as any specific order.
Claims (5)
1. the device controlling course antenna switching in aircraft control system, it is characterised in that including:
Information acquisition unit, it is realized by hardware module, and is configured to obtain the landing approach information for indicating aircraft landing mode, and is configured to obtain the landing period information for indicating the aircraft landing stage；
It line options unit, it is realized by hardware module, and is configured to determine the selection of course antenna according to described landing approach information and described landing period information；
Command control unit, it is realized by hardware module, and is configured to the selection generation switching command according to described course antenna, to control antenna change-over switch to the enforcement switching of described course antenna.
2. device according to claim 1, it is characterised in that described information acquisition unit is additionally configured to the switching state feedback information after obtaining switching；
Described device also includes:
Judging unit, it is realized by hardware module, and whether be configured to the selection of course antenna described in comparison consistent with described switching state feedback information；
Alarm Unit, it is realized by hardware module, and be configured as the selection of described course antenna and described switching state feedback information inconsistent time, then send warning information.
3. device according to claim 2, it is characterised in that described landing approach is instrument landing or satellite landing.
4. device according to claim 2, it is characterised in that described landing period is preliminary stage or later stage.
5. the device according to claim 3 or 4, it is characterised in that described sky line options unit is further configured to:
When described landing approach is instrument landing and described landing period is preliminary stage, select vertical fin VOR/LOC antenna；
When described landing approach is instrument landing and described landing period is later stage, select head LOC antenna；
When described landing approach is that satellite lands and described landing period is preliminary stage, select vertical fin VOR/LOC antenna；
When described landing approach is that satellite lands and described landing period is later stage, select vertical fin VOR/LOC antenna.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110488864A (en) * | 2019-08-15 | 2019-11-22 | 中国商用飞机有限责任公司 | The method and system of the LOC signal in flight control system for correcting aircraft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110488864A (en) * | 2019-08-15 | 2019-11-22 | 中国商用飞机有限责任公司 | The method and system of the LOC signal in flight control system for correcting aircraft |
| CN110488864B (en) * | 2019-08-15 | 2021-12-03 | 中国商用飞机有限责任公司 | Method and system for modifying a LOC signal in a flight control system of an aircraft |
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